N620PC

Part: LEVER — MALFUNCTIONED (MLG)

MSY - AFTER TAKEOFF LANDING GEAR WOULD NOT RETRACT. AIRCRAFT RETURNED TO MSY WITH NO INCIDENT. RESET LANDING GEAR LEVER AND PRESSURE WARNING CIRCUIT BREAKERS, SYSTEM CHECKED NORMAL PER MM 32-31-0. (M)

Part: FLOORBEAM — CORRODED (FUSELAGE)

SJO - FOUND DURING C-CHECK, CORROSION ON FLOORBEAM LOWER CHORD AT BS 867, RBL 25 AND WL 202. REPAIRED FLOORBEAM LOWER CHORD AT BS 867 WL 202 BETWEEN RBL 16 AND RBL 36 IAW SRM 53-10-9 FIG 7. (M)

Part: BULKHEAD — DAMAGED (FUSELAGE)

SJO - DURING C-CHECK, TEMPORARY REPAIR AT BS 178 FROM LBL 8 TO LBL 15 AND FROM WL 233 AND WL 238. INSTALLED PERMANENT REPAIR AT BS 178 FROM LBL 8 TO LBL 15 AND FROM WL 233 TO WL 238 IAW SRM 53-10-1 FIG 1. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, TEMPORARY REPAIR AT BS 178 FROM RBL 8 TO RBL 15 AND BETWEEN WL 233 TO WL 238. INSTALLED PERMANENT REPAIR AT BS 178 FROM RBL TO RBL 15 AND FROM WL 233 TO WL 238 IAW SRM 53-10-11 FIG 1. (M)

Part: SKIN — DELAMINATED (NR 1 SPOILER)

SJO - DURING C-CHECK, LEFT WING NR 1 SPOILER UPPER SKIN WITH DELAMINATION. REPAIRED NR 1 SPOILER IAW COOPESA EO COO-CMP-3-57-609-00, DATED OCT 2, 2000. (M)

Part: RUDDER — DELAMINATED (TAIL)

SJO - DURING C-CHECK, RUDDER DELAMINATION BETWEEN STA 17.25 AND STA 35.25. REPAIRED RUDDER IAW SRM 51-40-9, PARAGRAPH 3 AND PARAGRAPH 5, FIG 3. (X)

Part: SKIN — DELAMINATED (FLAP)

SJO - FOUND DURING C-CHECK, LEFT OUTBOARD FLIPPER FLAP UPPER AND LOWER SKIN WITH DELAMINATION. REPAIRED FLIPPER FLAP SKIN IAW COOPESA EO COO-CMP-3-57-607-00 DATED SEPT 29, 2000. (M)

Part: SKIN — DAMAGED (E/E DOOR)

SJO - DURING C-CHECK, RIGHT FORWARD AND AFT CORNERS WORN ON E/E DOOR. REPAIRED RIGHT SKIN SECTIONS AT FORWARD AND AFT CORNERS IAW SRM 52-00-3 FIG 5. (M)

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2

DURING C-CHECK, CORROSION (LEVEL 2) ON WEB SECTION AT BS 178 FROM LBL 16 TO LBL 29 AND BETWEEN WL 180 AND WL 240. REPAIRED WEB SECTION AT BS 178 FROM LBL 16 TO LBL 29 AND BETWEEN WL 180 AND WL 240 IAW SRM 51-10-1 PAGE 8, PARA 6. (X)

Part: SKIN — DELAMINATED (LT WING)

SJO - FOUND DURING C-CHECK, LEFT WING SPAR LOWER ACCESS PANEL INNER SKIN DELAMINTATED FROM RSS 339 TO 380. REPAIRED PANEL IAW COOPESA EO COO-CMP-3-57-608-00, DATED 9/29/2000. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, MFEC SKIN CRACK ON LOWER ROW OF FASTENERS AT BS 877 STRINGER 25R. REPAIRED SKIN FROM BS 870 TO BS 883 AND FROM STRINGERS 25R TO 27R IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, FOUND MFEC SKIN CRACKED INDICATIONS 3 INCHES LONG FROM BS 515 TO 518 AT STRINGER 10R. REPAIRED SKIN FROM BS 510 TO BS 500A PLUS 1 AND BETWEEN STRINGERS 9R TO 11R IAW SRM 53-30-3 FIG 13. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, MFEC SKIN CRACK INDICATION AT BS 778 STRINGER 25L. REPAIRED SKIN FROM BS 751 TO BS 795 AND BETWEEN STRINGERS 24L AND 26L IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, MFEC SKIN CRACK INDICATION, 2 INCHES LONG, ON UPPER ROW OF FASTENERS AT STRINGER 26L BETWEEN FROM BS 460 TO BS 464. REPAIRED SKIN FROM BS 455 TO BS 466 AND FROM STRINGERS 25L TO 27L IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, LFEC SKIN CRACK INDICATION BETWEEN BS 755 AND BS 760 AT STRINGER 25R. REPAIRED SKIN FROM BS 755 TO BS 769 BETWEEN STRINGERS 24R AND 26R IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, MFEC SKIN CRACK INDICATION ON LOWER ROW OF FASTENERS AT BS 1006 STRINGER 4L. REPAIRED SKIN FROM BS 1000 TO BS 1012 AND BETWEEN STRINGER 3L AND 5L IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, MFEC SKIN CRACK INDICATION AT BS 366 STRINGER 19R. REPAIRED SKIN FROM BS 306 TO BS 371 BETWEEN STRINGERS 18R AND 20R IAW SRM 53-30-3 FIG 13 DETAIL I. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, VERTICAL CHORD CRACKED AT BS 178. LBL 5.7 AND WL 184. FABRICATED AND REPLACED VERTICAL CHORD AT BS 178, LBL 5.7 AND FROM WL 177 AND WL 197 IAW SRM 53-10-11 FIG 8 AND SRM 51-10-1. (X)

Part: SKIN — DEBONDED (WINDOW BELT)

SJO - DURING C-CHECK, UPPER WINDOW BELT DISBONDING FROM BS 887 TO BS 907 AND BETWEEN STRINGER 11L AND 13L. REPAIRED WINDOW BELT FROM BS 887 TO BS 907 AND BETWEEN STRINGER 10L AND 14L IAW SB 737-53-1078, SECTION III, PART III, PARAGRAPH C, FIG 3 AND FIG 6 DATED SEPT 15, 1994. (M)

Part: SKIN — DEBONDED (WINDOW BELT)

SJO - DURING C-CHECK, UPPER WINDOW BELT DISBONDING FROM BS 360 TO BS 380 AND BETWEEN STRINGER 11R AND 13R. REPAIRED WINDOW BELT FROM BS 360 TO BS 380 AND FROM STRINGER 10R TO 14R IAW SB 737-53-1078, SECTION III, PART III PARAGRAPH C, FIG 3 AND FIG 6 DATED SEPT 15, 1994. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, SIX SKIN CRACKS, AVERAGE LENGTH .25 INCH, AT BS 188, WL 214, TWO BS 188 WL 216, ONE AT BS 203, WL 216, ONE AT BS 211, WL 217 AND TWO AT BS 211 WL 218 ON RT SIDE OF AIRCRAFT. REPAIRED RIGHT SKIN CRACKS FROM BS 183 TO BS 244 AND FROM WL 202 TO WL 229 IAW SB 737-53-1111 AND BOEING FAX COO-SJO-00-0114H DATED 9/25/00. (M)

Part: FRAME — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, INNER FRAME CRACKED, LENGTH .375, AT BS 500B BETWEEN STRINGER 20R AND 22R. REPAIRED FRAME AT BS 500B FROM STRINGER 20R TO 26R IAW SRM 53-10-4 FIG 1. (M)

Part: FRAME — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, FRAME INNER FLANGE CRACKED, LENGTH .250 INCH, AT BS 500A BETWEEN STRINGERS 21R AND 22R. REPAIRED FRAME AT BS 500A BETWEEN STRINGERS 20R AND 26R IAW SRM 53-10-4 FIG 1. (M)

Part: FRAME — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, INNER FRAME CRACKED, .125 INCH LENGTH, AT BS 500B STRINGER 26R. REPAIRED FRAME AT BS 500B BETWEEN STRINGERS 26R AND 27R IAW SRM 51-40-3 FIG 1. (M)

Part: FRAME — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, FRAME INNER FLANGE CRACKED .450 INCH LONG AT BS 500 BETWEEN STRINGERS 21R AND 22R. REPAIRED FRAME AT BS 500 BETWEEN STRINGERS 20R AND 26R IAW SRM 53-10-4 FIG 1. (M)

Part: FRAME — CRACKED (FWD CARGO BAY)

SJO - DURING C-CHECK, FORWARD CARGO COMPARTMENT FRAME CRACKS AT BS 420 BETWEEN STRINGER 20L AND STRINGER 23L, THREE EACH 5 INCHES. REPAIRED FRAME AT BS 420 FROM STRINGER 19L TO STRINGER 26L IAW SRM 53-10-4 FIG 1. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, HFEC CRACK INDICATIONS 3 EACH (AVG. L = .025 INCH) ON LEFT SIDE 1 EACH BS 227 WL 221, 1 EACH BS 227 WL 226 AND 1 EACH BS 235 WL 222. REPAIRED SKIN FROM BS 224 TO BS 255 AND BETWEEN STRINGERS 10L AND 18L IAW SB 737-53-1111, SECTION III PAR II DATED APRIL 15, 1993 AND BOEING FAX COO-SJO-00-01146H DATED SEPTEMBER 25, 2000. (X)

Part: SKIN — DENTED (TE FLAP)

DURING Q CHECK FOUND THE LEFT HAND INBOARD MID-FLAP LEADING EDGE SKIN AT STA RSS 215 WITH DENT L=1.0 IN, W=2.0 IN, D=0.200 IN. REPAIRED LT INBOARD MID-FLAP LEADING EDGE SKIN AT STA RSS 215 DENT IAW BOEING SREM 57-50-4 FIG 3

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, HFEC SKIN CRACK INDICATION ON UPPER ROW OF RIVETS BETWEEN BS 939 AND BS 946 AT STRINGER 20L. REPAIRED SKIN FROM BS 923 TO BS 950 AND FROM STRINGER 19L TO 21L IAW SRM 53-30-3 FIG 13 DETAIL III. (M)

Part: ANGLE — CRACKED (LT WING SPAR)

SJO - DURING C-CHECK, FOUND LT WING FRONT SPAR VERTICAL ANGLE AT FSS 346 CRACKED (L = 1.5 INCHES). FABRICATED AND REPLACED ANGLE IAW SRM 51-10-00 PAGE 8. (X)

Part: SKIN — CRACKED (FUSELAGE)

DURING C-CHECK, HFEC SKIN CRACK INDICATION ON UPPER ROW OF RIVETS AT STRINGER 26R, BS 404. REPAIRED SKIN FROM BS 397 TO BS 412 AND BETWEEN STRINGERS 25L AND 27L IAW SRM 53-30-3 FIG 13 DETAIL II. (M)

Part: SKIN — CRACKED (FUSELAGE)

DURING C-CHECK, HFEC SKIN CRACK INDICATION, LENGTH 2.5 INCH, AT BS 448 STRINGER 10R. REPAIRED SKIN FROM BS 442 TO BS 453 AND BETWEEN STRINGERS 10R AND 11R IAW SRM 53-30-3 FIG 13 DETAIL III. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - DURING C-CHECK, LFEC SKIN CRACK INDICATION BETWEEN BS 386 AND BS 392 ON TOP ROW OF FASTENERS AT STRINGER 26R. REPAIRED SKIN FROM BS 386 TO BS 392 BETWEEN STRINGERS 25R AND 27R IAW SRM 53-30-3 FIG 13, DETAIL III. (M)

Part: SKIN — CRACKED (FUSELAGE)

SJO - FOUND DURING C-CHECK, HFEC SKIN CRACK INDICATION ON UPPER ROW OF FASTENERS AT BS 500 STRINGER 26L. REPAIRED SKIN FROM BS 492 TO BS 506 AND FROM STRINGER 25L TO 27L IAW SRM 53-30-3 FIG 13 DETAIL 11. (M)

Part: FITTING — GOUGED (VERTICAL STAB)

MCI - DURING COMPLIANCE OF VANGUARD EO NR 993753A43, FOUND THE LEFT OUTBOARD 1088 VERTICAL LUG FITTING UPPER OUTBOARD HOLE GOUGED, LEFT .392 INCH, WIDTH .156 INCH, DEPTH .030 INCH. REPAIRED THE LEFT OUTBOARD 1088 VERTICAL LUG FITTING UPPER OUTBOARD HOLE IAW BOEING MESSAGE NR VAG-MCI-00-00091H DATED 09-07-2000. (M)

Part: FITTING — GOUGED (VERTICAL STAB)

MCI - DURING COMPLIANCE OF VANGUARD EO NR 993753A43, FOUND THE LEFT INBOARD 1088 VERTICAL LUG FITTING LOWER INBOARD HOLE WITH STEEL BUSHING INSTALLED. REPAIRED THE LEFT INBOARD 1088 VERTICAL LUG FITTING LOWER INBOARD HOLE IAW BOEING MESSAGE NR VAG-MCI-00-00091H DATED 09-07-200. (M)

Part: SENSOR — OUT OF POSITION (NR 6 SLAT)

ORD - FLT 420 - DIVERTED ORD, NO EMERGENCY DECLARED, LANDING UNEVENTFUL. ON CLIMB-OUT, NR 6 SLAT LIGHT CAME ON ALONG WITH LEADING EDGE FLAP TRANSIT LIGHT. LIGHTS WENT OUT AFTER 30 SECONDS, THEN CAME BACK ON FOR A SHORT PERIOD OF TIME, THEN BACK OUT. NO FURTHER PROBLEMS ON CLIMB-OUT. REPOSITIONED AND CLEANED NR 6 LEADING EDGE SLAT PROXIMITY SENSOR AS PER MM 27-81-0 AND MM 27-88-11. OPERATIONAL CHECK NORMAL. (M)

Part: CIRCUIT BREAKER — TRIPPED (MLG)

FLT 562 - MDW - WHEN GEAR WAS SELECTED DOWN FOR APPROACH, GEAR INDICATION LIGHTS WERE INOPERATIVE. TOWER CONFIRMED GEAR DOWN ON GO AROUND. FOUND LANDING GEAR LIGHTS CIRCUIT BREAKER POPPED. RESET CIRCUIT BREAKER. INDICATION WORKED NORMALLY. LANDING WAS UNEVENTFUL. PERFORMED LANDING GEAR POSITION INDICATING SYSTEM TEST PER MM 32-61-0. SYSTEM FOUND TO OPERATE NORMALLY. NO FAULT FOUND. (M)

Part: FIRE LOOP — LOOSE (NR 1 ENGINE)

ORD - FLT 564 - NR 1 ENGINE FIRE WARNING SOUNDED TWICE FOR ONE SECOND EACH TIME DURING CRUISE FLIGHT AND DURING DESCENT. ENGINE SHUT DOWN AND SECURED EIGHT MINUTES BEFORE LANDING, OIL PRESSURE REMAINED ABOVE 10 PSI. NOTE: ORIGINAL FLIGHT DESTINATION WAS MDW. AFTER EINGINE SHUTDOWN, DIVERTED TO ORD, LANDING UNEVENTFUL. FOUND NR 1 ENGINE LOWER FIRE LOOP CONNECTOR LOOSE. TIGHTENED AND SECURED CONNECTOR. SYSTEM OPS CHECKS NORMAL PER MM 26-11-1. PERFORMED WINDMILL INSPECITON ON NR 1 ENGINE PER PWA MM 72-00-158D, SCREENS CHECK OK AND LEAK CHECKS OK. (X)

Part: FLOORBEAM — CORRODED (BS 259.5)

DURING C-CHECK, FLOORBEAM UPPER CORD CORRODED AT BS 259.5 BETWEEN LBL 15.0 INCHES AND RBL 16.0 INCHES. REPAIRED FLOORBEAM WEB AT BS 259.5 BETWEEN LBL 25 INCHES AND RBL 22 INCHES WL 208.1 IAW COOPESA EO COO-3-53-028-00 DATED 1-14-00. DOCUMENTED ON FAA FORM 8110-3. APPROVED AND SUBMITTED BY FAA DER. DESIGNATION NR DERT 71-0004-2-344, VAM-100 NR 679. (X)

Part: FLOORBEAM — CORRODED (BS 259.5)

DURING C-CHECK, FLOORBEAM AT BS 259.5 BETWEEN LBL 7.0 INCHES AND RBL 10.0 INCHES, FLOORBEAM WEB HAS CORROSION. DEFECT SIZE LENGTH - 17.0 INCHES. WIDTH - 2.0 INCHES. DEPTH - 0.050 INCH. REPAIRED FLOORBEAM WEB AT BS 259.5 BETWEEN LBL 8.75 AND RBL 13.875, IAW COOPESA EO COO-3-53-027-00 DATED 1-14-00. DOCUMENTED ON FAA FORM 8110-3. APPROVED AND SUBMITTED BY FAA DER DESIGNATION NR DERT 710167SW DATED 1-14-00. SEE COOPESA WO N1-0004-2-343, VAM-100NR 678. (X)

Part: SKIN — DELAMINATED (SPOILERS)

SJO - RIGHT WING FLIGHT SPOILER NR 3 DELAMINATED, DEFECT SIZE VARIOUS. REPAIRED NR 3 FLIGHT SPOILER PER COOPESA EO COO-CMP-3-57-033-00 DATED JANUARY 16, 2000. (M)

Part: SKIN — DAMAGED (MLG DOOR)

DURING C-CHECK, LEFT MAIN LANDING GEAR OUTER DOOR WITH MISSING SKIN MATERIAL. DEFECT SIZE: LENGTH - 5.0 INCHES, WIDTH - 0.25 INCH. REPAIRED LT MAIN LANDING GEAR OUTER DOOR SKIN PER COOPESA EO NR COO-3-52-024-00 DATED JAN 14, 2000 AND BOEING FAX COO-SJO-00.00054H DATED JAN 13, 2000. DOCUMENTED ON FAA FORM 8110.3. APPROVED AND SUBMITTED BY FAA DER, DESIGNATION NR DERY-635781-NM. SEE COOPESA WO N10004-5-60, VAM 100 NR 589. (X)

Part: FRAME — CRACKED (BS 360)

SJO - DURING C-CHECK, FOUND CRACK AT BW 360 BETWEEN STR 19LT AND STR 20LT. DEFECT SIZE: LENGTH - 2.0 INCHES. REPAIRED FUSELAGE FRAME SECTION AT BS 360 BETWEEN STR'S 19LT AND 23LT PER SB 737-53A1064 SECTION III, PART II, PAR A AND B, FIG 2 REV 6, DATED JUNE 29, 1989, AND VANGUARD AIRLINES EO 973753A044, REPAIR SECTION, PART 1, PAR 2, DRAWING 65C23267. SEE COOPESA WO N1-0004-1-55, VAM 100 NR 466 FOR TECHNICAL INFORMATION. (X)

Part: INTERCOSTAL — CRACKED (BS 194.5)

SJO - C-CHECK. INTERCOASTAL CRACKED AT S 194.5, BETWEEN STR 111RH AND STR 12RH. DEFECT SIZE: LENGTH - 4.0 INCHES. REPLACED FITTING AT BS 194.5 PER SRM 51-10-1, PAGE 5, 51-30-2. COOPESA WO N1-0004-2-309, VAM 100 NR 503. (X)

Part: SKIN — DELAMINATED (SPOILER)

SJO - C-CHECK. NR 3 SPOILER UPPER SURFACE DELAMINATED AT WBL 227. DEFECT SIZE: LENGTH - 52.0 INCHES WIDTH = 20.75 INCHES. REPAIRED SPOILER PER COOPESA EO COO-CMP-3-57-032-00 DATED JAN 16, 2000. DOCUMENTED ON FAA FORM 8110-3. APPROVED AND SUBMITTED BY FAA DER DESIGNATION DERT-710167-SW DATED 01-17-2000. COOPESA WO N10004-5-33, VAM 100 NR 471 AND 661 FOR TECHNICAL INFORMATION. (X)

Part: SKIN — DELAMINATED (SPOILER)

DURING C-CHECK, FOUND LT WING NR 2 SPOILER UPPER AND LOWER SURFACE DELAMINATED AND UPPER SURFACE OUTBOARD END CORNER HAS SKIN DAMAGED. DEFECT SIZE: LENGTH - 8.00 INCHES, WIDTH - 9.50 INCHES. REPAIRED LT WING NR 4 SPOILER UPPER SKIN PER COOPESA EO COO-CMP-357-034-00 DATED JAN 16, 2000. DOCUMENTED ON FAA FORM 8110-3, APPROVED AND SUBMITTED BY FAA, DESIGNATION DERT-710167-SW, DATED JAN 17, 2000. SEE COOPESA WO NR 5-73 AND VAM-100 NR 662 FOR TECHNICAL INFORMATION. (X)

Part: WEB — CRACKED (BS 227-259)

DURING C-CHECK, FOUND NOSE WHEEL WELL, UPPER FORWARD RIB WEB WITH CRACK. FABRICATED WEB IAW SRM 51-20-1. REMOVED AND REPLACED WEB AT BS 227.8 TO BS 259.5, BL 0 IAW SRM 51-10-1 PAGE 5 AND SRM 51-30-2. (M)

Part: SKIN — CRACKED (BS 178)

SJO - FUSELAGE SKIN DOUBLER CRACKED AT BS 178, WL 170, DEFECT SIZE LENGTH 1.5 INCH. REWORKED EXTERNAL DOUBLER AT BS 178 BETWEEN RBL 2.250 AND RBL 5 WL 170 PER COOPESA EO COO-3-53-023-00 DATED JAN 13, 2000 AND BOEING FAX COO-00-000-49H JAN 12, 2000. (M)

Part: SKIN — DENTED (BS 1064)

SJO - DURING C-CHECK, SKIN DENTED AT BS 1064 BETWEEN 24R AND 25R. REPAIRED SKIN FROM BS 1064 TO BS 1068 AND BETWEEN 24R AND 25R IAW 53-30-03 FIG 5. (M)

Part: CONNECTOR — CONTAMINATED (NR 1 ENGINE)

MSP - FLT 705 - DURING FLIGHT, THE NR 1 ENGINE OVERHEAT LIGHT ILLUMINATED, THE SAME LIGHT REMAINED EXTINGUISHED AT REDUCED THROTTLE SETTINGS. EMERGENCY WAS DECLARED AND AIRCRAFT LANDED WITH NO INCIDENT. CLEANED CANNON PLUG ON FIRE TEST UNIT AND FIRE PROTECTION BOX. ENGINE RUN PERFORMED AT 75 PERCENT N2, ALL INDICATIONS NORMAL PER MM CHAPTER 71. (M)

Part: FITTING — CRACKED (RT WING)

MCI - RUNNING FUEL LEAK AT RIGHT WING ROOT, LOWER SURFACE AT WING-TO-BODY AREA NEAR SUMP DRAIN. PRESSURE CHECKED. CLEANED AND SEALED LEAK AREA. LEAK NOW CLASSIFIED AS STAIN PER MM 28-11-0. FOUND TIE FITTING CRACKED IN RADIUS, BL 70.85. STRINGER S9R WING LOWER SURFACE. REPLACED RT WING LOWER TIE FITTING AND FEED-THROUGH TUBE, BL 70.85, STR S9 PER SRM 51-30-2 AND BAC DRAWING 65-45414. PART TC: 59,093. (X)

Part: RETRACT MECH — MALFUNCTIONED (NR 1 LE SLAT)

MCI - FLT 588 - NR 1 LEADING EDGE SLAT TRANSIT LIGHT ON. VISUALLY CONFIRMED INBOARD END OF SLAT NOT FULLY EXTENDED WITH SLATS IN MID EXTEND POSITION. SLAT EXTENDED NORMAL WITH SLATS SELECTED TO FULL EXTEND POSITION. LUBED NR 1 LEADING EDGE SLAT. OPS CHECKS GOOD PER MM 27-88-11. (M)

Part: PRSOV — MALFUNCTIONED (NR 1 ENGINE)

ATL - FLT 406 - NO EMERGENCY DECLARED, LANDING UNEVENTFUL. DESCENDING THROUGH 15,000 FEET, THROTTLES NEAR IDLE, A LOUD BOOM HEARD IN COCKPIT AND CABIN IN THE AIRCONDITIONING SYSTEM. THE LEFT DUCT OVERHEAT LIGHT AND MASTER CAUTION/OVERHEAD LIGHT CAME ON. QRH ITEMS ACCOMPLISHED. EXTINGUISHED OVERHEAT LIGHTS WITH RESET BUTTON. LOUD NOISE CONTINUED WITH LEFT PACK OFF, LEFT ENGINE BLEED OFF, AND ISOLATION VALVE CLOSED UNTIL AFTER LANDING AND SHUT DOWN OF NR 1 ENGINE. INSPECTED NR 1 ENGINE PNEUMATIC DUCTS, DUCTS IN LEFT WING AREA, LEFT AND RIGHT AIR CONDITIONING PACK AREAS, FORWARD CARGO AFT AREA, E/E AREA. FOUND NO SIGNS OF BLOWN DUCTS. RAN ENGINES PRESSURIZED AIRCRAFT, NO LEAKS FOUND. INSPECTED LEFT AIR CY

Part: WIRE — LOOSE (NR 1/NR 2 EPR)

PIT - FLT 701 - ON TAKEOFF ROLL, NR 2 ENGINE EPR DID NOT RESPOND WITH ENGINE RUN-UP. FOUND NR 1 ENGINE EPR AND LANDING GEAR WARNING CIRCUIT BREAKERS POPPED. RESET CIRCUIT BREAKERS AND NR 2 EPR CAME UP. FOUND NR 1 AND NR 2 EPR CIRCUIT BREAKERS REVERSED POSITION AND WIRE LOOSE. REPOSITIONED CIRCUIT BREAKERS PER WIRING DIAGRAM MANUAL 77-13-01. SECURED WIRE, OPERATIONAL CHECK NORMAL PER MM 77. (M)

Part: PSU — MALFUNCTIONED (ROW 18-19)

FLT 404 - ATL - DURING LANDING, SEVERAL PASSENGERS NOTED SPARKS EMITTING FROM PASSENGER SERVICE UNIT AT ROW 18-19 DEF (RT).

Part: BLEED CONTROL — FAILED (LEFT ENGINE)

MSP - FLT 416 - DURING THROTTLE ADVANCEMENT FOR TAKEOFF, HEARD LOUD NOIS FROM LEFT SIDE OF AIRCRAFT. TAKEOFF ABORTED (LESS THAN 60 KNOTS), RETURNED TO GATE. REPLACED LEFT ENGINE PRESSURE RATIO BLEED CONTROL REGULATOR PER MM 75-31-11, OPERATIONAL CHECK OK. (M)

Part: ROLLER — BROKEN (L1 DOOR)

MDW - FLT 560 - DURING CLIMB-OUT OF MCI, THE L-1 DOOR SEAL DID NOT SEAT PROPERLY ALLOWING LOUD WIND NOISE. AFTER SEVERAL MOMENTS THE SEAL DID SET CORRECTLY, PRESSURE WAS THEN NORMAL. FIVE MINUTES LATER, LOUD POP AT DOOR, NO PRESSURE PROBLEMS RESULTED FROM THIS NOISE. NOTIFIED MAINTENANCE CONTROL EN ROUTE TO MDW. FOUND AFT UPPER LATCH ROLLER ASSY BROKEN. REPLACED LATCH ROLLER ASSY PER MM 52-11-0. OPS CHECK NORMAL PER MM 52-11-0. (M)

Part: TORSION BAR — OUT OF ADJUST (TE FLAP)

MCI - FLT 586 - NO EMERGENCY DECLARED LANDING UNEVENTFUL AT DESTINATION. AIRCRAFT ROLLS RIGHT WHEN FLAPS ARE EXTENDED. RETORQUED TORSION BAR ON NR 1 SLAT PER MM 27-81-21 AND LUBRICATED TRACKS, OPS CHECKED OK. (M)

Part: BOLT — LOOSE (NR 4 SLAT)

MDW - FLT 418 - NO EMERGENCY DECLARED LANDING UNEVENTFUL. AT FLAPS 1 RECEIVED UNCOMMANDED ROLL. POST FLIGHT REVEALS LOOSE, LEADING EDGE SLAT. FOUND NR 4 SLAT, INBOARD AUX TRACK ADJUSTMENT BOLT LOOSE. REPLACED BUSHING AND TIGHTENED BOLT PER MM 27-81-21, SLAT OPS CHECK NORMAL PER MM 27-81-0. (M)

Part: ADC — FAILED (E/E BAY)

MCI - FLT 819 - AIR RETURN NO EMERGENCY DECLARED LANDING UNEVENTFUL. BOTH AIRSPEED INDS HAD FALSE INDICATIONS ON CLIMB-OUT, F/O HIGH, CAPT'S LOW, CAPTS AIRSPEED THEN WENT OT ZERO AND STAYED THERE. CAPT'S LOW, CAPT'S AIRSPEED THEN WENT OT ZERO AND SYATED THERE. CAPTAINS VSI UNRELIABLE IN FLIGHT. SHOWED 500 FT DESCENT IN LEVEL FLIGHT. READ 0 FPM ON FINAL APPROACH. F/O'S VSI SEEMED OK. REPLACED NR 1 CADC PER MM 34-12-11. OPS CHECK AND LEAK CHECK NORMAL. (M)

Part: FITTING — DAMAGED (WS 432)

SJO - INTERNAL FITTING FOUND OUT OF LIMITS AT RT WING FRONT SPAR SECTION AS FSS 432. REPLACED RIGHT WING FRONT SPAR FITTING AT FSS 432 SRM 51-10-1 PAGE 5. (M)

Part: SPAR — CORRODED (WS 430)

SJO - RIGHT WING FRONT SPAR UPPER CHORD CORRODED AT FSS 430. REPAIRED RIGHT WING FRONT SPAR UPPER CHORD BETWEEN FSS 401.95 AND FSS 460 PER COOPESA EO COO-3-57-597 DATED OCT 30, 1998 AND BOEING INSTRUCTION LIST OF DATA INCLUDED ON FAA FORM 8110-3. (M)

Part: FRAME — CRACKED (PAX DOOR)

SJO - FORWARD ENTRY DOOR LOWER AFT SECTION CRACKED, DEFECT SIZE LENGTH 1 INCH. REPAIRED FORWARD ENTRY DOOR LOWER AFT FRAME SECTION PER SRM 51-40-3 FIG 1 AND SRM 51-30-2. (M)

Part: SKIN — CORRODED (BS 967)

SJO - FUSELAGE SKIN SECTION CORRODED AT BS 967 BETWEEN STRINGER 26 LT AND STRINGER 26 RT. REPAIRED FUSELAGE SKIN SECTION FROM BS 962 TO BS 983, BETWEEN STRINGER 26 LT TO STRINGER 26 RT PER SRM 53-30-3 FIG 17. (M)

Part: FITTING — CRACKED (WS 525)

SJO - RIGHT WING SPAR FITTING CRACKED AT FSS 525, DEFECT SIZE LENGTH=1 INCH. REPLACED FRONT SPAR FITTING PER SRM 51-10-01 PAGES 5 AND SRM 51-30-2. (M)

Part: SPAR — WORN (WS 475)

SJO - RIGHT WING FRONT SPAR LOWER CHORD WORN AT WSL 475, DEFECT SIZE LENGTH 2.625 INCH, WIDTH .812 INCH DEPTH .055 INCH. REPAIRED FRONT SPAR LOWER CHORD AT WS 475 PER COOPESA EO C00-SJO-57-567-98 DATED OCT 15, 1998 AND BOEING FAX COO-SJO-98-0755RR DATED OCT 9, 1998. DOCUMENTED ON FAA FORM 8110-3. (M)

Part: FAIRING — DELAMINATED (RIGHT FUSELAGE)

SJO - RIGHT WING TO BODY FAIRING (RT A/C BAY DOOR) INNER DOOR SKIN AND SEAL DELAMINATED. REPAIRED RT WING TO BODY FAIRING PER COOPESA EO C00-3-53-588-98 DATED OCT 26, 1998. (M)

Part: FAIRING — DELAMINATED (LT FUSELAGE)

SJO - LEFT WING TO BODY FAIRING (LT A/C BAY DOOR) INNER SKIN DELAMINATED. REPAIRED LEFT WING TO BODY FAIRING PER COOPESA EO C00-3-53-587-98 DATED OCT 26, 1998. (M)

Part: SEAT TRACK — CORRODED (BS 360-400)

SJO - PAX CABIN SEAT TRACK CORRODED FROM BS 360 TO BS 400, RBL 45 INCHES. REPLACED SEAT TRACK SECTION FROM BS 360 TO BS 400, RBL 45 INCHES, WL 208.1 PER SRM 51-10-1 PAGE 5, 51-30-2, AND 53-10-5 FIG 2. (M)

Part: SEAT TRACK — CORRODED (BS 847-947)

SJO - PAX CABIN SEAT TRACK CORRODED FROM BS 847 TO BS 947, RBL 45 INCHES. REPLACED SEAT TRACK SECTION FROM BS 847 TO BS 947 RBL 45 INCHES PER SRM 51-10-1 PAGE 5, 51-30-2, AND 53-10-5 FIG 2. (M)

Part: SEAT TRACK — CORRODED (BS 727-767)

SJO - PAX SEAT TRACK SECTION CORRODED FROM BS 727B TO BS 767, LBL 45 INCHES. REPLACED SEAT TRACK SECTION FROM BS 727B TO BS 767, LBL 45 INCHES, WL 208.1 PER SRM 51-10-1 PAGE 5, 51-30-2 AND 53-10-5 FIG 2. (M)

Part: SKIN — DAMAGED (BS 1020-1035)

SJO - PROVISIONAL FUSELAGE SKIN REPAIR FROM BS 1020 TO BS 1035, BETWEEN STRINGER 22 LT AND STRINGER 24 RT NOT COMPLIANT WITH THE SRM. REPAIRED FUSELAGE SKIN SECTION FROM BS 1020 TO BS 1035, BETWEEN STRINGER 2 LT AND STRINGER 24 LT PER SRM 53-30-3 FIG 16. (M)

Part: SKIN — DAMAGED (BS 1036-1051)

SJO - PROVISIONAL FUSELAGE SKIN REPAIR FROM BS 1036 TO BS 1051, BETWEEN STRINGERS 20 RT AND 23 RT NOT IN COMPLIANCE WITH SRM. REPAIRED FUSELAGE SKIN SECTION FROM BS 1035 TO BS 1054, BETWEEN STRINGER 19 RT AND 23 RT PER SRM 53-30-3 FIG 7. (M)

Part: SKIN — DAMAGED (BS 1016)

SJO - PROVISIONAL FUSELAGE SKIN REPAIR AT BS 1016, BETWEEN STRINGER 12 LEFT AND STRINGER 15 LEFT. REPLACED FUSELAGE SKIN SECTION FROM BS 989 TO BS 1016, BETWEEN STRINGER 10 LEFT AND STRINGER 14 LT PER SRM 51-10-1 PAGE 5 AND SRM 51-30-2. REPAIRED FUSELAGE SKIN SECTION FROM BS 999 TO BS 1016, BETWEEN STRINGER 13 LEFT AND STRINGER 17 LEFT PER COOPESA EO COO-3-53-585-98 DATED OCT 22, 1998. (M)

Part: SKIN — DAMAGED (BS 901)

SJO - PROVISIONAL FUSELAGE SKIN REPAIR AT BS 901, BETWEEN STRINGER 24 LT AND STRINGER 26 LT PER COOPESA EO C00-3-53-591-98 DATED OCT 27, 1998 AND BOEING FAX C00-SJO-98-0830RR DATED OCT 26, 1998. DOCUMENTED ON FAA FORM 8110-3. (M)

Part: SKIN — DENTED (LT TE FOREFLAP)

SJO - LEFT WING OUTBOARD FOREFLAP WORN AND DENTED. DEFECT SIZE, VARIOUS. REPAIRED LEFT WING OUTBOARD FOREFLAP PER COOPESA EO COO-3-57-583-98 DATED OCT 21, 1998. REPAIRED LEADING EDGE PER SRM 57-50-4 FIG 1. (M)

Part: SKIN — DAMAGED (AILERON)

SJO - LEFT AILERON DELAMINATED AND WITH HAIL DAMAGE, DEFECT SIZE VARIOUS. REPAIRED LEFT AILERON PER COOPESA EO COO-3-57-565-98 DATED OCT 15, 1998. (M)

Part: SKIN — DAMAGED (NR 5 SLAT)

SJO - NR 5 SLAT DELAMINATED UPPER AND LOWER SKIN. REPAIRED NR 5 SLAT PER COOPESA EO COO-3-57-573-98 DATED OCT 17, 1998. (M)

Part: SKIN — DELAMINATED (TE FLAP)

SJO - UPPER SKIN DELAMINATED INBOARD MID FLAP TRAILING EDGE. REPLACED LEFT WING, INBOARD MID FLAP TRAILING EDGE UPPER SKIN. (M)

Part: SKIN — DISBONDED (BS 328-338)

SJO - FUSELAGE SKIN INTERNAL DOUBLER DISBONDED FROM BS 328 TO BS 338, BETWEEN STRINGER 4 LT AND STRINGER 6 LT. REPAIRED INTERNAL DOUBLER FROM BS 328 TO BS 338, BETWEEN STRINGER 4 LT AND STRINGER 6 LT PER SRM 53-30-03, FIG 17 DETAIL 1. (M)

Part: SKIN — DISBONDED (BS 286-303)

SJO - FUSELAGE SKIN INTERNAL DOUBLER DISBONDED FROM BS 286 TO BS 303, BETWEEN STRINGER 4RT AND STRINGER 5 RT. REPAIRED FUSELAGE INTERNAL DOUBLER FROM BS 286 TO BS 303 PER SRM 53-30-3, FIG 17, DETAIL 1. (M)

Part: SKIN — DISBONDED (BS 344-360)

SJO - FUSELAGE SKIN INTERNAL DOUBLER DISBONDED FROM BS 344 TO BS 360, BETWEEN STRINGER 6 RT AND STRINGER 7 RT. REPAIRED FUSELAGE SKIN INTERNAL DOUBLER FROM BS 344 TO BS 360, BETWEEN STRINGER 6 RT AND STRINGER 7 RT PER SRM 53-30-3, FIG 17, DETAIL 1. (M)

Part: FLOORBEAM — CORRODED (BS 344)

SJO - PAX CABIN FLOORBEAM CORRODED AT BS 344, BETWEEN BL 0 TO LBL 55. REPLACED FLOORBEAM UPPER FLANGE AT BS 344 BETWEEN LBL 67 INCH TO RBL 41 INCH PER SRM 53-10-9 FIG 5, AND SRM 51-10-1 PAGE 5. (M)

Part: FLOORBEAM — CORRODED (BS 947)

SJO - FLOORBEAM UPPER CHORD CORRODED AT BS 947, FROM RBL 45 INCHES TO RBL 53 INCHES. REPAIRED FLOORBEAM UPPER CHORD AT BS 947, FROM LBL 60 INCH TO RBL 60 INCH PER BOEING FAX COO-SJO-98-0764RR DATED OCT 12, 1998 AND COOPESA EO COO-3-53-569-78 DATED OCT 15, 1998. DOCUMENTED ON FAA FORM 8110-3, (M)

Part: SKIN — CRACKED (BS 286-292)

SJO - FORWARD SERVICE DOOR (R1) UPPER HINGE CUTOUT CRACKED, DEFECT SIZE, CANNOT DETERMINE. REPAIRED FUSELAGE SKIN FROM BS 286.5 TO BS 292.5, BETWEEN STRINGER 9 RT AND STRINGER 13 RT. (M)

Part: SKIN — CRACKED (BS 946-956)

SJO - AFT SERVICE DOORWAY, LOWER HINGE CUTOUT CRACKED AT FORWARD SECTION, DEFECT SIZE LENGTH .625 INCH. REPAIRED FUSELAGE SKIN SECTION FROM BS 946 TO BS 956, BETWEEN STRINGER 13 RT AND STRINGER 16 RT PER SRM 53-30-3 FIG 33. (M)

Part: FRAME — CRACKED (BS 927)

SJO - FUSELAGE FRAME CRACKED AT BS 927, STRINGER 2 RT, DEFECT SIZE, LENGTH=.500 INCH. REPAIRED FRAME SECTION BS 927, BETWEEN STRINGER 2RT AND STRINGER 3 RT PER SRM 53-10-04 FIG 10. (M)

Part: FLOORBEAM — CORRODED (BS 360)

SJO - FLOORBEAM UPPER AND LOWER CHORD CORRODED AT BS 360, RBL 53. REPAIRED FLOORBEAM UPPER CHORD AT BS 360, BETWEEN RBL 47 INCH AND RBL 60 INCH PER SRM 53-10-9 FIG 7. REMOVED CORROSION AT LOWER CHORD AT BS 360, RBL 53 INCH AND FOUND WITHIN LIMITS PER SRM 51-10-6, SRM 53-10-01 FIG 1 AND SRM 51-10-2. (M)

Part: FLOORBEAM — CRACKED (BS 663-673)

SJO - FLOORBEAM CRACKED IN MULTIPLE PLACES FROM BS 663 AND BS 673, LBL 24 INCHES, AVERAGE DEFECT SIZE, LENGTH .312 INCH. REPAIRED FLOORBEAM UPPER CHORD FROM BS 660 AND BS 681, LBL 24.82. (M)

Part: SKIN — DISBONDED (BS 462-464)

SJO - FUSELAGE SKIN INTERNAL DOUBLER DISBONDED FROM BS 462 TO BS 464, BETWEEN STRINGER 13 LT AND STRINGER 14 LT. REPAIRED FUSELAGE SKIN INTERNAL DOUBLER FROM BS 400 TO BS 500, BETWEEN STRINGER 10 LT AND STRINGER 14 LT PER BOEING SERVICE BULLETIN 737-53-1048, REV 4 DATED SEPT 15, 1994, SEC 3 PART 3, FIG 3, DETAILS 2 AND DETAIL 3. (M)

Part: SEAT TRACK — CORRODED (BS 344-380)

SJO - PAX CABIN SEAT TRACK AND ANGLE CORRODED FROM BS 344 TO BS 380, LBL 46 INCHES AND LBL 63 INCHES. REPLACED SEAT TRACK SECTION BETWEEN BS 344 AND BS 380, LBL 46 INCHES PER SRM 53-10-5 FIG 2, 51-10-1 PAGE 5, AND 51-30-2. (M)

Part: RIB — CRACKED (WS 135)

SJO - RIGHT WING NR 3 FUEL TANK RIB CRACKED IN AFT SECTION BETWEEN REAR SPAR AND STRINGER 2, WBL 135.5 DEFECT SIZE, LENGTH 1 INCH. REPAIRED RIGHT WING RIB LOWER CHORD AT WBL 135.5 BETWEEN STRINGER 2 AND STRINGER 3 PER BOEING SERVICE BULLETIN 737-57-1186 DATED APRIL 13, SECTION 3 PART 3, FIG 3. (M)

Part: SPLICE — CRACKED (BS 663)

SJO - INTERIOR FUSELAGE SPLICE CRACKED AT BS 663.75, STRINGER 6 LT, DEFECT SIZE LENGTH .25O INCH. REPLACED FUSELAGE SPLICE FROM BS 657 TO BS 669, STRINGER 6 LEFT PER SRM 51-10-1 PAGE 5 AND SRM 51-30-2. (M)

Part: SEAT TRACK — CORRODED (BS 344-420)

SJO - PASSENGER CABIN SEAT TRACK CORRODED FROM BS 344 TO BS 420, LBL 25, WL 208.1. REPLACED SEAT TRACK SECTION FROM BS 344 TO BS 380, LBL 25 INCHES PER SRM 51-10-1 PAGE 5, 51-10-2, 53-10-5 FIG 2. (M)

Part: SKIN — CORRODED (BS 244-259)

SJO - FUSELAGE SKIN CORRODED AND DISBONDED FROM BS 244 TO BS 259, STRINGER 25LT, WL 154, LBL 19. REPAIRED FUSELAGE SKIN FROM BS 235.8 TO BS 259.5, BETWEEN STRINGER 24 LT AND STRINGER 26LT PER COOPESA EO COO-3-53-577-98 DATED OCT 19, 1998 AND BOEING FAX COO-SJO-98-0782RR DATED OCT 19, 1998. DOCUMENTED ON FAA FORM 8110-3. (M)

Part: STRINGER — CRACKED (BS 685)

SJO - STRINGER 5 RT CRACKED AT BS 685, DEFECT SIZE .375 INCH LENGTH. FUSELAGE STRINGER 5 RT REPAIRED BETWEEN BS 679 TO BS 691 PER SRM 53-10-3, FIG 4. (M)

Part: ANGLE — CORRODED (BS 344-380)

SJO - PAX CABIN SEAT TRACK AND ANGLE CORRODED FROM BS 344 TO BS 380, LBL 46 INCHES AND LBL 63 INCHES. REPLACED SEAT TRACK SECTION BETWEEN BS 344 AND BS 380, LBL 46 INCHES PER SRM 53-10-5 FIG 2, 51-10-1 PAGE 5, AND 51-30-2. (M)

Part: SPLICE — CRACKED (BS 663)

SJO - INTERIOR FUSELAGE SPLICE 5-7R CRACKED AT BS 663.75, DEFECT SIZE LENGTH .25 INCH. REPLACED FUSELAGE SPLICES FROM BS 657 AND BS 669, BETWEEN STRINGER 6 LT AND STRINGER 7 LT PER SRM 51-10-1 PAGE 5 AND SRM 51-30-2. (M)

Part: RIB — CRACKED (WS 135)

SJO - LEFT WING NR 1 FUEL TANK RIB CRACKED AT WBL 135.5 IN AFT SECTION, BETWEEN REAR SPAR AND STRINGER 16. REPAIRED LEFT WING LOWER CHORD AT WBL 135.5, BETWEEN STRINGER 2 AND STRINGER 3 PER BOEING SB 737-57-1186 DATED APRIL 13, 1989 SECTION 3, PART 3, FIG 3. (M)

Part: BEAM — CRACKED (CARGO DOOR)

SJO - C1 DOOR BEAM NR 5 CRACKED, DEFECT SIZE=.500 INCH. REPAIRED C1 DOOR NR 5 BEAM, PER SRM 51-40-3, FIG 1. (M)

Part: SKIN — WORN (WS 490-505)

SJO - RIGHT WING OUTBOARD FORE FLAP LEADING EDGE SKIN WORN. REPAIRED RIGHT WING FORE FLAP LEADING EDGE SKIN FROM WSL 490 TO WSL 505, PER SRM 57-50-4 FIG 1. (M)

Part: SKIN — WORN (WS 493-505)

SJO - RIGHT WING OUTBOARD FOREFLAP LEADING EDGE SECTION WORN. REPAIRED RIGHT WING OUTBOARD FOREFLAP LEADING EDGE SECTION FROM WS 493 TO WS 505 PER SRM 57-50-4 FIG 1. (M)

Part: SKIN — LIGHTNING STRIKE (BS 310-314)

SJO - LIGHTING STRIKE DETECTED IN FUSELAGE SKIN SECTION AT BS 312, STRINGER 3 LEFT, DEFECT SIZE .125 INCH LENGTH. REPAIRED FUSELAGE SKIN SECTION BETWEEN BS 310 AND BS 314 AT STRINGER 3 LEFT PER SRM 53-30-03, FIG 5. (M)

Part: FRAME — DENTED (BS 500)

SJO - FORWARD CARGO COMPARTMENT FRAME DENTED AT BS 500A, BETWEEN STRINGER 23 RT AND STRINGER 24 RT. REPAIRED FORWARD CARGO COMPARTMENT FRAME, UPPER FLANGE AT BS 500A, BETWEEN STRINGER 23 RT AND STRINGER 24 RT PER SRM 51-40-3, FIG 1, PAGE 5. (M)

Part: FITTING — WORN (PAX DOOR)

SJO - L1 ENTRY DOOR LOWER STOP FITTING WORN. REPLACED STOP FITTING PER SRM 51-10-01 PAGE 5 AND SRM 51-30-2. (M)

Part: SKIN — DAMAGED (BS 1104)

SJO - FUSELAGE SKIN WITH MISSING MATERIAL AT BS 1104, WL 223, RBL 23, DEFECT SIZE = .75 INCH. REPAIRED FUSELAGE SKIN BETWEEN BS 1095 AND BS 1108, WL 217 TO WL 223, RBL 23 INCH PER SRM 53-30-03 FIG 3. (M)

Part: STRINGER — CRACKED (BS 920-933)

SJO - STRINGER 25 LT CRACKED AT BS 927, DEFECT SIZE .375 INCH. REPAIRED FUSELAGE STRINGER SECTION BETWEEN BS 920 AND BS 933 PER SRM 53-10-03 FIG 1 SHEET 6. (M)

Part: STRINGER — CORRODED (BS 259-294)

SJO - STRINGER 23RT CORRODED BETWEEN BS 259.5 TO BS 294.5, DEFECT SIZE 35 INCHES IN LENGTH. REPAIRED FUSELAGE STRINGER SECTION BETWEEN BS 259 AND BS 313 PER SRM 53-10-03 FIG 1 SHEET 7. (M)

Part: SKIN — DAMAGED (BS 203)

SJO - HOLE FOUND IN FUSELAGE OUTER SKIN SECTION AT BS 203, RBL 7 INCH AND WL 153 INCH, DEFECT SIZE LENGTH .75 INCH WIDTH .437 INCH. REPAIRED FUSELAGE SKIN SECTION FROM BS 192.5 TO BS 203, BETWEEN BL 0 AND RBL 17 INCH, WL 153 PER SRM 53-30-3 FIG 6. (M)

Part: FITTING — WORN (PAX DOOR)

SJO - FORWARD ENTRY DOOR AFT LOWER STOP FITTING WORN. FORWARD ENTRY DOOR LOWER AFT STOP FITTING REPLACED PER SRM 51-10-1 PAGE 5, 51-30-2. (M)

Part: SKIN — DISBONDED (BS 259-360)

SJO - FUSELAGE SKIN DISBONDED FROM BS 259 TO BS 360, STRINGER 24 RT. REPLACED FUSELAGE SKIN SECTION FROM BS 259 TO BS 360, BETWEEN STRINGER 24 RT AND BL 0 PER SRM 51-10-1 PAGE 5, SRM 51-30-2 PAGE 1. (M)

Part: SKIN — DAMAGED (BS 178)

SJO - FUSELAGE SKIN MISSING MATERIAL AT BS 178, BETWEEN BL 0 TO RBL 6 INCH, WL 231. REPLACED FUSELAGE SKIN DOUBLER FROM BS 178 AND BS 188, FROM RBL 9 INCH TO LBL 9 INCH PER BOEING SERVICE BULLETIN 737-53-1059 REV 1 DATED MAY 17, 1990, SECTION 3. (M)

Part: BEAM — WORN (WS 222)

SJO - RIGHT WING TRUNNION SUPPORT BEAM WORN AT RSS 222. REPAIRED RIGHT WING MAIN LANDING GEAR BEAM UPPER FORWARD FLANGE SECTION PER BOEING FAX COO-SJO-98-0761RR DATED OCT 12, 1998. DOCUMENTED ON FAA FORM 8110-3. (M)

Part: BEAM — CRACKED (BS 727)

SJO - VERTICAL BEAM CRACKED IN AFT CARGO COMPARTMENT AT BS 727, LBL 18 INCHES, WL 150. DEFECT SIZE LENGTH 1 INCH. REPAIRED FUSELAGE BULKHEAD VERTICAL BEAM SECTION AT BS 727, LBL 18, WL 150 PER SRM 51-40-4 FIG 2. (M)

Part: STIFFENER — WORN (WS 155)

SJO - RIGHT WING REAR STIFFENER WORN AT RSS 155. REPLACED RIGHT WING REAR SPAR STIFFENER AT RSS 155 PER SRM 51-10-1 PAGE 5, AND SRM 51-30-2. (M)

Part: SKIN — DENTED (CARGO DOOR)

SJO - C1 DOOR SKIN DENTED, SCRATCHES AND PROVISIONAL REPAIRS, DEFECT SIZE AVERAGE .200 INCH. REPLACED C1 DOOR SKIN PER SRM 52-30-2 FIG 3. (M)

Part: SKIN — CORRODED (BS 815)

SJO - FUSELAGE SKIN SECTION CORRODED AT BS 815, STRINGER 20 LT. REPAIRED FUSELAGE LAP JOINT SKIN SECTION BETWEEN BS 809 AND BS 854, BETWEEN STRINGERS 19 LT AND 21 LT DUE TO CORROSION PER SRM 53-30-3 FIG 15. (M)

Part: SKIN — CANNED (BS 345-360)

SJO - FUSELAGE SKIN OIL CANNED FROM BS 345 TO BS 360, BETWEEN STRINGER 16 RT AND STRINGER 19 RT. REPAIRED FUSELAGE SKIN SECTION FROM BS 311 TO BS 360, BETWEEN STRINGER 15 RT AND STRINGER 19 RT PER COOPESA EO COO-3-53-570-98 DATED OCT 16, 1998 AND BOEING FAX COO-SJO-98-0773RR DATED OCT 14, 1998. DOCUMENTED ON FAA FORM 8110-2. (M)

Part: DOOR FRAME — DENTED (BS 500)

SJO - C1 DOOR FRAME DENTED AT BS 500B, STRINGER 25 RT, DEFECT SIZE LENGTH 1 INCH WIDTH .135 INCH. REPAIRED C1 DOOR FRAME AT BS 500B, BETWEEN STRINGER 22 RT AND STRINGER 25 RT PER SRM 51-40-3 FIG 1 PAGE 5. (M)

Part: FITTING — CRACKED (BS 685)

SJO - BS 685 RT FRAME FITTING CRACKED. REPLACED FUSELAGE FRAME FITTING AT BS 685 RT FROM WL 186 TO WL 255 PER BOEING FAX COO-SJO-98-0632RR DATED SEPT 16, 1998. (M)

Part: SKIN — CORRODED (BS 259-360)

SJO - FUSELAGE SKIN CORRODED FROM BS 259.5 TO BS 360, BETWEEN STRINGER 19 RT AND STRINGER 24 RT. REPLACED FUSELAGE SKIN SECTION FROM BS 259.5 AND BS 360, BETWEEN STRINGER 19 RT AND STRINGER 24 RT PER SRM 51-10-1 PAGE 5 AND SRM 51-30-2. (M)

Part: SKIN — CORRODED (BS 854-881)

SJO - EXTERNAL FUSELAGE SKIN WITH MATERIAL LOSS MORE THAN 10 PERCENT IN SEVERAL PLACES DUE TO CORROSION AT STRINGER 20L FROM BS 767 TO BS 887. REMOVED CORROSION FROM FUSELAGE SKIN FROM BS 747 TO BS 832 AND BS 854 TO BS 881 AT STRINGER 20L IN REFERENCE TO SRM 51-10-6 PAGE 12, WITH IN LIMITS REFERENCE SRM 53-30-1 FIG 1, DETAIL 2 ORIGINAL .036, REMAINING .034. REPAIRED FUSELAGE SKIN BETWEEN BS 832 AND BS 854 AT STRINGER 20L IN REFERENCE TO SRM 53-30-3 FIG 16. (M)

Part: SKIN — CRACKED (BS 188)

SJO - UPPER FUSELAGE BS 188, DOUBLER BELOW LEFT WINDSHIELD CENTER POST CRACKED. REPAIRED IAW BOEING S/B 737-53-1059. (M)

Part: SKIN — CRACKED (BS 727)

SJO - CRACKED SKIN AROUND FASTENER, EXTERNAL FUSELAGE BS 727A BETWEEN STRINGER 14R AND 15R. REPAIRED FUSELAGE SKIN CRACK AT BS 727A BETWEEN STRINGER 14R AND 15R IN REFERENCE TO SRM 53-30-3 FIGURE 17. (M)

Part: SKIN — CRACKED (BS 727)

SJO - REPAIR INTERNAL DOUBLER AT BS 727A STRINGER 16R. REPAIRED FUSELAGE SKIN DUE TO CRACK FROM BS 727 PLUS 11 INCHES TO BS 727 PLUS 4 INCHES, BETWEEN STRINGERS 15R AND 19R IN REFERENCE TO SRM 53-30-3 FIG 17 DETAIL 5. (M)

Part: ANGLE — CORRODED (NR 2 GALLEY)

SJO - PASSENGER CABIN FORWARD NR 2 GALLEY FLOOR ANGLE WITH CORROSION. REPLACED ANGLE IN REFERENCE TO SRM 51-10-1 PAGE 5. (M)

Part: SKIN — CRACKED (BS 312-318)

SJO - REPAIR L1 LOWER DOUBLER, FORWARD LOWER CORNER. REPAIRED FORWARD ENTRY DOOR EXTERNAL SKIN CRACK AT FORWARD LOWER CORNER BETWEEN BS 312 AND BS 318 FROM WL 212 TO WL 218 IN REFERENCE TO SRM 52-00-3 FIG 6. (M)

Part: WIRE — BROKEN (CABIN)

MCI - FLT 303 - EMERGENCY EXIT LIGHTS STAY ON WITH SWITCH IN ARM POSITION. REPAIRED BROKEN WIRE ON EMERGENCY EXIT SWITCH IN AFT GALLEY, OPS CHECK NORMAL. (M)

Part: MECHANISM — OUT OF ADJUST (NR 1 LE SLAT)

MCI - FLT 703 - NR 1 LEADING EDGE SLAT NOT EXTENDED WITH FLAPS AT 1 DEGREE. ADJUSTED NR 1 SLAT MID EXTEND DETENT ARMS PER MM 27-81-21. LEADING EDGE SLATS CHECK NORMAL PER MM 27-81-0. (M)

Part: COVER — CRACKED (NR 1 ENGINE)

FLT 804 - MDW - NO EMERGENCY DECLARED LANDING NORMAL. GOT HAZY VAPOR IN CABIN DURING FLIGHT. FOUND NR 1 BEARING ACCESSORY COVER CRACKED ON NR 1 ENGINE, REPLACED COVER PER PWA M/M 72-23. PERFORMED ENGINE RUN NO LEAKS OR HAZE NOTED. (M)

Part: CHECK VALVE — FAILED (RT CENTER TANK)

FLT 119 - MCI - NO EMERGENCY DECLARED LANDING NORMAL. WITH CENTER FUEL TANK BOOST PUMPS ON, RIGHT MAIN TANK CONTINUES TO FEED ON CLIMB-OUT DURING CRUISE, CENTER TANK TAKES ON FUEL WITH CENTER TANK BOOST PUMPS OFF. REPLACED RIGHT CENTER TANK BOOST PUMP CHECK VALVE PER MM 28-22-71. OPS CHECK OK, INSPECTED CENTER TANK FOR FUEL MIGRATION, NO DISCREPANCY NOTED. (M)

Part: LIGHT — INOPERATIVE (CABIN)

ATL - DISCREPANCY FOUND DURING SCHEDULED MAINTENANCE CHECK, EMERGENCY TRACK LIGHTING INOP, SEAT ROW 11 AND AFT. REPAIRED WIRING AT ROW 18 AND AFT BULKHEAD. REPLACED FUSES IN FWD AND AFT BATTERY PACKS. (M)

Part: SKIN — DENTED (BS 397)

SJO - DURING C-CHECK, UPPER FUSELAGE DENTED SKIN SECTION OUT OF LIMITS AT STATION 397, BETWEEN STRINGERS 2 AND 3 LEFT. REPAIRED DAMAGED SECTION PER SRM 53-30-3, FIG 7. (M)

Part: FRAME — CRACKED (BS 1040)

SJO - DURING C-CHECK, FOUND TAIL COMPARTMENT STATION 1040, STRINGER 8R, FRAME HAS CRACKS. REPAIRED FRAME AT STATION 1040, BETWEEN STRINGE 8 AND 10 RT, PER SRM 53-10-4, FIG 4. (M)

Part: SKIN — DELAMINATED (RUDDER)

SJO - DURING C-CHECK, FOUND RUDDER UPPER AFT TRAILING EDGE DELAMINATED. REPAIRED PER SRM 51-40-6, FIG 2, BALANCE OK PER SRM 51-80-1, POINT 2, FIG 8. (M)

Part: SKIN — DENTED (BS 890)

SJO - DURING C-CHECK, FOUND UPPER FUSELAGE DENTED SKIN SECTION OUT OF LIMITS AT BS 890 BELOW STRINGER 21R. REPAIRED DAMAGED SECTION IAW SRM 53-30-3 FIG 5. (M)

Part: SKIN — DENTED (BS 434)

SJO - DURING C-CHECK ITEM, UPPER FUSELAGE, DENTED SKIN SECTION OUT OF LIMITS AT BS 434 BETWEEN STRINGERS 1 AND 2L. REPAIRED DAMAGED SECTION IAW SRM 53-30-3 FIG 5. (M)

Part: RIB — CRACKED (WS 695)

SJO - DURING C-CHECK, FOUND RT W/W AT STATION 695, W/L 196, RIB WITH OUTBOARD CHORD CRACKED. REPAIRED OUTBOARD CHORD PER SRM 51-40-3. FIG1. (M)

Part: SKIN — DELAMINATED (RT AILERON)

SJO - DURING C-CHECK, RT AILERON UPPER AND LOWER SURFACES DELAMINATED AT SEVERAL PLACES. REPAIRED PER SRM 51-40-6, FIG 11. AILERON BALANCED PER SRM 51-80-1. AILERON REMOVED AND INSTALLED PER MM 27-11-11. (M)

Part: PANELS — MISSING (NR 2 ENGINE)

PIT - FLT 424 - DURING POST FLIGHT WALKAROUND INSPECTION, 2 AFT COWLING PANELS WERE NOTED MISSING ON NR 2 ENGINE. REPLACED MISSING COWLING PANELS. SECURED LATCHES. NO OTHER DEFECTS NOTED. A/C OK FOR SERVICE. COWL PANELS DEPARTED A/C DURING T/O ROLL AT MDW. MISSING COWL PANELS WERE LOCATED ON RUNWAY AT MDW. (M)

Part: PANELS — MISSING (NR 2 ENGINE)

PIT - FLT 424 - DURING POST FLIGHT WALKAROUND INSPECTION, 2 AFT COWLING PANELS WERE NOTED MISSING ON NR 2 ENGINE. REPLACED MISSING COWLING PANELS. SECURED LATCHES. NO OTHER DEFECTS NOTED. A/C OK FOR SERVICE. COWL PANELS DEPARTED A/C DURING T/O ROLL AT MDW. MISSING COWL PANELS WERE LOCATED ON RUNWAY AT MDW. (M)

Part: PACK — FAILED (RIGHT)

MSP - FLT 707 - RETURNED TO GATE, NO EMERGENCY DECLARED. AFTER STARTING NR 1 ENGINE AND TURNING THE RIGHT PACK ON, THE MAIN CABIN FILLED UP WITH AN ODORLESS HAZE. DEFERRED RIGHT A/C PACK PER MEL 21-1. DISCONNECTED RT PACK CANNON PLUG, D492, AND SLOWED. RIGHT PACK DEACTIVATED, CLOSED RIGHT PACK AIRCONDITIONING BAY DOOR. (M)

Part: BUSHING — LEAKING (NR 2 ENGINE)

DEN - FLT 327 - AIR RETURN, NR 2 ENGINE INFLIGHT SHUT DOWN. EMERGENCY DECLARED, RETURNED TO DENVER. LANDING UNEVENTFUL. NR 2 ENGINE LOW PRESSURE LIGHT CAME ON AND OIL PRESSURE GAUGE DROPPED TO 20 PSI. OIL QUANTITY DROPPED TO ZERO. WINDMILLING INSPECTION REQUIRED. REPLACED LP6 BUSHING ON NR 2 ENGINE GEARBOX. RAN ENGINE, NO LEAKS. REF: P & W OHM REPAIR NR 39/UAL MM 72-61-18. INSPECTED OIL FILTER, OIL SAMPLE SENT TO Q/A MCI. CHIP DETECTOR, OIL STRAINER CHECKED OK. RUN-UP OK. NO DEFECTS NOTED. REF: MM 72-00 PAGE 518D, ITEM 4. (X)