N936DL

Part: ENGINE — MAKING METAL (RIGHT) · airframe 74,300 hrs · 56,001 cycles

DECLARED AN EMERGENCY DUE TO A RIGHT ENGINE OIL STRAINER CLOG MESSAGE. FOUND METAL IN THE OIL FILTER AND ON MCD. RT ENGINE CHANGED.

Part: LIGHT — INOPERATIVE (SEAT 19DEF) · airframe 74,255 hrs · 55,961 cycles

SEAT 19DEF EMERGENCY LIGHT INOPERATIVE. REPLACED THE LIGHT ASSY IAW AMM 33-53.

Part: SKIN — CORRODED (BS 750-759) · corrosion level 2 · airframe 72,492 hrs · 54,561 cycles

FUSELAGE SKIN AND INTERNAL DOUBLER BS 750 - 759, LONGERON 29L - 29R CORRODED. REPAIRED IAW ERA 555617-14 ISSUED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 71,932 hrs · 54,173 cycles

AFT OVERWING EXIT LIGHTS INOPERATIVE. TROUBLESHOT TO THE BATTERY PACK B5105. R & R BATTERY PACK IAW WDM 33-51.

Part: FUSE — FAILED (EMERGENCY LIGHTS) · airframe 71,932 hrs · 54,173 cycles

FIRST CLASS EMERGENCY LIGHTS INOPERATIVE. FOUND A BAD FUSE AT BATTERY CHARGER BASE. REPLACED THE FUSE IAW AMM 33-51. LIGHTS CHECKED OK.

Part: FUSE — BLOWN (BATTERY PACK) · airframe 71,602 hrs · 53,915 cycles

EMERGENCY EXIT LIGHTING IN FIRST CLASS INOP. REPLACED FUSE NR 1 ON RT F/C EMERGENCY LIGHT BATTERY PACK, NOW OPS NORMAL. OK FOR SERVICE.

Part: PAN — CRACKED (EMERGENCY EXIT) · airframe 70,622 hrs · 53,168 cycles

RIGHT AFT OVERWING EXIT DOOR PAN CRACKED AT FWD UPPER DOOR STOP. R & R DOOR IAW AMM 52-21-00. LEAK CHECKED GOOD.

Part: TAIL CONE — OUT OF RIG · airframe 70,622 hrs · 53,168 cycles

VAULT DOOR FORCE REQUIRED TO DROP TAIL CONE EXCEEDED 20 LBS TENSION. ADJUSTED TAIL CONE RIG IAW AMM 53-53-00 AND AMDS 5350-01077-0101.

Part: SKIN — CORRODED (BS 217) · corrosion level 2 · airframe 70,622 hrs · 53,168 cycles

POPPED RIVET AND PILLOWING SKIN CORROSION ON BELLY AT BS 217 STR 30. COMPLETED SEC I IAW ERA 546984-14, REV O. SECTION II MONITOR TO BE ACCOMPLISHED AT 8000 CYCLE INTERVALS ESTABLISHED ON LOG PAGE 2509314.

Part: SKIN — CRACKED (BS 1418) · airframe 70,622 hrs · 53,168 cycles

A/C SKIN HAS .3750" LONG CRACK EXTENDING INBD FROM FASTENER HOLE AT BS 1418, 1.5" OTBD OF L2R. ACCOMPLISHED SEC I IAW ERA 547264-14AD. SEC II MONITOR AMOC REQUIRED BY 25 MAY 17. ESTABLISHED ON LOG PAGE 2505537.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 70,622 hrs · 53,168 cycles

FWD CARGO DOOR FRAME UNDER ENTRY SCUFF PLATE CORRODED. DOOR FRAME OF SRM LIMITS. REMOVED AND REINSTALLED NEW LOWER PAN. REPAIRED IAW SRM 53-05, FIG 44A.

Part: ATTACH FITTING — BROKEN · airframe 70,622 hrs · 53,168 cycles

DUCT JOINT LOWER ATTACH TAB IS BROKEN, AFT OF LT GROUND BLOWER. WELDED TAB IAW ER/A 494638-14MA, REV B.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,386 hrs · 52,988 cycles

MAINTENANCE FOUND THE AFT CABIN EMERGENCY LIGHTS INOPERATIVE. BATTERY PACK WAS REPLACED AND THE LIGHTS CHECKED OK.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 69,429 hrs · 52,323 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 22D IN THE CABIN WAS INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 69,194 hrs · 52,141 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE VENTRAL STAIRWAY ARE VERY DIM. MAINTENANCE REPLACED THE BATTERY PACKS FOR THE NOTED LIGHTED AREAS AND THE OPS CHECK WAS GOOD.

Part: ANGLE — CRACKED (VERTICAL STAB) · airframe 68,739 hrs · 51,797 cycles

STABILIZER SUPPORT STRUCTURE LT ANGLE CRACKED. REMOVED ANGLE, REPLACEMENT ANGLE WAS FABRICATED FROM .090, 7075-0, HEAT TREATED TO T6 CONDITION. ON RO 702799 IAW DWG 9911808, DRILL AND TRIMMED ANGLE. TREATED AND PAINTED. INSTALLED NEW ANGLE ALL FASTENERS SECURED 628417, REF SRM 51-30-05.

Part: ANGLE — CRACKED (VERTICAL STAB) · airframe 68,739 hrs · 51,797 cycles

DURING JACKSCREW INSPECTION FOUND VERTICAL STABILIZER SUPPORT STRUCTURE RT ANGLE CRACKED. ANGLE WAS FABRICATED FROM .090 7075-0 AND HEAT TREATED TO T6 ON RO 702799 IAW DWG 9911808. TREATED AND PAINTED. INSTALLED NEW ANGLE ALL FASTNERS SECURED REF SRM 51-30-05.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 68,339 hrs · 51,526 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY PATHWAY LIGHTING FROM THE EXIT ROWS TO THE AFT CABIN WERE INOPERATIVE. MAINTENANCE REPLACED THE WIRE HARNESS DUE TO THE WIRES BEING RIPPED FROM THE PINS AT THE CONNECTOR AT AFT CABIN LAST ROW. THE SYSTEM HAS RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 67,109 hrs · 50,725 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS ABOVE THE AFT OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: RELEASE CABLE — OUT OF TOLERANCE (TAILCONE) · airframe 65,304 hrs · 49,401 cycles

DURING THE TAILCONE RELEASE SYS FUNCTIONAL CHECK, MAINTENANCE FOUND THAT THERE WAS EXCESSIVE TENSION ABOVE 25 LBS IN THE RELEASE CABLE SYSTEM. THE CABLE RELEASE MECHANISM WAS ADJUSTED AND THE SYSTEM WAS RIGGED TO PULL AT 19 LBS. THE RII STEPS WERE COMPLETED AND THE FOLLOW-UP CHECK WAS SUCCESSFUL.

Part: CATWALK — CRACKED (TAILCONE) · airframe 65,304 hrs · 49,401 cycles

MAINTENANCE DISCOVERED THAT THE TAILCONE CATWALK OVER THE VENTRAL STAIRWAY HAD STRUCTURAL CRACKS IN 3 PLACES. THIS IS CONSIDERED A DEFECT IN THE EMERGENCY ESCAPE SYSTEM AND COULD HAVE AN ADVERSE AFFECT ON THE EVACUATION ROUTE. THE CATWALK WAS REPAIRED IAW ER/A 525099-14 AND RIGGED TO MEET PUBLISHED SPECIFICATIONS.

Part: WIRE HARNESS — INOPERATIVE (EMERGENCY LIGHT) · airframe 64,542 hrs · 48,909 cycles

DURING LINE CHECK, NOTED THE SEAT MOUNTED EMERGENCY LIGHT AT 22DE INOPERATIVE. REPLACED HARNESS AT 22DE IAW AMM 33-52 AND OPERATION THEN CHECKED GOOD.

Part: CABIN PRESSURE — MALFUNCTIONED · airframe 64,373 hrs · 48,780 cycles

PERFORMED AN AIR TURN BACK DUE TO ACFT CABIN WOULD NOT PRESSURIZE DURING CLIMB OUT. FLOW LIGHT ILLUMINATED. NO FAULTS ON EITHER CABIN PRESSURE CONTROLLERS. OUTFLOW VALVE OPERATION CHECKED GOOD. PRESSURIZED ACFT ON EACH PACK WITH NO EXTERNAL LEAKS FOUND. NO DUCT LEAKS TAIL COMPARTMENT. CABIN PRESSURE LEAK DOWN GOOD. CABIN SAFETY RELIEF VALVE CHECK GOOD. SINGLE ENGINE SECOND SEGMENT CLIMB SWITCH AMM 21-31 CHECKED GOOD.

Part: BALLAST — BURNED (CABIN LIGHTS) · airframe 64,063 hrs · 48,546 cycles

DURING CLIMBOUT, AN ACRID ODOR BEGAN ISSUING FROM AIR CONDITIONING DUCTS. THE ENGINE ANTI-ICE WAS ON AND NORMAL PNEUMATIC CONFIGURATION. SELECTED A COLDER TEMP ON PACKS AND FUMES EVENTUALLY DISSIPATED. FOUND INOPERATIVE LIGHTING BALLAST AT ROW 33ABC. BALLAST HAD BURNED ELECTRICAL ODOR. REPLACED BALLAST IAW AMM 33-20. RAN AIR CONDITIONING PACKS. NO ODOR DETECTED. ACFT OK FOR SERVICE.

Part: WIRE — DISCONNECTED (EMERGENCY LIGHTS) · airframe 62,661 hrs · 47,514 cycles

DURING OVERNIGHT MX, THE SEAT MOUNTED EMERGENCY ESCAPE PATH LIGHT AT ROW 31 WAS FOUND TO BE INOPERATIVE. MX FOUND A WIRE PULLED FROM THE CONNECTOR AT ROW 31. THE CONNECTOR WAS REPLACED IAW STANDARD WIRING PRACTICES MANUAL CHAPTER 20. OPERATION CHECKED GOOD.

Part: WIRE HARNESS — INOPERATIVE (EMERGENCY LIGHTS) · airframe 62,232 hrs · 47,219 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY LIGHTING AT SEATS 22 AND 28DE INOPERATIVE. MX REPLACED WIRE HARNESS AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: SEAT TRACK — CORRODED (BS 484-493) · airframe 62,121 hrs · 47,144 cycles

CORROSION AND GOUGES ON MAIN CABIN SEAT TRACK AT LBL 45.5 FROM FS 484 TO 493. REMOVED SEAT TRACK. FABRICATED AND INSTALLED NEW SEAT TRACK IAW SRM 51-30-5 AND SRM 51-30-1.

Part: SEAT TRACK — CORRODED (BS 1226-1250) · airframe 62,121 hrs · 47,144 cycles

AFT CABIN, SEAT TRACK CORRODED AND GOUGED, BS 1226 TO 1250, RBL 22. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS, REPLACED SEAT TRACK IAW SRM 51-30-1.

Part: LONGERON — DAMAGED (BS 250 L2L) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON DOME NUT IN MAIN CABIN BS 250 L1. REPLACED LONGERON 2L SECTION AND SPLICE. REPLACED TWO ATTACH ANGLE FWD AND AFT DOME NUTS BETWEEN BS 227 AND 290. PERFORMED TCAS SELF TEST FOR UPPER TCAS ANTENNA. ALL WORK ACCOMPLISHED IAW SRM 51-30-5, 51-30-2, 51-10-4 AND AMM 34-46-02-201.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 62,121 hrs · 47,144 cycles

VERTICAL STAB TO FUSELAGE LT SKATE ANGLE AND FASTENERS ARE CRACKED STA 1474 CANT. CUT OUT CRACKED AREA AT VERTICAL STAB TO FUSELAGE LT SKATE ANGLE STA 1474 CANT. FABRICATED AND INSTALLED FILLER AND REPAIR ANGLE IAW SRM 53-05, FIG 23 THE CRACKED FASTENER WAS REPLACED WITHIN THE REPAIR ANGLE.

Part: DOUBLER — CORRODED (BS 594) · airframe 62,121 hrs · 47,144 cycles

FS 594 BETWEEN L30-L29R, POTABLE WATER BELLY DRAIN DOUBLER CORRODED. REMOVED CORROSION FROM DOUBLER FS 594 L30-29R MID CARGO IAW SRM 51-10-3. FOUND TO BE OUT OF LIMITS. FABRICATED, TREATED, AND INSTALLED POTABLE WATER FITTING HOSE AND INTERNAL RING DOUBLER ACCOMPLISHED ON TO 144/100.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,121 hrs · 47,144 cycles

DURING NDT INSPECTION, FWD SERVICE DOOR JAMB CORNER, FOUND ONE CRACK ON UPPER FWD CORNER ON OUTER LAYER OF SKIN. CUT OUT DAMAGE AREA AND REPAIRED IAW SRM 53-05, FIG 112, VIEW D AND ER/A 45.

Part: CHANNEL — DAMAGED (BS 218) · airframe 62,121 hrs · 47,144 cycles

E & E BAY BS 218, LONGERON 30 & 29 LT HAS DAMAGE TO LONGERON FLANGE ON BOTH SIDES OF LONGERON HAT CHANNEL. REMOVED DAMAGE ON E/E BAY STA 218, LONGERON 30 AND 29L ON LONGERON FLANGE IAW SRM 51-03, FIG 1. FOUND TO BE WITHIN LIMITS. HFEC INSP DETECTED 1 EA CRACK EMANATING FROM EDGE OF LT FLANGE IN BLENDED AREA OF LONGERON 30. NEW LONGERON SECTION STA 170-227 WAS CREATED, TREATED, AND INSTALLED IAW SRM 51-30-2 AND 51-30-5. TREATED, PRIMED, AND APPLIED TOPCOAT ON E/E BAY STA 218 L29L IAW SRM 51-10-3, PARA 11, 14, AND 21.

Part: SKIN — DAMAGED (BS 370) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON CUTOUT AND AROUND FASTENERS, FWD CARGO BAY BS 370 L26R. REPAIRED DAMAGED IAW SRM 51-70-4, PG 1-4.

Part: FAIRING — CRACKED (VERTICAL STAB) · airframe 62,121 hrs · 47,144 cycles

ON INSTALLATION OF VERTICAL STAB TIP FAIRING, FOUND A CRACK ON RT SIDE, EMINATING FROM A RADIUS OF UPPER SKIN. REMOVED FITTING ON RT STAB FAIRING BY ACCESS TO CRACK. NDT VERIFIED END OF CRACK, CHECK STOP DRILL, AND OPEN HOLES. FABRICATED, PRIMERED, TREATED, AND INSTALLED REPAIR DOUBLER AND SHIMS. ACCOMPLISHED WITH ER/A 509299-14, REV.

Part: BULKHEAD — CRACKED (MLG WW) · airframe 62,121 hrs · 47,144 cycles

FS 1007, RBL18, MLG WW AFT PRESSURE BULKHEAD AFT FACE (ACCESS FROM AFT CARGO BIN) SUSPECTED CRACK NEXT TO U-CHANNEL STIFFENER APPROX 2" FROM TOP OF BULKHEAD (064-69). COMPLIED WITH PRI 508338-14, REV 0, COMPLIED WITH PRI 508338-14 REV 1, COMPLIED WITH FINAL ER/A 508338-14 REV ORIGINAL. COMPLETED AND INSPECTED. ASSOCIATED ER/A 14-508338 ADDED FOR AC 0936.

Part: BULKHEAD — CRACKED (MLG WW) · airframe 62,121 hrs · 47,144 cycles

FS 1007, LBL 18 MLG WW AFT PRESSURE BULKHEAD AFT FACE (ACCESS FROM AFT CARGO BIN) SUSPECTED CRACK NEXT TO U CHANNEL STIFFENER APPROX 2 INCHES FROM TOP OF BULKHEAD (064-68) COMPLIED WITH FINAL ER/A 508338-14 REV ORIGINAL.

Part: SKIN — CORRODED (BS 726 L29L/R) · airframe 62,121 hrs · 47,144 cycles

FS 726, L29L-29R BELLY SKIN CORRODED. CORROSION RUNNING UNDER DOUBLER AND DOUBLER IS BULGING BETWEEN L30-L29R (064-56). COMPLIED WITH ER/A 508346-14 REV. ORIGINAL. COMPLETED AND INSPECTED. ASSOCIATED ER/A 14-508346 ADDED FOR AC 0936.

Part: SKIN — CORRODED (BS 594) · airframe 62,121 hrs · 47,144 cycles

ON REMOVAL OF POTABLE WATER BELLY DRAIN AT FS 594 BETWEEN L30-L29R, EXTERNAL FUSELAGE FOUND CORROSION ON DRAIN CUTOUT AND INTERNAL SKIN. COMPLIED WITH ER/A 508946-14 REV ORIGINAL. COMPLETED AND INSPECTED. ASSOCIATED ER/A 14-508946 ADDED FOR AC 0936.

Part: LONGERON — DAMAGED (BS 522-541) · airframe 62,121 hrs · 47,144 cycles

LONGERON 4R CRACKED AT ST 522 AND ST 541 UNDER SUPPORT MOUNT (204-111&112). REMOVED INTERCOSTAL BETWEEN STA 522-541 AT L4R. REMOVED DAMAGE LONGERON AT STA 513 TO 550 AT L4R. HFEC INSPECTION NO CRACKS AT CUTOUT. FABRICATED AND INSTALLED LONGERON AND SPLICES (2EA) AT STA 513-550 AND REINSTALLED INTERCOSTAL BETWEEN STA 522-541 L4R AND INSTALLED ID TAG IAW P/S 900-5-1-NO04. COMPLETED AND INSPECTED.

Part: SKIN — BULGED (BS 1207) · airframe 62,121 hrs · 47,144 cycles

APPROX 1IN DIAMETER BULGE IN FUSELAGE SKIN AT FS 1207, LONGERON 5L. JOB COMPLETED BY ER/A 508962-14 REV O PRI, AND ER/A 508962-14 REV ORIGINAL. COMPLETED AND INSPECTED. ASSOCIATED ER/A 14-508962 ADDED FOR AC 0936.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON CUSP WEB FLOOR PANEL, AFT LT CORNER ST 199L AT BL 44L (204-151). CUTOUT CORROSION AND REPAIRED CUSP WEB FLOOR PANEL STA 199 LBL44 IAW SRM 53-01, FIG 4, SHEET 4. COMPLETED AND INSPECTED.

Part: SKIN — CORRODED (BS 256) · airframe 62,121 hrs · 47,144 cycles

ANTENNA DOUBLER FILLER IN FWD CARGO COMP HAS CORROSION 4 INCHES FWD OF BS 256 AT L29L. REPLACED SECTION LOWER FUSELAGE SKIN BS 229 TO 304 BETWEEN L26R TO L26L IAW SRM 53-04, FIG 12C VIEW A. COMPLETED AND INSPECTED.

Part: CUSP WEB — CORRODED (BS 1211-1219) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON RT CUSP WEB ALONG FASTENERS FROM BS 1211 TO 1219. CORROSION FOUND TO BE BEYOND SERVICABLE LIMITS WITH 100 PERCENT MATERIAL LOSS ON RT CUSP WEB BS 1211-1219 IAW SRM 53-01, FIG 1. REMOVED CUSP WEB IAW SRM 51-30-1, 51-30-2 AND 51-30-5. FABRICATED, LOCATED, AND DRILLED CUSP WEB. INSTALLED CUSP WEB IAW PROCESS STANDARD 900-5-1 NR 4.

Part: SKIN — DAMAGED (RUDDER) · airframe 62,121 hrs · 47,144 cycles

LT SIDE OF RUDDER HAS LARGE AREAS OF PROTECTIVE FINISH PEELING UP WITH AREAS OF EXPOSED COMPOSITE SKIN. SANDED, REPAIRED, FLAME SPRAYED, & PAINTED RUDDER REF ER/A 092613-14MA AND SRM 51-30-3B, PG 1&3. REMOVED AND REINSTALLED 9EA HILOKS REF SRM 51-30-5 AND BALANCED RUDDER REF SRM 55-40-1D. INSPECTED.

Part: TAB — CORRODED (RT ELEVATOR) · airframe 62,121 hrs · 47,144 cycles

RT ELEVATOR ANTI-FLOAT TAB HAS SURFACE CORROSION REMOVED SALVAGED AREA (RT ELEVATOR ANTI-FLOAT TAB INBD END), REPAIRED SKIN SURFACE REF SRM 55-01, FIG 1, SHEET 1, ER/A 497176-14MA AND PERFORMED WEIGHT, BALANCE AT RT ELEVATOR ANTI-FLOAT TAB REF SRM 55-20-20, PARR 16 ASSOCIATED ER/A 14-497176 ADDED FOR AC 0936.

Part: CUSP WEB — CORRODED (BS 427-503) · airframe 62,121 hrs · 47,144 cycles

MAIN CABIN RT CUSP WEB FROM STA 427 TO STA 503 HAS FIVE AREAS OF CORROSION. REMOVED CUSP WEB REPLACED CUSP WEB IAW SRM 53-24-0D, FIG 802 D PG 804 AND 51-30-5, 51-30-2.

Part: CUSP WEB — CORRODED (BS 1174) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON RT CUSP WEB AT FS 1174. REMOVED RT CUSP WEB. FABRICATED REPLACEMENT CUSP WEB AND INSTALLED IAW SRM 51-30-1 AND 51-30-5.

Part: WINDOW FRAME — CRACKED (BS 900) · airframe 62,121 hrs · 47,144 cycles

WINDOW FRAME IS CRACKED STA 900 LT SIDE IN MAIN CABIN. TRIMMED OFF DAMAGED CORNER AND INSPECTED FOR CRACKS AND DAMAGED HOLE. NO INDICATION. NDT DETERMINED CRACK REMOVED, LOCATED, AND INSTALLED REPAIR ANGLE.

Part: SEAT TRACK — CORRODED (BS 1231) · airframe 62,121 hrs · 47,144 cycles

MAIN CABIN LT SIDE AT BS 1231 SEAT TRACK ABOVE CUSP WEB HAS SURFACE CORRSION. OUT OF LIMITS AND REPAIRED IAW SRM 53-05, FIG 4A, PG 18.

Part: SEAT TRACK — CORRODED (BS 218-826) · airframe 62,121 hrs · 47,144 cycles

MAIN CABIN, RT OTBD SEAT TRACK FROM BS 218 TO 826 HAS 16 EA AREAS OF CORROSION. REMOVED CORROSION ON RT OTBD SEAT TRACK. FOUND OUTBD SEAT TRACK OUT OF LIMITS. REPLACED OTBD SEAT TRACK FROM STA 218 TO STA 798 IAW SRM 51-30-1. INSTALLED OTBD SEAT TRACK RT SPLICES IAW SRM 53-05, FIG 4F SHEET 3 AND 51-30-1.

Part: LONGERON — CRACKED (BS 513-550) · airframe 62,121 hrs · 47,144 cycles

LONGERON IS CRACKED, BS 522 L4L. REMOVED DAMAGED AREA OF LONGERON ON BS 513-550 AT L4L. FABRICATED AND INSTALLED LONGERON IAW SRM 51-30-2 AND 51-30-5 PG 1.

Part: SKIN — DELAMINATED (RT WING) · airframe 62,121 hrs · 47,144 cycles

RT WING UPPER T/E PANEL IS DELAMINATED AT APPROX 414 (XRS). REMOVED DAMAGED SKIN AND CORE FROM RT WING FIXED L/E IAW SRM 51-70-2. FABRICATED CORE, BONDED CORE. FABRICATED INTERNAL DOUBLER, SKIN, AND REPAIR DOUBLER IAW SRM 51-70-2D AND ER/A 497176-14MA. APPLIED ALODINE, PRIMER, AND TOP COAT. APPLIED SEALANT TO REPAIR. COMPLETED & INSPECTED.

Part: CUSP WEB — CORRODED (BS 788-807) · airframe 62,121 hrs · 47,144 cycles

MAIN CABIN RT CUSP WEB FROM BS 788 TO STA 807 HAS THREE AREA OF CORROSION. FOUND CORROSION TO BE OUT OF LIMITS AT 100 PERCENT MATERIAL LOSS. REMOVED CUSP WEB BS 788-807 RT. INSTALLED CUSP WEB IAW SRM 51-30-1, 51-30-2, 51-30-5.

Part: CUSP WEB — CORRODED (BS 311) · airframe 62,121 hrs · 47,144 cycles

CUSP WEB AT STA 311 LBL 59 HAS ONE SPOT OF CORROSION. REMOVED FRAME FOOT FITTING AT BS 313 IAW SRM 51-30-1,51-30-5 CUT OUT CORROSION IAW SRM 53-05 FIG.131A-10. AFTER CUT OUT NDT FOUND NO CRACKS EXIST. FABRICATED AND INSTALLED RING DOUBLER, FILLER, DOUBLER, AND FRAME FOOT FITTING IAW SRM 53-05.

Part: SKIN — DENTED (BS 268) · airframe 62,121 hrs · 47,144 cycles

MULTIPLE DENTS IN SMALL AREA LT FWD FUSELAGE AT APPROX BS 268 L19L. PERFORMED HFEC INSPECTION, NO CRACKS NOTED AT REFORMED AREA. FABRICATED AND INSTALLED INTERNAL DOUBLER IAW REPAIRED IAW SRM 53-04-1, PARA 7C(5)(9)1).

Part: FLOORBEAM — CORRODED (BS 1338) · airframe 62,121 hrs · 47,144 cycles

RT AFT LAVATORY FLOORBEAM HAS CORROSION BS 1338 FROM L18R TO CENTER FLOOR PANEL SUPPORT APPROX RBL 24, TOP & LWR SURFACE. REPLACED REPAIR STRAP BS 1338 RBL 24-41 IAW ER/A 458174-14. ORIG. MATERIAL .125" DAMAGE DIM. L-3.8" W-1.0" D-.023".

Part: FITTING — CRACKED (WING TO BODY) · airframe 62,121 hrs · 47,144 cycles

RT WING TO FUSELAGE FITTING IS CRACKED AT APPROX 993 BS 86. VERIFIED 1 EA CRACK COMING FROM FASTENERS, CUT OUT DAMAGE AREA OF RT WING IAW ER/A 38516-14MA REV A. INSPECTED NDT ALONG EDGE OF CUT OUT AREA NO CRACK NOTED AT OPEN FASTENER HOLE. FABRICATED 1EA REPAIR ANGLE. INSTALLED 2EA REPAIR ANGLES AND FILLER AT RT WING IAW ER/A 385816-14 MA.

Part: CUSP WEB — CORRODED (BS 1079) · airframe 62,121 hrs · 47,144 cycles

CORROSION ON RT CUSP WEB AT FS 1079. REPLACED CUSP WEB FS 1022-1098 RT IAW SRM 51-30-2 AND 51-30-5, SRM 51-30-1. ORIG. MAT .020 DAMAGE DIM. L=ALL W=ALL D=ALL COMPLETED.

Part: PANEL — CHAFED · airframe 62,121 hrs · 47,144 cycles

FWD CARGO BARRIER PANEL IS HEAVILY CHAFED ON A PRIOR REPAIR (DP-34) REPLACED REPAIR DOUBLER ON FWD CARGO BARRIER PANEL IAW ER/A 094625-14MA, REV C.

Part: LONGERON — CRACKED (BS 160) · airframe 62,121 hrs · 47,144 cycles

LONGERON 3L IS CRACKED ABOVE EPC IN MAIN CABIN BS 160. HFEC, VERIFIED CRACK AT LONGERON. REMOVED FASTENERS ON SPLICE FOR FOM AT BS 148 TO 160 IAW SRM. REMOVED SECTION DAMAGED LONGERON ABOVE EPC MAIN CABIN BETWEEN BS 148 TO 170 IAW SRM 51-30-5 PG 12. HFEC INSPECTION. NO CRACKS NOTED AT CUTOUT. FABRICATED SECTION LONGERON AND SPLICE IAW SRM. INSTALLED REPAIR PARTS AND REINSTALLED FORWARD SPLICE.

Part: CUSP WEB — CRACKED (BS 220) · airframe 62,121 hrs · 47,144 cycles

CUSP WEB CRACKED AT BS 220, RBL 54. REPAIRED CRACKED CUSP WEB IAW ERA 398191-14MA.

Part: VANE — GOUGED (RT WING TE FLAP) · airframe 62,121 hrs · 47,144 cycles

RIGHT WING, OTBD FLAP VANE NR 5, HAS SOME DEEP GOUGING ON THE UPPER SURFACE. REPAIRED RT WING OTBD NR 5 FLAP VANE BY REMOVING DAMAGE SKIN, FABRICATED FILLER AND DOUBLER, AND BONDED FILLER AND DOUBLER AT 225 DEGREES-240 DEGREES FOR 90 MINUTES IAW SRM 51-70-2D, PAR 18 AND ER/A 497176-14MA, REV ORIGINAL. ASSOCIATED ER/A 14-497176 ADDED FOR AC 0936.

Part: SKIN — CRACKED (BS 1437) · airframe 62,121 hrs · 47,144 cycles

FUSELAGE SKIN HAS POPPED FASTENER AND OTHER WORKING STA 1437 BETWEEN LONGERON 2L AND 5L WITH CRACKS IN SKIN. REPLACED POPPED FASTENER AND OTHER WORKING STA 1437 BETWEEN L2L-L5L, 2 CRACKS FOUND ON FUSELAGE SKIN STA 1437 BETWEEN L3L-L4L AND BETWEEN L4L-L5L, CUTOUT FUSELAGE SKIN TO REMOVE CRACKS AT STA 1437 BETWEEN L3L-L4L AND BETWEEN L4L-L5L AND REPAIRED FUSELAGE SKIN WITH A REPAIR DOUBLER AND 2 EA FILLERS AT STA 1437 BETWEEN L2L-L5L IAW SRM 53-04.

Part: SUPPORT — CRACKED (BS 1076) · airframe 62,121 hrs · 47,144 cycles

AFT CARGO SLANT PANEL SUPPORT, RT SIDE AT STA 1076 IS CRACKED. REPAIRED AFT CARGO SLANT PANEL SUPPORT IAW ER/A 413029-17MA, REV C.

Part: LONGERON — CRACKED (BS 160 L3L) · airframe 62,121 hrs · 47,144 cycles

LONGERON 3L IS CRACKED ABOVE EPC IN MAIN CABIN STA 160. HFEC IAW NDTSP-M 06-10-01.001 VERIFIED CRACK AT LONGERON ASSET 11-545 CAL DUE 03-23-13. REMOVED SECTION LONGERON DAMAGE ABOVE EPC MAIN CABIN BETWEEN STA 148 TO 170 IAW SRM 53-02, FIG 18. HFEC INSPECTION, NO CRACKS NOTED AT CUT-OUT. FABRICATED SECTION LONGERON AND SPLICE AND INSTALLED REPAIR PARTS AND REINSTALLED FWD SPLICE AT STA 148 TO 170 IAW SRM 53-02, FIG 18 INSTALLED ID TAG IAW PS 900-5-1, NR 4 COMPLETED.

Part: FLOOR SUPPORT — CORRODED · airframe 62,121 hrs · 47,144 cycles

MAIN CABIN FLOOR SUPPORT CHANNEL, AT STA 965 RBL 10, IS CORRODED. REMOVED CORROSION FROM FLOOR PANEL AND REMAINING MATERIAL FOUND OUT OF LIMITS IAW SRM 53-01, FIG 1. INSTALLED REPLACEMENT FLOOR PANEL SUPPORT AT STA 965, RBL 10 IAW SRM 51-30-5.

Part: LONGERON — CORRODED (BS 1312) · airframe 62,121 hrs · 47,144 cycles

AFT CARGO LONGERON 29R HAS CORROSION IN CHANNEL AT 2EA FASTENERS, STA 1312 (APPX) (50-76). REMOVED CORROSION AFT CARGO LONGERON 29R STA 1312 & REPAIRED IAW SRM 53-02 FIG 19, 51-10-3, 51-20-0, 51-30-5. ORIG MAT .125 DAMAGE DIM. L=2.0" W=1.0" D=.029.

Part: SKIN — CRACKED (BS 1439) · airframe 62,121 hrs · 47,144 cycles

FUSELAGE SKIN HAS CRACKED AND WORKING FASTENERS STA 1439 BETWEEN LONGERON 2R AND 4R. HFEC INSP. VERIFIED (2EA) CRACKS APPROX 1" LONG BETWEEN L3R AND L4R, CUT OUT 2 DAMAGE AREAS. CUT OUT DIMENSIONS IS 2", NDT CHECK FOR CRACKS AND OPEN HOLE, FABRICATED DOUBLER AND 2EA FILLERS. INSTALLED REPAIR DOUBLER AND 2EA FILLERS IAW SRM 53-04, FIG 27, PG 143.

Part: STRUCTURE — BINDING (TAIL CONE) · airframe 61,789 hrs · 46,896 cycles

THE FIRST OFFICER DISCOVERED THAT THE TAILCONE CATWALK OVER THE VENTRAL STAIRWAY WAS BINDING DURING OPERATION. THIS IS CONSIDERED A DEFECT IN THE EMERGENCY ESCAPE SYSTEM AND COULD HAVE AN ADVERSE AFFECT ON THE EVACUATION ROUTE. THE MOVEABLE CEILING (CATWALK) WAS ADJUSTED SO IT WOULD NO LONGER BIND DURING OPERATION AND RIGGED TO MEET PUBLISHED SPECIFICATIONS.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,643 hrs · 46,797 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT ALL OF THE EMERGENCY PATHWAY LIGHTS FOR THE CATWALK IN THE TAIL COMPARTMENT WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: UNKNOWN — LEAKING (CARGO BAY) · airframe 59,934 hrs · 45,657 cycles

WRITTEN IN REFERENCE TO NRC155 FOR "FOUND LAV LEAK IN AFT CARGO AT AFT RT SIDE. AFTER FURTHER INVESTIGATION, FOUND AGGRESIVE LEAKS AS WELL AS DAMAGE TO THE AFT CARGO COMPARTMENT. INSPECTION PRODUCE OVER 200 CARDS PERTAINING TO THE AFT CARGO. REPAIRS WERE WORKED PER SRM 53-01. NRC'S TO INCLUDE CARDS 105-107, 209-212, 220, 227-238, 240-242, 244-304, 312, 315-334, 372, 414, 416-432, 438-439, 447-449, 469-470, 472, 488, 494-498, 520, 523-252, 534-536, 551.

Part: SKIN — CORRODED (FUSELAGE) · airframe 59,934 hrs · 45,657 cycles

DURING PSV IN MSP FOUND CORROSION ON FUSELAGE SKIN AND ON INTERNAL DOUBLER AT STA 750 BETWEEN L-30 AND L-29R AND AT STA 759 AT L-30. REPAIRED ON NRC 467 AND 480 RESPECTIVLY. CUT OUT DAMAGE AND INSTALLED FILLER, DOUBLER, AND TRIPLER PER ERA 497861-14.

Part: MOUNT — CORRODED (L1 DOOR) · airframe 59,934 hrs · 45,657 cycles

DURING PSV VISIT, FOUND CORROSION ON AFT GIRT BAR FITTING MOUNT ANGLE INSIDE DOOR 1L AT STA 195. INSTALLED NEW MOUNT ANGLE PER SRM 57-01.

Part: SKATE ANGLE — CRACKED (FUSELAGE) · airframe 59,934 hrs · 45,657 cycles

RT SKATE ANGLE HAS CRACK EMINATING FROM FASTENER HOLE STA 1474 AFT FUSELAGE AREA. REPAIRED PER ERA498016-14 REF.

Part: SKIN — CORRODED (FUSELAGE) · airframe 59,934 hrs · 45,657 cycles

DURING PSV IN MSP MTC FOUND THE FUSELAGE SKIN AND INTERNAL DOUBLER WITH CORROSION DAMAGE. THE 5936004-7 INTERNAL DOUBLER IS MADE FROM 0.032 7075-T6 CLAD. THE -19 FUSELAGE SKIN IS MADE FROM .063 2024-T3 CLAD ALUMINUM. THE FINAL TRIM OUT SIZE FOR BOTH THE INTERNAL DOUBLER AND FUSELAGE SKIN WAS 7.2 INCHES CIRCUMFERENTIALLY AND 4.3 INCHES LONGITUDINALLY. THE SKIN TRIM OUT AT STA 759 MEASURED 1,75 FWD/AFT X 6.2 CIRCUMFERENTIALLY. REPAIRED PER EA 497861-14.

Part: SEAT TRACK — DAMAGED (BS 221) · airframe 59,934 hrs · 45,657 cycles

FWD LEFT OUTBOARD SEAT TRACK DAMAGED BS 221, LBL44. REPAIRED IAW ER/A 497684-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,934 hrs · 45,657 cycles

FUSELAGE SKIN CRACK STA 1478 BETWEEN L2 L32. REMOVED DAMAGE FABRICATED AND INSTALLED DOUBLER PER MD88 SRM 53-04 FIG 12B. REQUIRES REPETITIVE INSPECTION 15000 LANDINGS AND PERMANENT REPAIR 20000 LANDINGS.

Part: CONNECTOR — INOPERATIVE (EMERGENCY LIGHT) · airframe 58,101 hrs · 44,374 cycles

DURING LINE CHECK, MAINTENANCE FOUND EMERGENCY EXIT LIGHT AT ROW 13 D/E INOPERATIVE. MAINTENANCE REPLACED HARNESS CONNECTOR. OPERATIONALLY CHECKS NORMAL.

Part: SPLICE — WORN (VERTICAL STAB) · airframe 56,169 hrs · 43,087 cycles

REMOVABLE L/E OF VERTICAL SCREW ATTACH HOLES AND COUNTERSINKS WORN UPPER SPLICE REPAIRED ON ERA 482407-14, NR 128.

Part: WIRE HARNESS — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,048 hrs · 43,016 cycles

MX FOUND THE EMERGENCY LIGHT AT SEAT 14DE TO BE INOPERATIVE. MX REPLACED THE WIRE HARNESS. AN OPS CHECK WAS NORMAL AND THE ACFT WAS RETURNED TO SERVICE.

Part: MECHANISM — OUT OF ADJUST (COCKPIT WINDOW) · airframe 54,485 hrs · 41,971 cycles

CABIN UNABLE TO PRESSURIZE F/O WINDOW PHYSICALLY CLOSED BUT WIND NOISE IS DEAFENING. RESET F/O`S WINDOW. PRESS TO 5 PSI DIF. NO LEAKS NOTED. A/C PRESS NORMAL 456492. INSP F/O`S WINDOW AND FOUND TOP LOCK MECHANISM NOT FULLY ENGAGING ALL THE TIME. ADJ SAME. WINDOW NOW WORKS EVERY TIME. PRESS A/C TO 6 PSI. NO LEAKS AT WINDOW, A/C OK FOR SERVICE.

Part: CHARGER — BURNED (FWD E&E) · airframe 49,204 hrs · 38,429 cycles

DURING PREFLIGHT, BATTERY CHARGER C/B POPPED WITH ODOR/SMOKE IN COCKPIT/CABIN. BATTERY CHARGER REPLACED. UPON TEAR DOWN IN THE SHOP BATTERY CHARGER WAS SEVERELY CHARRED INTERNALLY. THERE WAS SUFFICIENT HEAT TO DISTORT THE ALUMINUM COVER.

Part: CONTROL QUADRANT — BROKEN (RUDDER PEDAL) · airframe 48,533 hrs · 37,972 cycles

CAPTAINS RUDDER PEDALS WON`T ADJUST. FOUND RUDDER PEDAL ADJUSTMENT QUADRANT ASSY BROKEN. ALSO FOUND RUDDER PEDAL ADJUSTMENT CABLE BROKEN. REMOVED AND INSTALLED NEW QUADRANT AND NEW RUDDER PEDAL CABLE. ADJ CABLE. ADJUSTED AND OPERATED CABLE AND QUADRANT. ALL CHECKS NORMAL. NO RII REQ. QUADRANT P/N 4616065BN.

Part: UNKNOWN — UNKNOWN (FUEL SYSTEM) · airframe 48,150 hrs · 37,746 cycles

AIRCRAFT DEVELOPED 2000LB IMBALANCE HALF WAY THRU FLIGHT. (RIGHT WING LOW) ACCOMPLISHED FUEL LEAK CHECKLIST. FUEL CONT TO DECLINE TO 1900 LBS ON RT GAUGE, WHEN RIGHT ENGINE FAILED. FUEL AT SHUTDOWN - 4200LT, 2000RT, 6300 TOTAL. ENGINE FLAMED OUT DESCENDING THRU 10000FT. NO RESTART ATTEMPTED. ENGINE SHUTDOWN CHECKLIST ACCOMPLISHED. LANDED APPROX 8 MINUTES AFTER FLAMEOUT. REPLACED COMP PROBE, REPLACED NR 6 PROBE. REPLACED JUNCTION PROBE. PERFORMED A FUEL QTY TEST WITH DIP STICK PER MM AND FUELING MANUAL AND CHECKED FUEL QTY SYS PER MM 28-40-00-101-1 AND ALL COMPONENTS CHECKED GOOD.

Part: CONNECTOR — BROKEN (CABIN) · airframe 47,290 hrs · 37,217 cycles

PAX SEAT 31D EMERG LIGHTS INOP. FOUND BROKEN CONNECTOR UNDER SEAT 36ED AND 27ED. REPAIRED WIRING REPLACED BATTERY PACK AND CHARGER, ALL EMERG LIGHTS NOW OPS NORM.

Part: FRAME — GOUGED (BS 522) · airframe 47,145 hrs · 37,120 cycles

DURING CURRENT HMV, THE FS 522 FRAME WAS FOUND GOUGED IN FIVE LOCATIONS. DUE TO THIS, A BOEING APPROVED FRAME SPLICE IS INSTALLED FROM THE PRODUCTION SPLICE AT 18R TO THE CUTLINE BEWTEEN L-26R AND L-27R, PER ERA 458177-14

Part: SKIN PANEL — DENTED (FS 232-241) · airframe 47,145 hrs · 37,120 cycles

DURING CURRENT HMV THE FUSELAGE SKIN WAS FOUND DENTED AT TWO LOCATIONS, FS 232 AND 241 BETWEEN L18L AND L19L. THE AREA THAT IS DAMAGED WILL BE CUTOUT, AND BOTH AREAS WILL BE REPAIRED WITH ONE EXTERNAL REPAIR DOUBLER PER BOEING GUIDELINES, SEE ERA 458176-14

Part: FLOORBEAM — CORRODED (BS 1338 RBL 30) · airframe 47,145 hrs · 37,120 cycles

DURING CURRENT HMV VISIT , CORROSION WAS NOTED ON THE UPPER CAP OF THE FS 1338 FLOORBEAM NEAR RBL 30. DUE TO THIS, THE UPPER CAP WAS CUT AND A NEW SECTION SPLICED IN PER BOEING INSTRUCTIONS, SEE ERA 457174-14.

Part: SKIN PANEL — CORRODED (FS 610-640 L28L) · airframe 47,145 hrs · 37,120 cycles

DURING CURRENT HMV, CORROSION DAMAGE WAS FOUND IN THE SAME AREA AS EXISTING REPAIR INSTALLED PER 091432-14. DUE TO THIS, THE EXISTING REPAIR WAS REMOVED, THE CORROSION WAS BLENDED, AND REPAIR PARTS INSTALLED PER BOEING INSTRUCTIONS, ERA 458175-14

Part: SKIN PANEL — CORRODED (FS 389 L28L) · airframe 47,145 hrs · 37,120 cycles

DURING CURRENT HMV, CORROSION DAMAGE WAS FOUND ON THE INTERNAL SKIN SURFACES COMMON TO PREVIOUSLY INSTALLED EXTERNAL SKIN REPAIR PER ERA 270282-14. A NEW REPAIR PROVIDED BY BOEING WILL BE INSTALLED PER ERA 457390-14.

Part: FRAME — CRACKED (BS 1174 L4-5L) · airframe 47,145 hrs · 37,120 cycles

FRAME AT STA 1174 BETWEEN LONGERON 4 AND 5 LT HAS A CRACK. FABRICATED AND INSTALLED REPAIR IAW MD-88 SRM 53-03 FIG 4.

Part: SUPPORT FITTING — CORRODED (MLG) · airframe 47,145 hrs · 37,120 cycles

THE LT AND RT MLG RETRACT ACTUATOR SUPPORT FITTING BORE DIAMETERS WERE FOUND CORRODED. THE HOLES WERE OVERSIZED TO REMOVE THE CORROSION AND OVERSIZED BUSHINGS WERE INSTALLED.

Part: LINE — LEAKING (THRUST REVERSER) · airframe 44,258 hrs · 35,028 cycles

STRONG BURNING ODOR DURING TAXI, REPLACED LEAKING LINE AT LEFT THRUST REVERSER CONTROL VALVE. PERFORMED DUCT BURNOUT.

Part: SKIN — CORRODED (FUSELAGE) · airframe 41,400 hrs · 32,943 cycles

FUSELAGE SKIN FOUND BULGED/CORRODED AT STA 625 BETWEEN LONGERONS 29R AND 30. DAMAGE CUT OUT AND EXTERNAL DOUBLER/TRIPLER INSTALLED PER ERA 091432-14 REV A.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 37,415 hrs · 30,163 cycles

LT HYD QTY DECREASED FROM 11 T0 5 QTS AT FL 280. FOUND ELEVATOR PRESSURE TUBE WORN THROUGH AT CLAMP. LOCATED IN TAIL COMPARTMENT LT SIDE. REPLACED LINE LEAK CHECKS OK

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 31,869 hrs · 26,076 cycles

AFT CABIN EMERGENCY FLASHLIGHT INOP. REPLACED SAME.

Part: MICROPHONE — FAILED (COCKPIT O2 MASK) · airframe 31,801 hrs · 26,023 cycles

F/O OXYGEN MASK MICROPHONE IS INOP. REPLACED O2 MASK AND STORAGE BOX ASSY.

Part: THROTTLE — BINDING (NR 1 ENGINE)

AFTER T/O, LEVELING AT 6,000 FEET, LEFT THROTTLE WOULD NOT MOVE BACK. STUCK AT F/F APPROX 6000 PPH. MOVING LEFT THROTTLE TOOK EXCESSIVE FORCE. COULD SEE LEFT FUEL CONTROL LEVER MOVING AS ATTEMPT WAS MADE TO MOVE LEFT THROTTLE. RETURNED CVG UNEVENTFULL LANDING. TURNING FINAL APPROACH, LEFT THROTTLE STARTED WORKING NORMALLY. THROTTLE AND FUEL CONTROL AT ENGINE, FUEL CONT CROSSOVER SHAFT-TELEFLEX CK NORMAL. RECONNECTED THROTTLE AND FUEL CONTROL. RAN ENGINE TO TAKEOFF PWR, NO TROUBLE FOUND. OK FOR SERVICE.

Part: HOSE — FAILED (RT HYD SYS)

IN FLT PASSING APPROX 16,000 FT, GOT RT HYD PRESS LOW MESSAGE. HYD PRESS WAS 0 AND HYD QTY READ 6. RAN POM CHECKLIST (17-104 AND 17-106) HYD PRESS LOW AND HYD QTY DECREASING. TURNED OFF THE RIGHT HYD PUMP AND HAD TO USE ALT GEAR EXTEND PROCEDURE. WITH RT ENG DRY SPIN FOUND RT HYD PRESS LINE LEAKING IN TAIL SECTION TO POWER MODULE. REMOVED AND REPLACED RT ENG HYD PRESS LINE. LEAK CHECKED OK.

Part: VALVE — LEAKING (NLG STRUT)

AFTER T/O, NOSE GEAR FAILED TO RETRACT, RED IND LIGHT ON. IND PIN WAS RETRACTED, NOISE FROM NOSE GEAR AREA. NOSE STRUT FOUND FLAT. REPLACED SCHRADER VALVE AND SERVICED STRUT.

Part: SKIN — CORRODED (BS 245)

THE FUSELAGE SKIN WAS FOUND CORRODED AROUND THE TCAS ANTENNA CUTOUT BETWEEN FS 237 AND 256 OVER STRINGERS 29L AND 30. THE TCAS STRUCTURE WAS REMOVED AND THE SKIN CUT OUT OVER A 17.5 X 14.5 AREA. AN EXTERNAL ALUMINUM REPAIR DOUBLER AND INTERNAL FINGER DOUBLERS WERE INSTALLED TO REPAIR THE CUT OUT PER ER/A 365510-14. THE TCAS STRUCTURE WAS RE-INSTALLED AFTER THE REPAIR.

Part: LENS — MISSING (CABIN)

EMERG TRACK LIGHT LIGHT MISSING LENS AT 15C. REPLACED TRACK ASSY AND LENS SYS TEST OK.

Part: BATTERY CHARGER — INOPERATIVE (CABIN)

EMERGENCY TRACK LIGHT 3D INOP. REPLACED BATTERY CHARGER.

Part: AIRSPEED IND — FAILED (LT COCKPIT)

ABORTED TAKEOFF AT 70 KNOTS DUE TO CAPTS AIRSPEED INDICATOR FAILURE. REPLACED CAPTS AIRSPEED INDICATOR WITH PART BORROWED\FROM AMERICAN. ALSO, REPLACED NR 1 CADC, SYS NOW TESTS NORMAL.

Part: LIGHT TRACK — CRACKED (CABIN)

EMERGENCY LIGHT TRACK CRACKED.

Part: EEL LENS — MISSING (CABIN)

FLOOR TRACK AT SEAT 38D, BULB AND COVER MISSING. REPLACED FLOOR TRACK LIGHT, LENS AND OPS NORMAL.

Part: SKIN — DENTED (FS 440-488)

A 7 INCH WIDE BY 48 INCH LONG BY .1250 DEEP DENT WAS FOUND IN THE FUSELAGE SKIN FROM FS 440 TO FS 488 BETWEEN STR 19R AND STR 20R. NEITHER FRAMES NOR STRINGERS AT THE SUBJECT AREA WAS DAMAGED. THE DAMAGED SKIN IS M/F FROM .050 2024-T3 CLAD. ACCOMPLISHED REPAIRS PER DL ERA 271142-14.

Part: HANDLE CUTOUT — WORN (C-1 DOOR)

DURING HMV FOUND C-1 DOOR HANDLE CUT-OUT WORN AND BENT ALONG EDGE. REPAIRED PER SRM 52-05 FIG 30.

Part: STRINGER — CRACKED (FS 1418)

AT HMV, FOUND AFT UPPER FUSELAGE STRINGER 2L CRACKED AT FS 1418. REPAIRED PER SRM 53-02 PG 6 FIG 5.

Part: STRINGER — CRACKED (FS 1418)

AT HMV, FOUND AFT UPPER FUSELAGE STRINGER 2R CRACKED AT FS 1418. REPAIRED PER SRM 53-02 PG 6 FIG 5.

Part: SUPPORT — CRACKED (BS 1510)

AT HMV, FOUND LEFT AND RIGHT SIDE TAIL COMPARTMENT LOUVER VENT SUPPORT STRUCTRUE CRACKED AT APPROXIMATE FS 1510. REPAIRED PER SRM 53-05 FIG 66.

Part: SEAT TRACK — CORRODED (FS 1190)

AT HMV, LT INBD SEAT TRACK AT FS 1190 IS CORRODED AFT GALLEY INBD AFT MOUNT. CLEANED CORROSION, CUT OUT CORRODED SEAT TRACK FABRICATED REPAIR SPLICE AND ANGLES AND INST NEW SECTION OF SEAT TRACK PER SRM 53-05 FIG 4F.

Part: DOOR FRAME — CORRODED (CARGO DR AREA)

AT HMV, AFT B/B FUSELAGE LOWER DOOR FRAME CORRODED 6 INCHES FROM FWD LOWER CORNER TO 37 INCHES AFT JUST FWD OF 2ND LOWER DOOR STOP. CLEANED CORROSION FOUND OUT OF LIMITS PER SRM 53-05 PAGE 173. INSTALLED REPAIR DOUBLER PER SRM 53-05 FIG 63.

Part: PANEL — CRACKED (UPR WING TE)

DURING HMV, FOUND PANEL CRACKED WITH SMALL DENT IN UPPER WING T/E PANEL 10 INCHES OB OF OB END OF OB SPOILER. REPAIRED PER SRM 57-04 FIG 3 PAGE 7 AND 8.

Part: SKIN — DENTED (C 2 DOOR)

C2 DOOR HANDLE CUTOUT SKIN IS DENTED AND GOUGED. INSTALLED REPAIR DOUBLER PER SRM 52-05 FIG 30.

Part: SKIN — DENTED (FS 218)

FUSELAGE DENTED JUST AFT OF L1 DOOR ABOVE THE FLOOR LINE AT STA 218. INSTALLED REPAIR PER SRM 53-04 FIG 12B. FOUND AT HMV.

Part: SEAT TRACK — CORRODED (FWD COAT CLOSET)

AT HMV, SEAT TRACK IS CORRODED AT FWD COAT CLOSET AFT OUT BD MOUNT. REPAIRED PER ERA 270258-14.

Part: SKIN — DENTED (FUS BELLEY)

DURING HMV FOUND SKIN DENTED APPROX 12 INCHES LONG AT LOWER BELLY SKIN JUST BELOW C-1 DOOR CUT-OUT. REPAIRED PER ERA 270282-14.

Part: SKIN — DELAMINATED (TE FLAP VANE)

I/B FLAP O/B VANE HAD SHARP DENT ON LOWER I/B SIDE AT MOUNT POINT. MADE BONDED REPAIR PER MD 88 SRM 57-04, DAMAGE FOUND AT HMV.