N958DL

Part: FUSE — BLOWN (BATTERY PACK) · airframe 74,337 hrs · 55,391 cycles

EMERGENCY LIGHTS AT ROWS 24-30 ARE INOPERATIVE. MAINTENANCE FOUND A FUSE ON BATTERY PACK B5-212 TO BE BAD. THE BAD FUSE WAS REPLACED AND THE LIGHTS NOW OPERATE NORMALLY REF AMM 33-50.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 74,109 hrs · 55,196 cycles

WHILE DES FROM FL360 NOTICED ACRID SMOKE SMELL IN THE COCKPIT. FLIGHT ATTENDANT THEN HAD SMOKE IN THE CABIN THAT STARTED NEAR ROW 26 AND STARTED AFTER SET OFF BOTH SMOKE ALARMS IN THE TWO AFT LAVS NORMAL CABIN PX + ENG INDICATIONS. SMOKE DISSIPATED AFTER 10 MIN. PERFORMED ODI PREVENTION PER WORKCARD 2120-2367. NO TROUBLE NOTED. CHECKED SADDLE DUCTS AND BOROSCOPED BOTH ENGINES, SCOPED ACM DUCTING, PULLED FWD FLT ATT SEAT AND INSPECTED ALL WIRING AND RELAYS, PULLED DOWN COCKPIT OVERHEAD PANELS AND INSPECTED, INSPECTED WIRING UNDER PANELS IN FWD GALLEY AND UNDER AFT OVERHEAD PANELS BETWEEN AFT LAVS, INSPECTED ALL 3 LAVS, INSP RECIRC FAN, EQUIP COOLING FAN, AND RADIO RACK, NTF.

Part: FAN — ODOR (RECIRCULATION) · airframe 73,847 hrs · 54,963 cycles

AFTER TAKEOFF, FROM WHEELS UP TILL 2 MINUTES, FA REPORTED AN ODOR, SHE DESCRIBED AS ELECTRICAL. 2 MINUTES LATER THE ODOR WENT AWAY AND NEVER REOCCURRED. DURING TROUBLESHOOTING IAW AMDS CARD 2120-2367, FOUND THE RECIRCULATION FAN INOPERATIVE. REPLACED THE FAN. NO ODOR PRESENT.

Part: PANEL — DAMAGED (RT SPOILER) · airframe 73,789 hrs · 54,917 cycles

RT INBOARD FLIGHT SPOILER DAMAGED. REMOVED AND REPLACED RT INBOARD SPOILER PANEL REF WORKCARD 2700-4727.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,789 hrs · 54,917 cycles

FUSELAGE SKIN FS 1322 L-20L - L-22L CORROSION. CORROSION WAS REMOVED AND REPAIRED PER ER/A 524660-14.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,789 hrs · 54,917 cycles

CORROSION ON SKIN AND PAN AT AFT LAV SERVICE PANEL LOWER QUADRANT. COMPLIED WITH ERA 569995-14 REV O.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 73,789 hrs · 54,917 cycles

REPAIR OF CORROSION LOCATED AT THE AFT LAV SERVICE PANEL CUTOUT. FS 1307 TO FS 1322, L-21L AND L-22L.

Part: VANE — GOUGED (TE FLAP) · airframe 73,789 hrs · 54,917 cycles

LT WING LE OF FLAP VANE GOUGED AFT OF CENTER HINGE POINT OB FLAP- REF NRC 189. FLAP VANE REPLACED ON NRC 189.

Part: BATTERY — DISCHARGED (CABIN) · airframe 73,719 hrs · 54,860 cycles

TAIL CAT WALK CEILING LIGHTS INOP. REMOVED AND REPLACED 'D' CELL BATTERIES TWO IN AFT LAV RIGHT. OPERATIONAL CHECK OK IAW AMM 33-50.

Part: SLIDE — LOW PRESSURE (L2 DOOR) · airframe 72,818 hrs · 54,148 cycles

L2 DOOR SLIDE PRESSURE LOW. REPL L2 DOOR SLIDE PER WORK CARD 2561-4002.

Part: FRAME — CRACKED (MLG WW) · airframe 72,287 hrs · 53,720 cycles

LT AND RT WHEEL WELL FWD FRAMES CRACKED. STOP DRILLED RT AND LT WHEEL WELL FWD FRAMES IAW ERA 536531-14, REV ORIG. OK FOR SERVICE.

Part: FITTING — BROKEN (ACTUATOR ATTACH) · airframe 71,344 hrs · 52,930 cycles

CREW REPORTED A RED LT MLG UNSAFE INDICATION WITH ASSOCIATED AMBER GEAR DOOR OPEN LIGHT AND AUTO-SPOILER FAIL EOAP MESSAGE AFTER GEAR RETRACTION. GEAR WAS EXTENDED AND CREW RECEIVED 3 GREEN DOWN AND LOCKED INDICATIONS WITH GEAR DOOR LIGHT EXTINGUISHED AND RETURNED TO DEPARTURE. MAINTENANCE FOUND THE LOWER LINK ASSEMBLY FOR THE MLG RETRACT ACTUATOR LOWER ATTACH POINT BROKEN. THE UPPER AND LOWER LINK ASSEMBLIES WERE REMOVED AND REPLACED AND A GEAR SWING ACCOMPLISHED.

Part: UNKNOWN — ODOR (CABIN) · airframe 71,095 hrs · 52,748 cycles

FLIGHT ATTENDANT IN REAR OF AIRCRAFT REPORT THAT DURING TAXI INTO THE GATE THEY OBSERVED A VERY INTENSE ODOR DESCRIBED AS POPCORN BURNED IN A MICROWAVE OVEN. INBOUND PILOTS REPORTED THAT THEY SHUTDOWN THE RIGHT ENGINE. DURING TAXI IN AND STARTED THE APU BEFORE ARRIVING AT THE GATE. THE ODOR BECAME VERY INTENSE AS THE AIRCRAFT PARKED AT THE GATE. THE LEFT ENGINE AND APU WERE RUNNING PROVIDING BLEED AIR FOR AIR CONDITIONING. ONCE THE LEFT ENGINE WAS SHUT DOWN THE ODOR DISAPATED. THE APU CONTINUED SUPPLYING BLEED AIR FOR 10 MINUTES WITH NO ODOR PRESENT. PERFORMED PNEUMATIC DIST AMDS WORKCARD 2120-2367 AND AMDS WORKCARD 7100-2619. NO SMOKE OR ODOR NOTED. C/W ODI PREVENTION PROGRAM. MC NOTIFIED. A/C OK FOR SVC. (LP9601133)

Part: LINE — LEAKING (HYD SYSTEM) · airframe 70,960 hrs · 52,642 cycles

ON APPROACH, LT HYD PRESSURE LOW CAUTION LIGHT, HYD PRESSURE & QTY BOTH INDICATED 0. LEAK COMING FROM CHAFED LEFT WING NR 4 FLAP ACTUATOR UP LINE. REPLACED THE HYD LINE AND SERVICED SYSTEM. CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,753 hrs · 52,493 cycles

EMERGENCY LIGHTS IN CEILING FIRST CLASS SECTION INOPERATIVE. REPLACED THE BATTERY PACKS IAW AMM 33-53. OPS CHECKED GOOD.

Part: SPLICE — CUT (FUSELAGE) · airframe 68,765 hrs · 51,040 cycles

SPLICE IN APB, STA 1338, TEE CHORD BETWEEN L26L AND L27L WITH NO FASTENERS IN FORMER TAB, SPLICE CUT IS BETWEEN FORMER TAB AND L26L END FITTING. REPAIRED IAW PRI 548159-14, REV "0" AND "1" AND FINAL ER/A 548159-14, REV "A".

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 68,765 hrs · 51,040 cycles

RIGHT AFT OVERWING EXIT DOOR, PAN CRACKED AT FWD AFT SUPPORT BRACKET. REPAIRED IAW PRI 548238-14, REV 0 AND ER/A 548238-14, REV ORIGINAL.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 65,995 hrs · 49,110 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 14D IN THE CABIN WAS INOPERATIVE. MAINTENANCE FOUND WIRES DAMAGED IN THE UNDERSEAT HARNESS. THE WIRE HARNESS WAS REPAIRED AND THE SYS RETURNED TO NORMAL OPERATION. LP 6717398.

Part: SKIN — CRACKED (FUSELAGE) · airframe 77,562 hrs · 58,148 cycles

DURING HMV4 AT QRO, WHILE A SID INSPECTION WAS BEING PERFORMED, A 0.125 LONG CRACK ON THE FUSELAGE SKIN 5911432-81, AND TWO (0.152 AND 1.906 LONG) CRACKS ON THE FUSELAGE SKIN 5911432-83 WERE FOUND, ALL OF THEM LOCATED NEAR STA Y=1418, BETWEEN L3LH AND L3RH, REPAIRED PER SECTION I ER/A 521202-14AD REV. ORIGINAL

Part: DISPLAY — INOPERATIVE (COCKPIT) · airframe 64,417 hrs · 48,106 cycles

THE F/O PRIMARY FLIGHT DISPLAY FAILED AFTER TAKEOFF WITH CREATED SMOKE AND FUMES IN THE COCKPIT. CREW RETURNED THE ACFT AND LANDED UNEVENTFULLY. F/O PRIMARY FLIGHT DISPLAY WAS FOUND TO BE INOPERATIVE. INSPECTED WIRING AND PROPER VOLTAGE AT THE CONNECTOR WITH NO DEFECTS NOTED SO THE PFD WAS REPLACED. OPS CHECKED NORMAL.

Part: LONGERON — DAMAGED (BS 1407-1422) · airframe 63,213 hrs · 47,220 cycles

ELONGATED HOLES WERE FOUND ON LONGERON 2R BS 1407-1422. DAMAGE LONGERON REMOVED, NEW LONGERON WAS DRILLED, ADJUSTED, TREATED, AND PAINTED. NEW LONGERON INSTALLED IAW SRM 53-02, PAR 12, FIG 18.

Part: VANE — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

RUSTED HARDWARE ON LT OTBD FLAP INBD VANE CLEVIS (AYP). RUSTED HARDWARE ON LT OTBD FLAP INBD VANE CLEVIS WERE REPLACED IAW AMM 20-30-01. CORROSION LEVEL 2. PRIMARY STRUCTURE.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PLATE NR 1460C AT COUNTERSINK AREA, MRB 57-083-02, REF 20000005843, CORROSION ON COUNTERSINK WAS REMOVED AND MAXIMUM DIAMETER ALLOWABLE IS 0.532" AND WERE FOUND 4 COUNTERSINK ADJACENT OUT OF LIMITS MEASURED 0.545", 0.570", 0.548" AND 0.562" ON ACCESS PLATE 1460C, THEREFORE ACCESS PLATE WAS REPLACED IAW SRM 51-22-2, A CON II MEASURING STICK WAS REMOVED AND INSTALLED ON NEW ACCESS PLATE IAW AMM 28-40-02-201. SUPPORT WAS REMOVED IAW SRM 51-30-5 NEW ACCESS PLATE WAS DRILLED IAW SRM 51-10-4, NEW DRILL HOLES WERE TREATED AND PAINTED IAW SRM 51-10-3 AND SUPPORT WAS INSTALLED IAW SRM 51-30-5.

Part: LONGERON — CORRODED (BS 1297-1309) · airframe 69,714 hrs · 51,764 cycles

CORROSION ON LONGERON 22L, BS 1297-1309. THE DAMAGE WAS REMOVED, AND A NEW SECTION OF THE LONGERON WAS DRILLED, ADJUSTED, TREATED, PAINTED AND INSTALLED.

Part: CARGO TRACK — CORRODED (BS 1007-1222) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON CARGO TRACK BS 1007-1222. NEW CARGO TRACK DRILLED, TREATED, PAINTED AND INSTALLED IAW SRM 51-10-3, PAR 14,21 AND 38 AND 51-30-1.

Part: CARGO TRACK — CORRODED (BS 1212-1240) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON CARGO TRACK FROM BS 1212-1240. CARGO TRACK REMOVED AND TRACK DRILLED AND INSTALLED IAW SRM 51-10-3 PAR. 14 AND 21 SRM 51-30-1.

Part: LONGERON — CORRODED (BS 1338-1380) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LONGERON 24L BETWEEN BS 1338-1380. LONGERON REPLACED IAW SRM 51-30-2, 51-30-5, 53-14-4, AND 51-10-3 PAR 21,14,38.

Part: LONGERON — CRACKED (BS 1437) · airframe 63,213 hrs · 47,220 cycles

CRACK ON LONGERON 5R BS 1437. DAMAGE LONGERON WAS REMOVED NEW LONGERON AND SPLICE WERE DRILLED, ADJUSTED, TREATED, PAINTED AND WERE INSTALLED IAW SRM 53-02, FIG 18, 51-10-3, 51-30-2, 51-30-5.

Part: PAN — CRACKED (CARGO DOORWAY) · airframe 63,213 hrs · 47,220 cycles

CRACKED FWD DOOR PAN ON BEAM NR 3 AT MID CARGO DOOR, C2, REF NRC 20000006058 CARD 67 A/C ZONE 100. CRACK IN DOOR PAN STOP DRILLED 52.05, FIG 50, NEW DOUBLER WAS FABRICATED IAW SRM 52.05, FIG 50. NEW DOUBLER WAS PAINTED IAW SRM 51.10.3 PAR 14. REPAIR DOUBLER WAS INSTALLED IAW SRM 52.05, FIG 50 AND 51.30.2.

Part: ANGLE — CRACKED (BS 1418) · airframe 63,213 hrs · 47,220 cycles

CRACK ON ANGLE BS 1418 BETWEEN LONGERON 1-2R.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 69,714 hrs · 51,764 cycles

RT WING FUEL TANK ACCESS PANEL 1460 CORRDED. REPLACED THE ACCESS PANEL.

Part: ACCESS PANEL — CORRODED (WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON FUEL TANK ACCESS PANEL 1466. CORROSION REMOVED AND FOUND OUT OF LIMITS AND WAS REPLACED IAW SRM 51-22-2A CONDITION.

Part: CUSP WEB — CORRODED (BS 1180-1272) · airframe 69,714 hrs · 51,764 cycles

RIGHT CUSP WEB CORRODED, BS 1180-1190, 1193-1195, 1212, 1216, 1235-1244, 1272. X -54 TO -60. DAMAGE REMOVED AND A REPAIR FABRICATED AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 996-1005) · airframe 69,714 hrs · 51,764 cycles

RIGHT CUSP WEB CORRODED BS 996 - 1005, X -54 TO X -60. DAMAGE REMOVED, REPAIR INSTALLED.

Part: CUSP WEB — CORRODED (BS 1060-1079) · airframe 69,714 hrs · 51,764 cycles

PREVIOUS REPAIR OF RH CUSP WEB CORRODED, BS 1060 - 1079, X -54 TO -60. A NEW REPAIR WAS FABRICATED AND INSTALLED.

Part: SKIN — DAMAGED (RUDDER) · airframe 63,213 hrs · 47,220 cycles

DAMAGED METAL ON RT AND LT RUDDER SURFACE. REPAIRED IAW SRM 51-70-1.

Part: TAB — DAMAGED (RUDDER) · airframe 63,213 hrs · 47,220 cycles

DAMAGED METALLIZED ON RUDDER CONTROL TAB. METALLIZED ON RUDDER CONTROL TAB WAS REPAIRED IAW AC 0958 CARD 2000-8149-07, CREW 02 "7412731" SRM 51-70-1, AD PAR 23A. RII COMPLETED BY INSPECTION STAMP INSPECTOR C.D.T.L 200500612 TECHOPS DELTA ID550902.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1470C. CORROSION REMOVED AND FOUND OUT OF LIMITS. ACCESS PANEL REMOVED IAW SRM 51-22-2A CONDITION II. BUSHING FABRICATED" AND COUNTERSUNK IAW SRM 51-22-2A PAR NR 6. NEW BUSHING AND AREA WERE TREATED IAW SRM 51-10-3, PAR. 21 AND NEW BUSHING AND AREA WERE TREATED IAW SRM 51-10-3, PAR. 21 AND NEW BUSHING WAS INSTALLED IAW SRM 51-22-2A, PAR 6.

Part: CUSP WEB — CORRODED (BS 622-653) · airframe 69,714 hrs · 51,764 cycles

CUSP WEB CORRODED BS 650-653, 622-644 X 54 - 60. DOUBLERS FABRICATED AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 844-855) · airframe 69,714 hrs · 51,764 cycles

RIGHT CUSP WEB CORRODED BS 844 - 855, X -54 TO X -60. THE DAMAGE WAS REMOVED AND A REPAIR FABRICATED AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 719-721) · airframe 69,714 hrs · 51,764 cycles

RIGHT CUSP WEB CORRODED, BS 719 - 721, X -54 TO X -60. THE DAMAGE WAS REMOVED, REPAIR FABRICATED AND INSTALLED.

Part: LONGERON — CORRODED (BS 1138) · airframe 69,714 hrs · 51,764 cycles

LONGERON 23L END FITTING CORRODED, BS 1338 IN AFT CARGO. REPLACED.

Part: CUSP WEB — CORRODED (BS 465-484) · airframe 69,714 hrs · 51,764 cycles

PREVIOUS CUSP WEB REPAIR CORRODED, REPLACED STA 465-484, X -54 TO -60.

Part: CUSP WEB — CORRODED (BS 984-988) · airframe 69,714 hrs · 51,764 cycles

CORRODED CUSP WEB BS 984-988 X -54 TO -60. DOUBLER, TRIPLER FABRICATED AND INSTALLED.

Part: CUSP WEB — CORRODED (BS 712-731) · airframe 69,714 hrs · 51,764 cycles

PREVIOUS CUSP WEB REPAIR CORRODED. BS 712-731 BETWEEN X 44 - 60. REPAIR FABRICATED AND INSTALLED.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1335C AT COUNTERSINK AREA AND DAMAGED DOME NUTS, CORROSION REMOVED, AND FOUND TO BE OUT OF LIMITS. REWORKED IAW SRM 51-22-2A, CONDITION II, REPAIR BUSHINGS INSTALLED IAW SRM 51-22-2A, NUTS DAMAGED WERE REMOVED AND NEW NUTS WERE INSTALLED IAW SRM 51-30-02.

Part: LONGERON — CRACKED (BS 1437) · airframe 63,213 hrs · 47,220 cycles

LONGERON 4L BS 1437 CRACKED. SPLICE AND LONGERON SECTION REMOVED IAW SRM 53-02, FIG 18. NEW LONGERON SECTION AND SPLICE FABRICATED IAW SRM 53-02, FIG 18. NEW LONGERON SECTION AND SPLICE TREATED AND PAINTED IAW SRM 51-10-3, PAR 14 AND 21. NEW LONGERON SECTION AND SPLICE INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: LONGERON — CRACKED (BS 1380) · airframe 63,213 hrs · 47,220 cycles

CRACK ON LONGERON 9L BS 1380. LONGERON REMOVED, NEW SECTION AND SPLICES WERE INSTALLED IAW SRM 53-02, FIG 18, & 51-30-2,51-10-3, PAR 21-14.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION FOUND ON RT FUEL TANK ACCESS PANEL 1414C. CORROSION REMOVED AND FOUND OUT OF LIMITS. REPLACED THE ACCESS PANEL IAW SRM 51-22-2A.

Part: LONGERON — CRACKED (BS 984) · airframe 63,213 hrs · 47,220 cycles

CRACKED LONGERON 4R BS 984 IN CROWN AREA. DAMAGE REMOVED AND NEW SECTION OF LONGERON. NEW LONGERON & SPLICES FABRICATED AND INSTALLED IAW SRM 53-02, FIG 18, 51-30-2, 51-30-5.

Part: LONGERON — CRACKED (BS 465) · airframe 63,213 hrs · 47,220 cycles

CRACKED LONGERON 4R BS 465 AT CROWN AREA. LONGERON SECTION REMOVED. NEW LONGERON DRILLED AND AJUSTED SPLICE. INSTALLED NEW SECTION AND SPLICE IAW SRM 53-02, FIG 18, & 51-30-2.

Part: CUSP WEB — CORRODED (BS 502-512) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT CUSP WEB REPAIR DOUBLER, X=-54 TO X =-60 BETWEEN BS 502-512. DOUBLER WAS REMOVED, NEW DOUBLER FABRICATED IAW SRM 53-05, FIG 131A-6 AND DWG 9930538-29.

Part: FLOORBEAM — CORRODED (BS 1322) · airframe 69,714 hrs · 51,764 cycles

FLOORBEAM CORRODED, BS 1322 X -42 . REPAIR FABRICATED AND INSTALLED.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1464C AT COUNTERSINK. CORROSION WAS REMOVED AND FOUND OUT OF LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1465C AT COUNTERSINK. CORROSION WAS REMOVED AND WAS FOUND OUT LIMITS, ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL TANK ACCESS PANEL 1361C AT COUNTERSINK AND SETTLEMENT. CORROSION REMOVED AND FOUND OUT OF LIMITS, ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION III.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL TANK ACCESS PANEL 2302C AT COUNTERSINK. CORROSION WAS REMOVED AND WAS FOUND OUT OF LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT WING FUEL TANK ACCESS PANEL 1355C AT COUNTERSINK. CORROSION WAS REMOVED AND WAS FOUND OUT OF LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1462C AT COUNTERINK. CORROSION WAS REMOVED AND WAS FOUND OUT OF LIMITS, ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL TANK ACCESS PANEL 1357C. CORROSION REMOVED AND FOUND ONE COUNTERSINK OUT LIMITS. ACCESS PANEL WAS REPAIRED IAW SRM 51-22-2A, CONDITION II. BUSHING FABRICATED AND COUNTERSUNK IAW SRM 51-22-2A, PAR 6. NEW BUSHING AND AREA WERE TREATED IAW SRM 51-10-3, PAR 21 AND NEW BUSHING WAS INSTALLED IAW SRM 51-22-2A, PAR NR 6.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT WING FUEL TANK ACCESS PANEL 1454C AT COUNTERSINK. CORROSION WAS REMOVED AND WAS FOUND OUT LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1436C AT COUNTERSINK AREA. CORROSION REMOVED AND FOUND OUT OF LIMITS. ACCESS PANEL WAS REPAIRED IAW SRM 51-22-2A, CONDITION II. REPAIR BUSHINGS WERE FABRICATED IAW SRM 51-22-2A, PAR 6 CONDITION II, B, 4. NEW BUSHINGS AND REWORKED AREA WERE TREATED IAW SRM 51-10-3, PAR 21. REPAIR BUSHINGS INSTALLED IAW SRM 51-22-2A.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL TANK ACCESS PANEL 1311C AT COUNTERSINK AREA AND DAMAGE. CORROSION REMOVED AND FOUND OUT OF LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A, CONDITION III.

Part: ACCESS PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON RT FUEL TANK ACCESS PANEL 1410C AT COUNTERSINK AREA. CORROSION REMOVED AND FOUND OUT OF LIMITS ACCESS PANEL REPLACED IAW AMM 51-22-2A.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL ACCESS PANEL 1363C AT COUNTERSINK. CORROSION REMOVED AND WAS FOUND OUT LIMITS. ACCESS PANEL WAS REPLACED IAW SRM 51-22-2A CONDITION II.

Part: ACCESS PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 63,213 hrs · 47,220 cycles

CORROSION ON LT FUEL TANK ACCESS PANEL 1307C AT COUNTERSINK. CORROSION WAS REMOVED AND FOUND THREE COUNTERSINKS OUT OF LIMITS. ACCESS PANEL WAS REPAIRED IAW SRM 51-22-2A, CONDITION II. BUSHINGS WERE FABRICATED AND COUNTERSUNK IAW SRM 51-22-2A PAR 6. NEW BUSHINGS AND AREA WERE TREATED IAW SRM 51-10-3 PAR 21 AND BUSHINGS INSTALLED IAW SRM 51-22-2A, PAR 6.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 63,213 hrs · 47,220 cycles

DELAMINATED FLOOR PANEL. FABRICATED FLOOR PANELS IAW AMM 53-20-01-201.

Part: FLOOR PANEL — DELAMINATED · airframe 63,213 hrs · 47,220 cycles

DELAMINATED FLOOR PANEL . FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: LONGERON — CRACKED (BS 1338) · airframe 63,213 hrs · 47,220 cycles

CRACKED LONGERON 1 & 2L/R ENDS BS 1338, LONGERON ENDS WERE REMOVED, NEW LONGERON ENDS WERE DRILLED AND ADJUSTED, NEW LONGERON ENDS WERE TREATED, PAINTED AND INSTALLED IAW SRM 51-30-2, SRM 51-30-5, SRM 51-10-4, DWG 5911422, REV B1, SRM 51-10-3 PAR 21, 14.

Part: LONGERON — CRACKED (12 LEFT) · airframe 63,213 hrs · 47,220 cycles

LONGERON 12L CRACKED, DAMAGE REMOVED, NEW SECTION AND SPLICE WERE DRILLED, ADJUSTED, TREATED, PAINTED, AND INSTALLED IAW SRM 53-02, FIG 18.

Part: CUSP WEB — CORRODED (BS 598-617) · airframe 69,714 hrs · 51,764 cycles

CUSP WEB CORRODED. X -54 TO -60, BS 598 - 617.

Part: CUSP WEB — CORRODED (BS 996-1147) · airframe 69,714 hrs · 51,764 cycles

CUSP WEB CORRODED. X -54 TO -60, BETWEEN BS 996-1147.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 63,213 hrs · 47,220 cycles

NICKS ON PREVIOUS REPAIR DOUBLER, PAN, SEAL RETAINERS BETWEEN BEAMS 1-2, AT AFT CARGO DOOR AFT EDGE AROUND HOLD OPEN SHAFT AREA. REPAIR DOUBLER REMOVED IAW SRM 51-30-5, REPAIR ANGLE FABRICATED IAW SRM 52-05, FIG 26A. REPAIR ANGLE TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21 REPAIR ANGLE INSTALLED IAW SRM 51-30-5.

Part: PANEL — CORRODED (LAVATORY SERVICE) · airframe 69,714 hrs · 51,764 cycles

AFT LAV SERVICE PANEL, PANEL PAN CORRODED AND REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 62,540 hrs · 46,791 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT SEAT 3D IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK. OPS CHECK WAS GOOD.

Part: SKIN — CRACKED (BS 581) · airframe 61,608 hrs · 46,108 cycles

SKIN CRACKED NEAR BS 581 & 3 INCHES LT OF LONGERON 30. REMOVED DAMAGED SKIN WITH A 21 X 11 INCH CUT OUT. BLENDED INTERNAL DOUBLER. REMOVED DAMAGE TO INNER DOUBLER WITH A 3.25 X 2 INCH CUTOUT. DAMAGE CONTAINED. REPAIR PARTS FABRICATED AND INSTALLED.

Part: SKIN — CORRODED (BS 579) · airframe 61,569 hrs · 46,085 cycles

FUSELAGE SKIN WAS FOUND PILLOWING AT BS 579, L30. REPAIR IAW ERA 517181-14.

Part: CLAMP — OUT OF ADJUST (TAILCONE RELEASE) · airframe 61,569 hrs · 46,085 cycles

MX FOUND THAT THERE WAS EXCESSIVE SLACK IN THE TAILCONE RELEASE CABLE CONDUIT CLAMPS AT THE 7 O'CLOCK POSITION. THE CABLE SYS CLAMPS WERE TIGHTENED AND ADJUSTED IAW SRM 51-30-01.

Part: PIN — WORN (UNKNOWN) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT THE TEE PIN AND THE TEE PIN BUSHING WERE WORN BEYOND ALLOWABLE LIMITS AND REQUIRED REPLACEMENT.

Part: FRAME — CRACKED (BS 1418) · airframe 61,569 hrs · 46,085 cycles

FRAME BS 1418 AFT FLANGE CRACKED AT LONGERON 2R. REMOVED FRAME, DRILLED NEW FRAME & INSTALLED ALL FASTENERS IAW DWG SR09530003.

Part: RECEPTACLE — WORN (TAILCONE RELEASE) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT BOTH THE LT AND RT UPPER RELEASE LATCH RECEPTACLES FOR THE TAILCONE WERE WORN OUT OF ALLOWABLE LIMITS. THE RECEPTACLES WERE REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORY.

Part: PIN — WORN (TAILCONE RELEASE) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE LATCH RECEPTACLE ALIGNMENT PINS WERE WORN OUT OF ALLOWABLE LIMITS. THE RECEPTACLES WERE REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. THE FUNCTIONAL CHECK WAS COMPLETED SATISFACTORY.

Part: LONGERON — CRACKED (BS 1418) · airframe 61,569 hrs · 46,085 cycles

LONGERON 2R CRACKED BS 1418. REMOVED FASTENERS. REMOVED LONGERON 2R FROME BS 1410-1420. FABRICATED LONGERON SECTION IAW SRM 53-02. INSTALLED LONGERON REPAIR IAW 53-02 FIG-8.

Part: CABLE — FRAYED (TAILCONE RELEASE) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE CABLE WAS FRAYED BEYOND ALLOWABLE LIMITS. THE CABLE WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS.

Part: BRACKET — WORN (TAILCONE) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT THE TAILCONE UPPER RT BRACKET IS WORN. THE BRACKET WAS REPLACED AND THE SYSTEM WAS RIGGED TO SPECIFICATIONS. FUNCTIONAL CHECK WAS COMPLETED SATISFACTORY.

Part: BRACKET — WORN (TAILCONE) · airframe 61,569 hrs · 46,085 cycles

MX DISCOVERED THAT THE TAILCONE LT AND RT SPRING BRACKETS ARE WORN FROM THE SPRING. THE BRACKETS WERE REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS. FUNCTIONAL CHECK WAS COMPLETED SATISFACTORILY.

Part: BULKHEAD — CRACKED (NOSE) · airframe 61,569 hrs · 46,085 cycles

BULKHEAD CRACKED AT LOWER RT RADOME ALIGNMENT STOP. REMOVED FASTENERS IN AREA. REMOVED SPLICE, CUT OUT DAMAGE, HFEC TRIM OUT IAW NDT SP06-10-01.001 & ETHF, AND OPEN HOLES IAW NDTSP 06-10-01.003 DAMAGE CONTAINED. INSTALLED NEW DOUBLER AND FITTING IAW ER/A 483847-14MA, REV ORIG.

Part: SKIN — CRACKED (BS 1380) · airframe 61,569 hrs · 46,085 cycles

SKIN CRACKED AT RT AFT FUSELAGE ABOVE PYLON BS 1380. VERIFIED ENDS OF CRACKS HFEC IAW SPM 06-10-01.001. INSTALLED REPAIR IAW PRI 517079-14, REV 1 WAITING FOR FINAL ER/A. 361750/QC1974 FINAL ER/A 517079-14 REV ORIG 750016.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,569 hrs · 46,085 cycles

ACFT SKIN CRACKED APPROX .2500" LONG AT FASTENERS 3" INBD OF LONGERON 3 L. WORK ACCOMPLISHED IAW ER/A 517075-14, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1380) · airframe 61,569 hrs · 46,085 cycles

ACFT SKIN CRACKED APPROX .2500" LONG AT FASTENER APPROX 2" ABOVE LONGERON 13 RT BS 1380 . VERIFIED ENDS OF CRACKS HFEC IAW SPM 056-10-01.001, QC2021. INSTALLED REPAIR IAW PRI 517079-14, REV 1 WAITING FOR FINAL ER/A. FINAL ER/A 517079-14, REV ORIG 750016.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,569 hrs · 46,085 cycles

ACFT SKIN CRACKED APPROX .2500" LONG AT FASTENER 3" INBD OF LONGERON 3 RIGHT. WORK ACCOMPLISHED IAW ER/A 517076-14, REV ORIGINAL.

Part: CONNECTOR — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,528 hrs · 46,052 cycles

DURING LINE CHECK, MX FOUND THAT EMERGENCY PATHWAY LIGHTING AT ROWS 18-23D IN THE CABIN WERE INOPERATIVE. MX FOUND A LOOSE WIRE IN THE CONNECTOR, RECONNECTED THE WIRE AND THE SYS RETURNED TO NORMAL OPERATION.

Part: FLOOR PANEL — DAMAGED (GALLEY) · airframe 59,555 hrs · 44,632 cycles

F/C GALLEY FLOOR SOFT. REMOVED FLOOR COVERING AND MOISTURE MEMBRANE. REMOVED FLOOR PANEL 160E. MANUFACTURED SAME. INSPECTED AREA AND INSTALLED NEW FLOOR PANEL, MOISTURE MEMBRANE AND FLOOR COVERING.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 59,313 hrs · 44,447 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE FORWARD LEFT AND RIGHT OVERHEAD EMERGENCY ESCAPE LIGHTING WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERY POWER SUPPLY B5-103 AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,026 hrs · 44,258 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY ESCAPE LIGHTING AT ROWS 32-34 AND THE LEFT DOOR WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY — DISCHARGED (CABIN) · airframe 58,849 hrs · 44,142 cycles

DURING SERVICE CHECK, TEST OF EMERGENCY LIGHTS FOUND LT AND RT FWD OVERWING EXIT LIGHTS ABOVE DOORS INOPERATIVE. REPLACED BATTERIES AND SYSTEM CHECKED GOOD.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 58,788 hrs · 44,092 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING AT ROW 17D IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,545 hrs · 43,926 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT BOTH OF THE OVERWING EMERGENCY EXIT SIGNS WERE INOPERATIVE. MAINTENANCE REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY — DISCHARGED (CABIN) · airframe 58,247 hrs · 43,729 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE FORWARD OVERWING EMERGENCY EXIT ROW LIGHTS ABOVE THE DOOR WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPERATIONAL CHECK OF THE EXIT SIGN WAS GOOD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 57,950 hrs · 43,553 cycles

DURING PSV VISIT MSP FORWARD JACK FAILED AND DAMAGED LOWER FUSELAGE SKIN JACK PAD AREA AND INTERNAL STRUCTURE. WORKED ON NRC 166. REPAIRED PER ERA 499356-14.

Part: RELEASE CABLE — MISROUTED (TAILCONE) · airframe 57,950 hrs · 43,553 cycles

MAINTENANCE DISCOVERED THAT THE TAIL CONE EXTERNAL RELEASE HANDLE CABLE WAS MISROUTED THROUGH THE PULLEY BRACKET. THIS COULD HAVE AN ADVERSE AFFECT ON THE OPERATION OF THE RELEASE SYSTEM AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE CABLE ROUTING WAS CORRECTED ON NON-ROUTINE CARD 97.

Part: BATTERY — DISCHARGED (CABIN) · airframe 57,012 hrs · 42,906 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY PATH LIGHTS INOPERATIVE. LIGHTS 31DE TO 36DE. MAINTENANCE RE-SECURED THE BATTERY B5-212. LIGHTS OPERATIONAL CHECK IS GOOD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 55,494 hrs · 41,868 cycles

DURING PSV VISIT IN MSP FWD JACK FAILED AND DAMAGED BELLY SKIN AND FORWARD JACK PAD AREA. REPAIRED PER ERA 499356-14.

Part: WIRE HARNESS — SHORTED (EMERGENCY LIGHT) · airframe 55,260 hrs · 41,731 cycles

DURING LINE CHECK, MX FOUND PATH EMERGENCY LIGHT AT 1C INOPERATIVE. MX REPLACED SHORTED LIGHT HARNESS, FWD/ AFT POWER SUPPLIES, AND BATTERY PACKS IAW AMM 33-53-00. OPS OF LIGHT NOW CHECKS OK.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHT) · airframe 55,100 hrs · 41,649 cycles

DURING LINE CHECK MX FOUND EMERGENCY PATH LIGHT AT SEAT 26D INOPERATIVE. MX RE-SECURED A PIN IN THE LIGHT ASSY. OPERATION OF LIGHT NOW CHECKS OK.

Part: RIB — CRACKED (XIS 134.54) · airframe 53,116 hrs · 40,307 cycles

LT WING L/E RIB CRACKED STA XIS 134.54.

Part: PAN — CRACKED (L1 DOOR) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, A CRACK WAS FOUND ON INNER PAN OF L1 DOOR AFT LOWER CORNER. DOOR WAS REPAIRED IAW SRM 52-05 FIG 18A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 48,511 hrs · 37,219 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE SKIN AT STA Y=499 BETWEEN LONGERON 3 AND 4 LT. CRACK WAS REPAIRED IAW SRM 53-04D FIG38 AND 51-30-2 PAR 13.

Part: NOZZLE — CRACKED (RADIO RACK) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, CRACKS WERE FOUND ON FWD CORNERS OF RADIO RACK FAN AIR EXHAUST NOZZLE. EXHAUST NOZZLE WAS REPAIRED IAW ER/A 464964-14MA.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, A CRACK WAS FOUND ON LONGERON 24 LT AT STA Y=200AT E/E COMPARTMENT. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: PAN — CRACKED (AFT CARGO DOOR) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, A CRACK WAS FOUND ON PAN FWD EDGE OF C3 AT BEAM NR 2 PAN WAS REPAIRED IAW SRM 52-05D FIG 50.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A CRACK SUPPORT WAS FOUND FOR CABIN FLOOR PANEL 465A. SUPPORT WAS REPAIRED IAW ER/A 466354-14.

Part: SPLICE — CORRODED (BULKHEAD) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, CORROSION WAS FOUND ON AFT P-DOME WEB SPLICE AT 6HRS POSITION. WEB SPLICE WAS REPLACED IAW DOUGLAS DWG 5910130.

Part: SEAT TRACK — DAMAGED (BS 705) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, BLEND OUT WAS FOUND OUT OF LIMIT ON SEAT TRACK AT STA Y=705 X=22. SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: MEMBRANE — CRACKED (FUSELAGE) · airframe 48,511 hrs · 37,219 cycles

DURING HMV A CRACKED WAS FOUND ON MEMBRANE AT STA Y=218 AND X=10. MEMBRANE WAS REPAIRED IAW SRM 51-30-2 AND 51-30-5.

Part: FRAME — CORRODED (BS 1287) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, EXFOLIATION CORROSION WAS FOUND ON FRAME AT STA Y=1287 LONGERON 30 IN AFT CARGO COMPARTMENT. FRAME WAS REPAIRED IAW SRM 53-03D FIG 2A.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, GALVANIC CORROSION WAS FOUND ON FLOOR PANEL SUPPORT AT STA Y=160 TO 200 X=-8 FWD WET AREA. SUPPORT WAS REPLACED IAW SRM 51-30-01.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV CORROSION WAS FOUND ON RIGHT CUSP WEB AT STA Y=277. CUSP WEB WAS REPAIRED IAW DOUGLAS DWG SG09530003.

Part: SEAT TRACK — DAMAGED (BS 455) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, BLEND OUT WAS FOUND OUT OF LIMIT ON SEAT TRACK AT STA Y=455 X=54 . SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: SEAT TRACK — DAMAGED (BS 641) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, BLEND OUT WAS FOUND OUT OF LIMIT ON SEAT TRACK AT STA Y=641 X=22. SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: PAN — CRACKED (FWD CARGO DOOR) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, A CRACK WAS FOUND ON FWD CARGO COMPARTMENT DOOR OUTBD PAN WAS REPAIRED IAW SRM 52-03D FIG 10.

Part: CUSP WEB — CORRODED (BS 541-580) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, CORROSION WAS FOUND ON LEFT CUSP WEB BETWEEN STA Y=541 AND 560. CUSP WEB WAS REPAIRED IAW DOUGLAS DWG SG09530003.

Part: TAB — DAMAGED (LT ELEVATOR) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, LIGHTNING STRIKE WAS FOUND ON TRAILING EDGE ON LEFT ELEVATOR CONTROL TAB. TAB WAS REPAIRED IAW SRM 55-04D PARAGRAPH 3 FIG 2. WEIGHT AND BALANCE IAW SRM 55-20-2D.

Part: RIB — CRACKED (RT WING) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A CRACK RIB WAS FOUND AT RIGHT WING FIXED LEADING EDGE AT STA XRS=164. RIB WAS REPLACED IAW SRM 51-30-5,51-30-2 AND DWG 9937517 REVE-J.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A CRACKED SUPPORT WAS FOUND FOR CABIN FLOOR PANEL 927A. SUPPORT WAS REPAIRED IAW ER/A 466354-14.

Part: PAN — CRACKED (CARGO DOOR) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A CRACK WAS FOUND ON FWD CARGO COMPARTMENT DOOR INBD PAN. DOOR WAS REPAIRED IAW SRM 52-05 FIG 26A.

Part: FRAME — CORRODED (BS 1380 L28L-R) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, CORROSION WAS FOUND ON FRAME Y=1380 BETWEEN LONGERON 28 LT AND 28 RT. FRAME WAS REPLACED IAW DOUGLAS DWG 9912246.

Part: INTERCOSTAL — CORRODED (BS 1380) · airframe 48,511 hrs · 37,219 cycles

DURING HMV, CORROSION WAS FOUND ON INTERCOSTAL AT STA Y=1380 LONGERON 28 RT. INTERCOSTAL WAS REPAIRED IAW SRM 51-70-05 FIG 1.

Part: RIB — CRACKED (RT WING) · airframe 48,518 hrs · 37,224 cycles

DURING HMV A CRACK WAS FOUND ON RT WING LEADING EDGE RIB AT STA XRS=271. RIB WAS REPAIRED IAW SRM 57-06 BD FIG 801D.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, GENERAL SURFACE CORROSION WAS FOUND ON FUSELAGE SKIN AT ANTENNA RADIO ALTIMETER SETTLING SURFACE. REMOVED CORROSION IAW SRM 51-10-3D PARAGRAPH 35. REMAINING THICKNESS AT STA Y=655-750 WITHIN LIMIT IAW SRM 53-01 FIG 1 AT STA Y=598-617 OUT OF LIMIT AND TO BE REPAIRED ON NRC T0088183.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A CRACK LEFT CUSP WEB WAS FOUND AT STA Y=800. CUSP WEB WAS REPAIRED IAW SRM 53-05D FIG 827D.

Part: SEAT TRACK — DAMAGED (BS 531) · airframe 48,518 hrs · 37,224 cycles

DURING HMV, A BLEND OUT WAS FOUND OUT OF LIMIT ON SEAT TRACK AT STA Y=531 X=22. SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON FLOOR SUPPORT STA Y=200 AND X-10 TO -40 FWD WET AREA. FLOOR SUPPORT WAS REPLACED IAW DOUGLAS DWG 9936534.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV BLEND OUT IS OUT OF LIMIT ON SEAT TRACK X=22 STA Y=485, SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A CORRODED AND DEFORMED SLANT PANEL SUPPORT WAS FOUND AT STA Y=1250 BETWEEN LONG 27 LT AND 25 RT. SUPPORT WAS REPLACED IAW ER/A 413029-14MA.

Part: STIFFENER — CRACKED (BULKHEAD) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A BROKEN P-DOME STIFFENER WAS FOUND AT 12:00 POSITION. STIFFENER WAS REPLACED IAW DOUGLAS DWG 9915562.

Part: CHANNEL — CORRODED (BS 1354) · airframe 48,510 hrs · 37,218 cycles

DURING HMV PITTING CORROSION WAS FOUND ON CHANNEL AT STA Y=1354 AND X=-32 AT RT AFT LAVATORY. CHANNEL WAS REPLACED IAW DOUGLAS DWG 5925005.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED WAS FOUND ON SUPPORT FOR CABIN FLOOR PANEL 389A. SUPPORT WAS REPLACED IAW DOUGLAS DWG 9952521-5.

Part: RIB — CRACKED (LT WING) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED RIB WAS FOUND AT LEFT WING FIXED LEADING EDGE STA XIS=136 LOWER SIDE. RIB WAS REPAIRED IAW ER/A 466349-14 REV ORIG.

Part: FITTING — CORRODED (DOOR FRAME) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON FWD DOOR JAMB LOWER CORNER FITTING AT C3. FITTING WAS REPLACED IAW SRM 51-30-5.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED SUPPORT WAS FOUND FOR PANEL NR 693A. SUPPORT WAS REPLACED IAW DWG 9952521.

Part: FITTING — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED WAS FOUND ON FITTING AT STA Y=927 X=-44. FITTING WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON PILOT REGULATOR VALVE SUPPORT AT STA Y=1358 LONG 13 LT. SUPPORT WAS REPLACED IAW SRM 51-30-1.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON FLOOR PANEL SUPPORT STA Y=255 X=34 FWD WET AREA. FLOOR SUPPORT WAS REPLACED IAW DOUGLAS DWG 5930544.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON RIGHT CUSP WEB AT STA Y=551. CUSP WEB WAS REPAIRED IAW ER/A 398191-14MA.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON FLOOR SUPPORT STA Y=166 AND X=52 FWD WET AREA. FLOOR SUPPORT WAS REPLACED IAW DOUGLAS DWG 9936534.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV BLEND OUT AREA WAS FOUND TO BE OUT OF LIMIT ON SEAT TRACK AT STA Y=1025 X=54. SEAT TRACK WAS REPAIRED IAW SRM 53-05D FIG 4F.

Part: SEAT TRACK — DAMAGED (BS 996) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, BLEND OUT AREA WAS FOUND TO BE OUT OF LIMIT ON SEAT TRACK AT STA Y=996 X=54. SEAT TRACK TO BE REPLACED ON NRC T0088136.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV GALVANIC CORROSION WAS FOUND ON FLOOR PANEL SUPPORT STA Y=180 FROM X=-1O TO -40 FWD WET AREA. SUPPORT WAS REPLACED IAW SRM 51-30-2.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, GALVANIC CORROSION AND WEAR WAS FOUND ON LONGERONS OF LT LAVATORY FLOOR PAN. LONGERON WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: SUPPORT — CRACKED (CARGO DOOR) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A CRACKED STOP SUPPORT WAS FOUND AT AFT UPPER SIDE OF C3 DOOR. SUPPORT WAS REPLACED IAW DOUGLAS DWG 5910141 REV EY.

Part: ANGLE — CRACKED (BS 1485) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK ANGLE WAS FOUND AT STA Y=1485 AND 1:00 POSITION AT AFT ACCESSORY COMPARTMENT. ANGLE WAS REPLACED IAW DWG 9911842.

Part: SUPPORT — CRACKED (BS 275 L27L) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CRACK WAS FOUND ON LT SLANT PANEL SUPPORT AT STA Y=275 AND LONGERON 27 LT. SUPPORT WAS REPLACED IAW ER/A 413029-14MA REV ORG.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON RIGHT CUSP WEB BETWEEN STA Y=1136 AND 1148. CUSP WEB WAS REPAIRED IAW SRM 51-70-4 FIG 2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON FLOOR SUPPORT STA Y=196 AND X=52 FWD WET AREA. FLOOR SUPPORT WAS REPLACED IAW DOUGLAS DWG 9936534.

Part: SKIN — CRACKED (BS 1309 L6-7L) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON FUSELAGE SKIN AT STA Y=1309 BETWEEN LONGERON 6 AND 7 LT. SKIN WAS REPAIRED IAW SRM 51-30-2 AND 51-20.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON RIGHT CUSP WEB BETWEEN STA Y=1155 AND 1174. CUSP WEB WAS REPAIRED IAW SRM 51-70-4 FIG 2.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON SUPPORT FOR CABIN FLOOR PANEL NR 927E. SUPPORT WAS REPAIRED IAW SRM 51-90-0D.

Part: SUPPORT — CRACKED (BS 1308 L28R) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED WAS FOUND ON FIBERGLASS SUPPORT AT STA Y=1308 LONG 28 RT. SUPPORT WAS REPLACED IAW ER/A 413029-14MA.

Part: ATTACH BRACKET — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMY EXFOLIATION CORROSION WAS FOUND ON ATTACH BRACKET STA Y=198 AND X=-55 FWD WET AREA. BRACKET WAS REPLACED IAW DOUGLAS DWG 9436534.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON RIGHT CUSP WEB BETWEEN STA Y=700 AND 712. CUSP WEB WAS REPAIRED IAW ER/A 398191-14MA.

Part: LONGERON — CRACKED (BS 1193-1212) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A CRACK WAS FOUND ON SPLICE BETWEEN STAY=1193 AND 1212 LONG 28LH. SPLICE WAS REPLACED IAW DOUGLAS DWG 3914677-507.

Part: ANGLE — CRACKED (BS 1463) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, TWO CRACKED ANGLES WAS FOUND ON STA Y=1463 AT 11:00 POSITION AT AFT ACCESSORY COMPARTMENT. ANGLES WERE REPLACED IAW DOUGLAS DWG 9977839.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON ANGLE AT STA Y=1474 CANT BELOW ACCUMULATOR. ANGLE WAS REPLACED IAW DOUGLAS DWG 5917686.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACKED FLOOR SUPPORT WAS FOUND AT STA Y=1271 BETWEEN LONG 30 AND 25 RT. SUPPORT WAS REPLACED IAW ER/A 413029-14MA.

Part: BEAM — CORRODED (DOOR FRAME) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, GALVANIC CORROSION WAS FOUND ON C2 DOOR JAMB UPPER BEAM STA Y=684 TO 694. DOOR JAMB BEAM WAS REPLACED IAW DOUGLAS DWG 5936072.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON FLOOR PANEL SUPPORT STA Y=180 TO 200 X=-44 FWD WET AREA. FLOOR SUPPORT WAS REPLACED IAW DOUGLAS DWG 9936534.

Part: LONGERON — CRACKED (BS 160 L2) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A BROKEN LONGERON WAS FOUND AT STA Y=160 LONG 2. LONGERON WAS REPAIRED IAW SRM 53-02 FIG 18.

Part: SUPPORT — CRACKED (MLG DOOR FRAME) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A BROKEN OBD SUPPORT WAS FOUND AT LT MLG FWD DOOR JAMB. SUPPORT WAS REPLACED IAW DOUGLAS DWG 5930516.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, BLEND OUT IS OUT OF LIMIT ON SEAT TRACK X=22 STA Y732. SEAT TRACK WAS REPAIRED IAW SRM 53-05 FIG 4A.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON CLIP AT STA Y=1437 BETWEEN LONGERON 1 AND 2 LT. CLIP WAS REPLACED IAW SRM 51-30-5.

Part: ATTACH FITTING — CRACKED (RT WING) · airframe 48,510 hrs · 37,218 cycles

DURING HMV A CRACK WAS FOUND ON RIGHT WING LEADING EDGE CLIP AT STA XRS=271. CLIP WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: WEB — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV CORROSION WAS FOUND ON WEB BETWEEN STA Y=1155 AND 1212 AND BETWEEN LONG 29 RT AND BOTTOM OF C3 DOOR JAMB. WEB WAS REPLACED IAW DOUGLAS DWG 5936442.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV, A CRACK WAS FOUND ON SLANT PANEL SUPPORT WITHIN C2 STA Y=579 RT SIDE. SUPPORT WAS REPLACED IAW ER/A 413029-14MA REV ORIG.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 48,510 hrs · 37,218 cycles

DURING HMV GALVANIC CORROSION AND WEAR WAS FOUND ON LONGERONS OF RT LAVATORY FLOOR PAN. LONGERONS WAS REPLACED IAW SRM 51-30-2.

Part: DOOR FRAME — CORRODED (BS 1209 S29R) · airframe 48,502 hrs · 37,214 cycles

DURING HMV AT GDL, CORROSION WAS FOUND IN THE AFT CARGO COMPARTMENT INTERNAL DOOR JAMB DOUBLER AT STA 1209 BETWEEN S-29R AND S-30R. THE DAMAGE WAS REPAIRED PER BOEING INSTRUCTIONS.

Part: SKIN — DENTED (BS 110) · airframe 44,689 hrs · 34,657 cycles

THE FUSELAGE SKIN HAS A LARGE DENT AT STA. 110. THE DAMAGED SKIN WAS CUT OUT AND A REPAIR DOUBLER WAS INSTALLED.

Part: O-RING — OUT OF POSITION (APU) · airframe 43,370 hrs · 33,736 cycles

SMOKE IN COCKPIT AND CABIN AFTER TAKEOFF. FOUND APU OIL CAP SEAL ROLLED BACK. CLEANED APU, INLET AND SURROUNDING AREA. REPLACED COALESCER BAGS. PERFORMED DUCT BURN OUT.

Part: COALESCER BAG — DIRTY (CABIN) · airframe 42,575 hrs · 33,203 cycles

ODOR IN COCKPIT AND CABIN. AIR TURNBACK. REPLACED COALESCER BAGS, PERFORMED DUCT BURN OUT AND HIGH PWR RUN.

Part: CAP — FAILED (NR 3 TIRE) · airframe 39,077 hrs · 30,669 cycles

NR 3 MAIN TIRE CAP FAILED AFTER TAKEOFF FROM PVD, A/C DIVERTED TO BOSTON. REPLACED SAME AND REPAIRED SECONDARY DAMAGE.

Part: DOOR — LIGHTNING STRIKE (NLG) · airframe 36,439 hrs · 28,856 cycles

SUSPECT AIRCRAFT STRUCK BY LIGHTNING ON APPROACH. FOUND CORNER OF RIGHT NOSE GEAR FLYING DOOR WITH EVIDENCE OF LIGHTNING STRIKE. BURNISHED AREA PER SRM, OK FOR SERVICE.

Part: START VALVE — INOPERATIVE (NR 2 ENGINE) · airframe 35,124 hrs · 27,923 cycles

RT ENGINE START VALVE OPEN MESSAGE DURING CLIMB OUT FLT 250. REDUCED ENGINE TO IDLE PER POM, MESSAGE CLEARED. ILLUMINATED OIL TEMP RT ENGINE 125 DEG VERSUS 85 ON LT. ALL OTHER ENGINE PARAMETRS NORMAL. DIVERTED TO RDU. REPLACED START VALVE.

Part: UPLOCK SENSOR — MALFUNCTIONED (NLG) · airframe 34,747 hrs · 27,661 cycles

AFTER TAKEOFF, HAD ALL GEAR RETRACTED NOSE GEAR WAS SLOW BUT SHOWED NORMAL ( NO LIGHTS) AFTER APPROX 30 SECONDS RED NOSE LIGHT CAME ON. RAN CHECK LIST, CYCLED GEAR RED NOSE LIGHT REMAINED ON. NOISE LEVEL ALSO INDICATED THAT GEAR WAS NOT TOTALLY UP. GEAR WAS EXTENDED FOR NORMAL LANDING ( RTN BACK TO BOSTON ) INSPECTED NOSE GEAR AND DOORS NO TROUBLE FOUND. FOUND NOSE GEAR STRUT PROPERLY SERVICED. LUBED NOSE GEAR AS PRECATIONARY. REPLACED NOSE GEAR UP DOWN LOCK SENSORS PER MM. OPERATED NOSE GEAR UP/DOWN_SEVERAL CYCLES ALL INDICATIONS NORMAL.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 33,912 hrs · 27,025 cycles

DURING HMV CORROSION FOUND ON HORIZONTAL FLANGE OF C3 DOOR LOWER JAMB BEAM. PRIOR SRM REPAIR FOUND IN AREA. CORROSION REMOVED. FOUR FASTENER HOLES NOTED WITH LESS THAN 2D ED. ALL DAMAGE REMOVED AND REPAIRED IAW ERA 413057-14.

Part: SKIN — CORRODED (FUSELAGE) · airframe 33,912 hrs · 27,025 cycles

DURING HMV INSPECTION REVEALED CORROSION BETWEEN OUTER SKIN AND BEAR STRAP FOR THE C2 DOOR (FS 731 BETWEEN L29R AND L30). CORROSION REMOVED AND REPAIRED PER ERA 413053-14.

Part: OIL CAP — LEAKING (APU) · airframe 33,896 hrs · 27,011 cycles

AT T/O HAZE FORMED IN CABIN AND AFT SMOKE DETECTORS WENT OFF. ADJUSTED PACKS MANUALLY AND HAZE AND ODOR DISSIPATED. FOUND APU OIL CAP LEAKING CAUSING INLET CONTAMINATION. REPLACED OIL CAP, CLEANED APU INLET AND PERFORMED DUCT BURNOUT PROCEDURE PER M/M.

Part: BALLAST — DEFECTIVE (CABIN) · airframe 33,340 hrs · 26,588 cycles

EMERGENCY LIGHT B5-101 INOP. REPLACED BALLAST ASSY, CHECKS GOOD.

Part: ANGLE — CRACKED (KEEL BEAM)

KEEL BEAM AFT ANGLE CROSSOVER RIB CRACKED LT AND RT SIDES, FOUND DURING F-1 LTR CK. REPAIRED PER SRM 53-05 FIG 101.