N72821

Part: BEAM — CORRODED (BULKHEAD) · airframe 53,397 hrs · 25,691 cycles

INSPECTION FOUND STA 110 BULKHEAD BEAM WEB CORRODED AT MAIN BATTERY GROUND STUD HOLE. THE BEAM WEB WAS REPAIRED IAW ECRA 5310-04387.

Part: SEAT TRACK — CORRODED (STA 1079-1136) · airframe 50,556 hrs · 24,224 cycles

INSPECTION FOUND L/H CENTER SEAT TRACK CORRODED BETWEEN STA 1079 AND 1136. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,556 hrs · 24,224 cycles

INSPECTION FOUND E&E COMPARTMENT SUBFLOOR CORRODED AT VENTRAL STAIR MECHANISM, STA 162-168, X = 54.000. A DOUBLER WAS INSTALLED IAW SRM 51-70-4.

Part: SEAT TRACK — CORRODED (STA 228) · airframe 50,556 hrs · 24,224 cycles

INSPECTION FOUND R/H CENTER AND R/H I/B SEAT TRACKS CORRODED AT STA 228. THE CORRODED SEAT TRACK SECTIONS WERE REMOVED AND NEW SECTIONS WERE SPLICED IN IAW SRM 53-05, FIGURE 4F AND 51-30-0.

Part: SKIN — DENTED (STA 435-510) · airframe 48,039 hrs · 22,916 cycles

THE R/H FUSELAGE SKIN WAS DENTED BETWEEN FORWARD CARGO DOOR AND RIGHT TURN OFF LIGHT AT STA 435-510 BETWEEN LONGERONS 20R AND 21R. A FLUSH SKIN PANEL REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 12C.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A .25 INCH CRACK IN TAIL COMPARTMENT LEFT VENTRAL BOX SUPPORT ANGLE AT CANTED FRAME STA 1474. THE SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-05.

Part: LONGERON — CRACKED (STA 1418) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A 10" CRACK AT END OF LONGERON 2L AT STA 1418. A HAT SECTION REPAIR SPLICE WAS INSTALLED IAW SRM 53-02, FIGURE 18.

Part: FITTING — CRACKED (FUSELAGE) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A 2 INCH CRACK IN TAIL COMPARTMENT SUPPORT FITTING BETWEEN CANTED FRAMES 1463 AND 1485 AT LOWER AFT SIDE. THE SUPPORT FITTING WAS REMOVED AND A NEW FITTING WAS INSTALLED IAW SRM 51-10-4.

Part: FRAME — CRACKED (STA 1474) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A 2" CRACK IN TAIL COMPARTMENT CANTED FRAME AT STA 1474, LEFT LOWER SIDE, BY VENT BOX DRAIN HOSE. REPAIRED IAW ECRA 5310-04173.

Part: PLATE — CORRODED (HORIZ STAB) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND HORIZONTAL STABILIZER PIVOT PLATES CORRODED AT RIGHT O/B AND RIGHT I/B LUG BORES. THE PIVOT PLATES WERE REMOVED AND REPLACED IAW EA 5530-01238.

Part: PLATE — CORRODED (HORIZ STAB) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND HORIZONTAL STABILIZER PIVOT PLATE CORRODED AT LEFT I/B LUG BORES. THE PIVOT PLATES WERE REMOVED AND REPLACED IAW EA 5530-01238.

Part: ATTACH ANGLE — CRACKED (STA 1463) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A 3/4" CRACK COMING FROM RIVET HOLE IN R/H SIDE VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE AT STA 1463. THE CRACKED AREA WAS CUT OUT AND A REPAIR ANGLE WAS INSTALLED IAW SRM 53-05, FIGURE 23.

Part: PAN — CRACKED (L/H MLG DOOR) · airframe 48,039 hrs · 22,916 cycles

INSPECTION FOUND A 1" CRACK IN L/H MLG I/B DOOR PAN AT LEADING EDGE. THE DOOR PAN WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-3, 51-30-8, AND 51-10-2.

Part: SKIN — CRACKED (WS 286)

INSPECTION FOUND A 3 CRACK IN RT WING LEADING EDGE UPPER SKIN AT STA XOS 286. A DOUBLER WAS INSTALLED IAW ECRA 5720-01773 AND A DIP WAS INITIATED TO REINSPECT THE REPAIR AT INTERVALS NOT TO EXCEED 14 DAYS AND TO INSTALL A PERMANENT REPAIR WITHIN 12 MONTHS.

Part: SKIN — CRACKED (SERVICE DOOR)

INSPECTION FOUND A 1 INCH CRACK IN AFT SERVICE DOOR SKIN AT TOP AFT EDGE OF HOLD OPEN HOOK CUTOUT. REPAIRED IAW ECRA 5205-01008.

Part: BAYONET — WORN (TAIL CONE)

THE FORCE REQUIRED TO RELEASE TAIL CONE USING EXTERNAL HANDLE WAS LOW. THE LEFT LOWER TAIL CONE BAYONET WAS REMOVED AND REPLACED DUE TO WEAR. AN ADJUSTMENT/TEST OF THE TAIL CONE RELEASE MECHANISM WAS PERFORMED IAW MM 53-53-00.

Part: PAN — CRACKED (CARGO DOOR)

INSPECTION FOUND A 2.25 INCH CRACK IN AFT CARGO DOOR PAN AT FORWARD HOLD OPEN LATCH AND A .75 INCH CRACK IN AFT CARGO DOOR PAN AT AFT HOLD OPEN LATCH. INSTALLED REPAIRS IAW ECRA 5321-01010.

Part: BEAM — CRACKED (PAX DOOR)

INSPECTION FOUND TWO CRACKS IN THE NR 1 BEAM OF MAIN CABIN DOOR. THE BEAM HAD A .75 INCH CRACK ON AFT END AND A .375 INCH CRACK ON FORWARD END.

Part: SKIN — DENTED (BS 237)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 237 ABOVE CUSP. A NEW SKIN SECTION WAS INSTALLED BETWEEN LONGERON 15L AND 18L IAW ECRA 5330-02445.

Part: SEAT TRACK — CORRODED (BS 117-1174)

INSPECTION FOUND SEAT TRACK CORRODED AROUND SCREW HOLES AT LT I/B POSITION, STA 1117-1174 AFT GALLEY AREA. NEW SEAT TRACK SECTIONS WERE INSTALLED IAW SRM 53-05.

Part: PAN — CRACKED (CARGO DOOR)

INSPECTION FOUND A 1.5 INCH CRACK IN MID CARGO BIN DOOR PAN. THE CRACK WAS STOP DRILLED AND A DOUBLER REPAIR WAS INSTALLED IAW SRM 52-05, FIGURE 26A.

Part: SEAT TRACK — CORRODED (BS 1117-1174)

INSPECTION FOUND LEFT CENTER SEAT TRACK CORRODED AROUND SCREW HOLES FROM GALLEY NR 3 TO GALLEY NR 4 AREA, STA 1117 TO 1174. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 4F.

Part: ANGLE — CORRODED (CARGO COMPT)

INSPECTION FOUND AFT CARGO COMPARTMENT Z-ANGLE CORRODED. THE Z-ANGLE WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 63 AND 51-30-5.

Part: SENSOR — INOPERATIVE (NLG)

THE AIRCRAFT HAD A BRIEF HISTORY OF THE NOSE GEAR UNSAFE LIGHT REMAINING ILLUMINATED AFTER TAKEOFF. CYCLING THE GEAR WOULD EXTINGUISH THE LIGHT. THE NOSE GEAR LOCK SENSOR WAS REMOVED AND REPLACED IAW MM 32-60-05, PAGES 216-220. THE NOSE GEAR WAS SWUNG WITH OPERATION AND INDICATIONS CHECKING NORMAL.

Part: CHANNEL — CRACKED (MLG DOOR JAMB)

INSPECTION FOUND A 1 INCH CRACK IN RT MLG INBOARD DOOR FORWARD JAMB CHANNEL. A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2.

Part: SKIN — DAMAGED (BS 427-507)

FINGER DOUBLERS WERE INSTALLED TO FUSELAGE SKIN AT STA 427 TO 507, LONGERON 20L IAW SRM 53-04, FIGURE 12B. THE SKIN DAMAGE HAD BEEN REPAIRED PREVIOUSLY AND DEFERRED PER DIP NR D16874.

Part: SKIN — TORN (BS 427-507)

TUS - FLT 0425 - INSPECTION FOUND A 1.5 INCH TEAR IN FUSELAGE SKIN AND DAMAGE TO TWO SKIN CLIPS DUE TO GROUND DAMAGE. THE DAMAGE WAS LOCATED AT STA 427-STA 507 AND LONGERONS 19L AND 20L. THE SKIN TEAR WAS REPAIRED IAW ECRA 5330-02317 AND SRM 53-04, FIGURE 12B. THE SKIN CLIPS WERE REPAIRED PER SRM 53-03, FIGURE 3. (X)

Part: EEL PWR SUPPLY — INOPERATIVE (CABIN)

FLT NR 0305 - EWR - BOTH OVERWING EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE. THE POWER SUPPLY WAS REPLACED AND OPERATION OF THE OVERWING EMERGENCY EXIT LIGHTS WAS RESTORED. (M)