N92874

Part: SKIN — CRACKED (L-1 DOOR) · airframe 60,851 hrs · 36,583 cycles

INSPECTION FOUND A 1/4" CRACK AT RIVET IN L-1 DOOR SKIN AND THE CORNER WAS BENT. THE CRACK WAS LOCATED AT THE UPPER AFT CORNER OF DOOR. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 32 AND 51-10-3B.

Part: SEAT TRACK — CORRODED (STA 200-228) · airframe 60,851 hrs · 36,583 cycles

INSPECTION FOUND R/H I/B SEAT TRACK CORRODED AT STA 200-228. THE SEAT TRACK SECTION WAS REPLACED IAW SRM 53-05, FIGURE 4F, SHEET 1.

Part: SEAT TRACK — CORRODED (STA 1136-1174) · airframe 60,851 hrs · 36,583 cycles

INSPECTION FOUND L/H CENTER SEAT TRACK CORRODED AROUND FLOOR PANEL MOUNT HOLES BETWEEN STA 1136 AND 1174. A NEW SEAT TRACK SECTION WAS INSTALLED IAW SRM 53-05.

Part: SEAT TRACK — CORRODED (STA 200-228) · airframe 60,851 hrs · 36,583 cycles

INSPECTION FOUND R/H I/B SEAT TRACK CORRODED AT STA 200-228. THE CORRODED SECTION OF SEAT TRACK WAS REPLACED IAW SRM 53-05, FIGURE 4F, SHEET 1.

Part: FAN — OVERHEATED (A/C BAY) · airframe 60,196 hrs · 36,160 cycles

THE FLIGHT ATTENDANT REPORTED AN ELECTRICAL SMOKE ODOR APPARENTLY COMING FROM THE RIGHT AFT LAV AREA AFTER TAKEOFF FROM MIA. THE AIRCRAFT WAS RETURNED TO MIA WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE CABIN AIR RECIRCULATION FAN HAD OVERHEATED. THE CABIN RECIRCULATION FAN WAS REMOVED AND REPLACED IAW MM 21-20-12. OPERATIONAL CHECKS WERE GOOD WITH NO ODORS DETECTED.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 58,535 hrs · 35,229 cycles

INSPECTION FOUND EMERGENCY AISLE PATH LIGHTING IN CENTER OF AIRCRAFT INOPERATIVE. THE EMERGENCY BATTERY CHARGER NEAR TOP BEACON WAS REMOVED AND REPLACED AND OPERATION OF AISLE PATH LIGHTING CHECKED GOOD.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND FIVE INTERCOSTALS CORRODED INSIDE TORQUE BOX AT AFT CARGO PIT AREA, FS 1165 - 1203. THE INTERCOSTALS WERE REMOVED AND NEW INTERCOSTALS WERE INSTALLED IAW SRM 51-10-4, 51-10-3, 51-30-1, AND 51-30-5.

Part: SKIN — GOUGED (AFT OF R1 DR) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND EXTERNAL FUSELAGE SKIN GOUGED AFT OF R-1 DOOR GUST LOCK. THE GOUGED AREA WAS REMOVED. SKIN FILLER AND REPAIR DOUBLERS WERE INSTALLED IAW SRM 53-34-0, 51-10-4, 51-10-3, AND 53-04, FIGURE 24.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO INTERCOSTAL CORRODED AT FS 769-788 BETWEEN LONGERONS 27R AND 28R. PANEL 2214C WAS REMOVED IAW SRM 51-30-01. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-05. PANEL 2214C WAS REINSTALLED IAW SRM 51-30-01.

Part: SKIN — DENTED (T/E FLAP) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND LEFT I/B FLAP LOWER SKIN SURFACE DENTED. THE LEFT I/B FLAP PANEL WAS REMOVED AND NEW SKIN WAS INSTALLED IAW SRM 51-50-14, 51-10-3, 51-50-20, AND 57-52-14. THE PANEL WAS INSTALLED IAW SRM 51-30-1.

Part: WEB — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO PIT TORQUE BOX WEB CORRODED. THE TORQUE BOX WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-5.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND FORWARD CARGO DOOR FORWARD JAMB UPPER WEB CORRODED. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-30-5.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CUSP ANGLE CORRODED AT FS 200, RBL 54. THE R-1 DOOR, FRAME FITTING, AND CUSP ANGLE WERE REMOVED IAW MM 52-41-00, SRM 51-30-05, AND 53-05, FIGURE 55. A NEW ANGLE AND REPAIR SPLICE ANGLES WERE INSTALLED IAW SRM 51-30-01. THE R-1 DOOR WAS REINSTALLED IAW MM 52-41-00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND TAIL COMPARTMENT LT SIDE CANTED FRAME GOUGED AT FS 1463. THE CORROSION WAS REMOVED AND REPAIR ANGLES WERE INSTALLED IAW SRM 51-30-5, 53-01, FIGURE 1, 51-10-3, AND EA 9-5311-2-A0888, FIGURE 2.

Part: WEB — CRACKED (L1 DOOR) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND A 1 INCH CRACK IN L1 DOOR TORQUE BOX WEB AFT OF TANG AT LONGERON 15L. THE FASTENERS WERE REMOVED, TANGS TRIMMED, AND FILLER AND DOUBLER WERE INSTALLED IAW SRM 51-30-2, 51-10-4, AND EA 9-5314-2-A0884.

Part: SKIN — DENTED (L/E SLAT) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND RT WING EXTERNAL SURFACE OF ZERO SLAT SKIN DENTED I/B OF THE DRIVE TRACK. THE SLAT WAS REMOVED, REPAIRED, AND REINSTALLED IAW MM 27-80-01, EA 9-5740-2-A0890, AND ECRA 5740-01040.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO FLOORBEAM AND NUT PLATES CORRODED AT FS 1338. THE UPPER L-ANGLE ON FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 53-05, 51-30-01, 51-30-02, 51-30-05, AND 51-10-4.

Part: BEAM — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO DOOR JAMB BEAM CORRODED. THE LOWER DOOR JAMB BEAM WAS REMOVED AND A NEW LOWER DOOR JAMB BEAM WAS INSTALLED USING A DOUBLER AND SPACER IAW SRM 51-30-5 AND 51-30-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO CABIN FLOORBEAM AND NUT PLATES CORRODED AT FS 1322. THE FLOORBEAM WAS REPAIRED IAW SRM 53-05 AND 53-05, FIGURE 20A.

Part: STRAP — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO DOOR JAMB TORQUE BOX FWD STRAP CORRODED. THE FORWARD STRAP WAS REMOVED AND A NEW STRAP WAS INSTALLED IAW SRM 53-01, FIGURE 1, 51-10-4, 51-10-3, AND 51-30-5.

Part: FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO FRAME CORRODED AT FS 541 BETWEEN LONGERONS 26R AND 26L. THE CORRODED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-03, FIGURE 2A, 51-10-4, 51-10-3, 53-05, FIGURE 2A, AND 51-30-5.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO FALSE BULKHEAD LOWER SUPPORTS CORRODED AND CRACKED AT FS 1007, LONGERON 28L AND 28R. BOTH SUPPORTS WERE REMOVED AND NEW SUPPORTS WERE INSTALLED IAW SRM 51-10-5, 51-10-4, AND 51-10-3.

Part: FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO FRAME CORRODED AT FS 560 BETWEEN LONGERONS 26R AND 26L. THE CORRODED SECTION OF FRAME WAS REMOVED AND A Z-FRAME REPAIR SPLICE WAS INSTALLED IAW SRM 53-03, FIGURE 2A AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND EXTERNAL FUSELAGE SKIN CREASED AT FS 230 BETWEEN LONGERON 17L AND 18L. THE SKIN WAS REPAIRED IAW ECRA 5330-02445.

Part: FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO FRAME CORRODED AT FS 1117, LONGERON 30. THE CORRODED SECTION OF FRAME WAS REMOVED AND A NEW FRAME SECTION WAS INSTALLED IAW SRM 51-30-5, 51-10-4, AND 51-10-3.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO RT TIE DOWN TRACK CORRODED BETWEEN FS 693 AND 788. THE CARGO TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-01, 51-10-4, AND 51-10-3.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO SUPPORT CORRODED AT FS 750 BETWEEN LONGERONS 29L AND 29R. THE SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW 51-30-5, 51-10-4, AND 51-30-2.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MID CARGO DOOR LOWER JAMB BEAM CORRODED AROUND RIVNUTS. THE DOOR JAMB WAS REPAIRED IAW ECRA 5310-03027.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND AFT CARGO OVERHEAD FLOORBEAM CORRODED ON NUT PLATES AND EXFOLIATION CORROSION ON RT SIDE AT FS 1309. THE FLOORBEAM WAS REMOVED AND A NEW FLOORBEAM WAS INSTALLED IAW SRM 51-30-2 AND 51-10-4.

Part: WEB — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CUSP WEB CORRODED AT FS 200 - 207, RBL 56. THE CUSP WEB WAS REMOVED AND A REPAIR DOUBLER AND FILLER WERE INSTALLED IAW SRM 53-01, FIGURE 1, 51-30-02, 51-30-08, AND 51-10-3.

Part: WEB — CRACKED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CRACKED IN SEVERAL PLACES AT FS 1280, RBL 54. THE CRACKS WERE APPROXIMATELY 1 INCH LONG. FLOOR PANELS WERE REMOVED TO GAIN ACCESS. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-05, FIGURE 96, 51-10-3, AND 51-30-2. THE FLOOR PANELS WERE REINSTALLED IAW ECRA 5100-01844.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND SUPPORT CORRODED AT AFT LT SIDE OF WEB AT CUSP AREA, STA 1309. THE SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2 AND 51-10-4.

Part: WEB — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MAIN CABIN CUSP WEB CORRODED AT FS 160 - 200, RBL 56. THE CORRODED AREA WAS CUT OUT IAW SRM 53-01, FIGURE 3. A REPAIR DOUBLER AND FILLER WERE INSTALLED IAW SRM 53-14-1, FIGURE 11, 51-30-02, 51-10-3, AND 53-01, FIGURE 3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED ON UPPER AND LOWER SURFACE IN MID CARGO AREA AT FS 636, LONGERON 28R-29R. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-1.

Part: SKIN — GOUGED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND RT INTERNAL FUSELAGE SKIN GOUGED AT FS 1429. THE AREA WAS BLENDED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, 51-10-3, 51-10-4, AND 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND MAIN CABIN FLOOR SUPPORT CORRODED AT FS 160-200, RBL 56. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-10-4, 51-30-3, 51-30-4, AND 51-30-2.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND LT EXTERNAL FUSELAGE SKIN DENTED AT FS 195, LONGERON 23L. A DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND RT EXTERNAL FUSELAGE SKIN DENTED BETWEEN FS 313 - 332, LONGERON 20-21R. THE EXISTING DOUBLER WAS REMOVED IAW SRM 51-30-05 AND 51-30-02. THE DENTED SKIN WAS REMOVED IAW SRM 53-04, FIGURE 12 & 13. REPAIR DOUBLERS AND FINGER DOUBLERS WERE INSTALLED IAW SRM 53-04, FIGURE 12B, 51-10-3, 51-30-2, AND 51-30-5.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND LT EXTERNAL FUSELAGE SKIN DENTED AT FS 233, LONGERON 23L. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-4 AND 51-30-2.

Part: SKIN — DENTED (RT MLG DOOR) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND RT MLG DOOR EXTERNAL SKIN DENTED IN TWO PLACES 7 INCHES APART I/B OF DOOR SKID. A REPAIR PATCH WAS INSTALLED IAW SRM 52-01, FIGURE 2 AND 51-30-3.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND EXTERNAL FUSELAGE SKIN DENTED AND CREASED AT FS 322, LONGERON 25R. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, 51-10-4, AND 51-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND EXTERNAL FUSELAGE SKIN CREASED AT FS 312, LONGERON 24L. THE SKIN WAS COLD WORKED AND A DOUBLER WAS INSTALLED IAW SRM 51-10-2, 53-04, FIGURE 38, 51-10-3, AND 51-30-2.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND THE EXTERNAL FUSELAGE SKIN DENTED AT FS 340, LONGERON 24L. THE DENTED AREA WAS REFORMED AND A DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN CENTER FLOOR PANEL DELAMINATED AT FS 905 - 946. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5100-01844.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN CENTER FLOOR PANEL CRACKED AT FS 905-946. THE PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-2 AND 51-30-8.

Part: WEB — CRACKED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND A 2 INCH CRACK IN CUSP WEB AT FS 237, RBL 56. THE CUSP WEB WAS REMOVED AND THE CRACK WAS STOP DRILLED IAW SRM 51-30-2 AND 53-01, FIGURE 2. A REPAIR DOUBLER AND THE CUSP WEB WERE INSTALLED IAW SRM 53-01, FIGURE 4, 51-30-2, AND 51-30-1.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN RT I/B FLOOR SUPPORT CORRODED WITH A 1.5 INCH EDGE CRACK AT FS 210. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2 AND 51-10-3.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND FORWARD ENTRY FLOOR PANEL DAMAGED (BROKEN CORNERS AND SOFT SPOTS) AT FS 160-200, LBL 44 TO LBL 54. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265.

Part: FLOOR PANEL — GOUGED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN LT I/B FLOOR PANEL GOUGED AT FS 916. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265 AND ECRA 5100-01844.

Part: FLOOR PANEL — GOUGED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN RT I/B FLOOR PANEL GOUGED AT FS 1040. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-1, ECRA 5320-01265, AND 5100-01844.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN RIGHT I/B FLOOR PANEL DELAMINATED AT FS 466. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265, ECRA 5100-01844, AND SRM 51-30-1.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND A CREASE IN EXTERNAL RT FUSELAGE SKIN AT FS 522, LONGERONS 16L AND 18L. DOUBLERS WERE INSTALLED IAW SRM 53-04, FIGURE 38, 51-10-4, AND 51-10-3.

Part: FLOOR PANEL — GOUGED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN RIGHT I/B FLOOR PANEL GOUGED AT FS 946. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265 AND ECRA 5100-01844.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN LT O/B FLOOR PANEL DELAMINATED AT FS 1155. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265 AND ECRA 5100-01844.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN LEFT I/B FLOOR PANEL CRACKED IN TWO PLACES AT FS 313. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW ECRA 5320-01265, ECRA 5100-01844, AND SRM 51-30-1.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND CABIN RT I/B FLOOR PANEL DELAMINATED AT FS 916. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-30-1, ECRA 5320-01265, AND ECRA 5100-01844.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 58,259 hrs · 35,062 cycles

INSPECTION FOUND A 2 INCH CRACK AND LOOSE SCREWS IN CABIN LT O/B FLOOR PANEL AT FS 313. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-05, FIGURE 1, 51-10-4, AND 51-10-3.

Part: STRUT — DAMAGED (NLG)

THE NLG WOULD NOT RETRACT AFTER TAKEOFF FROM EWR. QRH PROCEDURES WERE FOLLOWED WITH NO CHANGE IN RESULTS. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE NLG SHOCK STRUT OUTER CYLINDER IAW MM 32-21-02, PAGE 401/801.. THE GEAR WAS SWUNG SEVERAL TIMES WITH NO DEFECTS NOTED.

Part: VALVE — LEAKING (NLG)

THE NOSE GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM IAH. THE SIF LIGHT AND AUTOSPOILER DO NOT USE LIGHT WERE ILLUMINATED. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MX FOUND THE SHRADER VALVE LEAKING. THE SCHRADER VALVE AND O-RING WERE REPLACED AND THE STRUT WAS SERVICED IAW MM 32-21-02. A GEAR RETRACTION WAS PERFORMED IAW MM 32-30-00 WITH ALL INDICATIONS AND OPERATION CHECKING GOOD.

Part: LIGHT — INOPERATIVE (ROW 28-30)

INSPECTION FOUND EMERGENCY AISLE LIGHTING AT ROW 28-32 INOPERATIVE. MAINTENANCE FOUND LIGHT FIXTURE AT ROW 30 BLOWING FUSE AT THE POWER SUPPLY. REPLACED LAMP AND FUSE.

Part: MECHANISM — OUT OF ADJMT (EMER EXIT DOOR)

THE OVERWING EMERGENCY EXIT DOORS ON BOTH SIDES WERE DIFFICULT TO CLOSE/OPEN. ALL EMERGENCY EXIT DOORS WERE ADJUSTED IAW MM 52-21-00.

Part: WIRE — FAILED (E & E COMPT)

INSPECTION FOUND APU POWER FEEDER CABLES BURNT AT 'T' STRIP S3-23 IN E/E COMPARTMENT, STA 207. ALL THREE PHASES (A,B, AND C) OF APU POWER FEEDER CABLES WERE REPLACED. IN ADDITION, BOTH APU GEN RELAYS AND WIRES WERE REPLACED. OPERATIONAL CHECKS WERE GOOD.

Part: FRAME — CRACKED (BS 1463)

INSPECTION FOUND A 6 INCH CRACK IN CANTED FRAME WEB AT STA 1463. THE CRACKED AREA WAS REMOVED AND A WEB AND SPLICE REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2.

Part: SKIN — CORRODED (BS 180-200)

INSPECTION FOUND FUSELAGE SKIN CORRODED AROUND MARKER BEACON ANTENNA AREA AT STA 180 TO 200. A DOUBLER WAS INSTALLED IAW ECRA 5330-02745.

Part: BELTFRAME — CRACKED (BS 1446)

INSPECTION FOUND 1 INCH CRACKS BETWEEN ATTACH BOLTS IN BELTFRAME STA 1446 AT LONGERONS 2L, 3L, 4L, 2R, 3R, 4R, AND 5R. THE BELTFRAME WAS REMOVED AND A NEW FRAME WAS INSTALLED IAW SRM 51-30-2.

Part: FITTING — CRACKED (CARGO DOOR)

INSPECTION FOUND A 2 INCH CRACK IN AFT CARGO DOOR NR 1 HORIZONTAL BEAM FORWARD END FITTING. A NEW FITTING WAS INSTALLED IAW SRM 51-30-5.

Part: BEAM — CRACKED (PAX DOOR)

INSPECTION FOUND A .75 INCH CRACK IN MAIN CABIN DOOR NR 5 HORIZONTAL BEAM. A NEW NR 5 BEAM WAS INSTALLED IAW SRM 51-30-2 AND 51-10-3.

Part: BELTFRAME — CRACKED (BS 1136)

INSPECTION FOUND TWO, 1 INCH CRACKS IN BELTFRAME AT STA 1136, LONGERON 6R. A NEW BELTFRAME SECTION WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: SEAT TRACK — CORRODED (BS 1117)

INSPECTION FOUND LT OUTBOARD SEAT TRACK FORWARD OF AFT SERVICE DOOR AT STA 1117 CORRODED. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1.

Part: BELTFRAME — CRACKED (BS 712)

INSPECTION FOUND TWO 1 INCH CRACKS IN BELTFRAME AT STA 712 LONGERON 6L AND TWO 1 INCH CRACKS WERE FOUND IN BELTFRAME AT STA 712 LONGERON 6R. THE BELTFRAME WAS REMOVED AND REPLACED FROM LONGERON 7L TO 7R IAW SRM 53-03, FIGURE 32.

Part: SEAT TRACK — CORRODED (BS 1079-1212)

INSPECTION FOUND SECOND SEAT TRACK FROM OUTBOARD CORRODED AROUND ALL CAP NUTS AT STA 1079 TO 1212. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 53-05.

Part: BEAM — CRACKED (CABIN DOOR)

INSPECTION FOUND A 1.25 INCH CRACK IN MAIN CABIN DOOR LOWER HORIZONTAL BEAM. THE BEAM WAS REMOVED AND REPLACED IAW SRM 51-30-0.

Part: FRAME — CRACKED (BS 503)

INSPECTION FOUND TWO 1 INCH CRACKS IN FRAME AT LONGERON 6R AND A 1 INCH CRACK IN FRAME AT LONGERON 6L, STA 503. FRAME REPAIRS WERE INSTALLED IAW SRM 53-03, FIGURE 32.

Part: CLIPS — OUT OF ADJMT (TAIL CONE)

THE FORCE REQUIRED TO PULL BOTH THE EXTERIOR AND INTERIOR TAIL CONE RELEASE HANDLES FROM CLIPS WAS LOW. THE EXTERIOR AND INTERIOR HANDLE CLIPS WERE ADJUSTED IAW MM 53-53-00.

Part: CABLES — OUT OF ADJMT (TAIL CONE)

THE FORCE REQUIRED TO RELEASE TAIL CONE USING EXTERIOR HANDLE WAS LOW. THE TAIL CONE CABLES WERE ADJUSTED IAW MM 53-53-00.

Part: SEAT TRACK — CORRODED (BS 196-218)

INSPECTION FOUND SEAT TRACK CORRODED AT STA 196-218. A NEW SECTION OF SEAT TRACK WAS INSTALLED IAW SRM 53-05.

Part: SEAT TRACK — CORRODED (BS 200-266)

INSPECTION FOUND LT INBOARD SEAT TRACK CORRODED AT STA 200-266. A NEW SEAT TRACK SECTION WAS INSTALLED IAW SRM 53-05, FIGURE 4.

Part: ESCAPE LINE — ROTTED (LT & RT OVERWING)

INSPECTION FOUND THE LT AND RT EMERGENCY OVERWING EXIT DOOR ESCAPE LINES DRY ROTTED AT HOOK ATTACH POINT. THE EMERGENCY ESCAPE LINES WERE REMOVED AND REPLACED IAW MM 25-61-00, PAGES 201A-204.

Part: BULKHD STIFFENER — CRACKED (BS 218)

INSPECTION FOUND A 1.5 INCH CRACK IN E & E COMPARTMENT VERTICAL STIFFENER AT AFT BULKHEAD STA 218, FOUR INCHES ABOVE LONGERON 28L. THE CRACK WAS STOP DRILLED AND STACK DOUBLERS WERE INSTALLED IAW SRM 53-01, FIGURE 2, SHEET 4.

Part: SEAT TRACK — CORRODED (BS 205)

INSPECTION FOUND RIGHT CENTER SEAT TRACK CORRODED AT STA 205. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: SKIN — DAMAGED (BS 285)

THE FUSELAGE SKIN AT STA 285 BETWEEN LONGERON 23L AND 24L WAS BENT DUE TO IMPACT BY A TRUCK. THE DENTED AREA WAS CUT OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-04 FIGURE 38 SHEET 21.

Part: BATTERIES — DISCHARGED (L & R OVERWING)

INSPECTION FOUND BOTH AFT LT AND RT OVERWING EMERGENCY EXIT SIGNS INOPERATIVE. THE BATTERIES WERE REMOVED AND REPLACED IAW MM 33-53-00, PAGE 409.

Part: O-RING — LEAKING (NLG STRUT)

THE NLG RED UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. MAINTENANCE FOUND THE NLG STRUT SCHRADER VALVE LEAKING. THE O-RING WAS REPLACED. THE NLG STRUT WAS SERVICED WITH NITROGEN AND A DIP WAS ISSUED FOR FULL SERVICE AT NEXT RON MAINTENANCE.

Part: O-RING — CUT (NLG STRUT)

THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM IAH. THE GEAR REMAINED DOWN WITH THREE GREEN INDICATIONS AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NLG SCHRADER VALVE O-RING CUT AND NLG STRUT DEFLATED. THE O-RING WAS REPLACED AND THE NLG WAS SERVICED IAW MM 32-21-02. A NOSE GEAR SWING WAS PERFORMED IAW MM 32-30-00 AND OPERATION CHECKED GOOD.

Part: SKIN — DENTED (BS 37-110)

INSPECTION FOUND FORWARD LOWER LT FUSELAGE DENTED FROM STA 37 TO 110. THE DENT WAS REPAIRED IAW ECRA 5330-02600, SRM 51-10-03, AND 51-30-2.

Part: LANYARD — BROKEN (R1 DOOR SLIDE)

FORWARD GALLEY SLIDE WIRE BROKEN. REPLACED BROKEN LANYARD ON R1 DOOR SLIDE.

Part: ANGLE — CORRODED (BS 1155-1211)

INSPECTION FOUND FLOOR SUPPORT ANGLE CORRODED FROM STA 1155 TO 1211, LONGERON 29R. THE FLOOR SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-1.

Part: SKIN — DENTED (BS 218-237)

INSPECTION FOUND SEVERAL DENTS IN FUSELAGE SKIN AT STA 218 TO 237, LONGERON 14L TO 18L. NEW SKIN AND DOUBLERS WERE INSTALLED IAW ECRA 5330-02445 AND ECRA 5330-02471.

Part: CHANNEL — CORRODED (BAGGAGE COMPT)

INSPECTION FOUND AFT BAGGAGE BIN DOOR THRESHOLD Z-CHANNEL CORRODED. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 63.

Part: SKIN — CRACKED (RUDDER)

INSPECTION FOUND TOP LT SIDE OF RUDDER SKIN BENT WITH A 2 INCH CRACK. THE CRACKED AREA OF SKIN WAS CUT OUT AND A DOUBLER WAS INSTALLED IAW SRM 55-01.

Part: TAILCONE — DEPLOYED (AFT FUSELAGE)

WHEN OPERATIONS ARRIVED AT AIRCRAFT THE TAILCONE WAS FOUND DEPLOYED WITH THE EMERGENCY SLIDE UNRAVELED, BUT NOT INFLATED. MAINTENANCE FOUND THE TAILCONE CRACKED AND THE EVACUATION SLIDE DEPLOYMENT LANYARD CLEVIS END BROKEN. A NEW LANYARD WAS INSTALLED IAW MM 25-62-01. THE EVACUATION SLIDE WAS REMOVED AND REPLACED IAW MM 25-02-01 AND THE TAILCONE WAS REMOVED AND REPLACED IAW MM 53-53-00, BLOCK 401. IN ADDITION, THE TAILCONE RELEASE CABLE WAS REPLACED DUE TO FRAYING. AN ADJUSTMENT/TEST OF THE TAILCONE RELEASE SYSTEM WAS PERFORMED IAW MM 53-53-00 AND OPERATION CHECKED GOOD.

Part: HYD LINE — LEAKING (LT MLG DOOR)

THE AIRCRAFT LOST RT HYDRAULIC SYSTEM PRESSURE WHILE EN ROUTE TO CLE. THE HYDRAULIC QUANTITY INDICATION FLUCTUATED BETWEEN TWO AND TWELVE QUARTS. THE LANDING GEAR WAS LOWERED USING ALTERNATE EXTENSION HANDLE. WHEN THE AIRCRAFT ARRIVED IN CLE, THE NOSE GEAR STEERING WAS INOPERATIVE. THE AIRCRAFT WAS TOWED TO THE GATE. MAINTENANCE FOUND HYDRAULIC LINE TO LT MLG DOOR LATCH LEAKING. THE LINE WAS REPLACED USING FLEX LINE AND A DIP WAS ISSUED TO REPLACE THE FLEX LINE BEFORE 1,200 HOURS OR 500 FLIGHTS.

Part: CYLINDER — INOPERATIVE (NLG)

THE NOSE GEAR RED UNSAFE LIGHT REMAINED ILLUMINATED WHEN GEAR WAS EXTENDED FOR LANDING. THE GEAR WAS CYCLED AND THE RED LIGHT EXTINGUISHED WITH THE GREEN INDICATION LIGHT ILLUMINATING. THE AIRCRAFT HAD A BRIEF HISTORY OF THE NLG RED LIGHT REMAINING ILLUMINATED AFTER GEAR EXTENSION. MAINTENANCE REMOVED AND REPLACED THE NLG RETRACT CYLINDER IAW MM 32-32-06, PAGE 201, LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: BUNGEE CYL — INOPERATIVE (NLG)

THE NLG LIGHT INDICATED UNSAFE DURING APPROACH. THE GEAR WAS CYCLED AND INDICATIONS WERE GOOD. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NLG BUNGEE CYLINDER AT FAULT. THE NLG BUNGEE CYLINDER WAS REPLACED. THE GEAR WAS RETRACTED SEVERAL TIMES AND OPERATION CHECKED GOOD.

Part: HYD LINE — LOOSE (LT TR CONTL VLV)

EWR - FLT 0362 - THE LT HYDRAULIC QUANTITY DROPPED TO 3 QUARTS ON APPROACH TO EWR. THE CABIN BEGAN TO FILL WITH SMOKE WHILE TAXIING IN AFTER LANDING. THE COCKPIT WINDOWS WERE OPENED AND CABIN WAS PRESSURIZED TO CLEAR THE AIR. MAINTENANCE FOUND THE LT THRUST REVERSER CONTROL VALVE SYSTEM PRESSURE SUPPLY LINE LEAKING AT B-NUT WHICH HAD BACKED OFF. THE B-NUT WAS RESECURED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK AND OPERATIONAL CHECKS WERE GOOD. THE CABIN SMOKE WAS A RESULT OF THE LEAKING HYDRAULIC LINE. BOTH PACK WATER SEPARATOR BAGS WERE REMOVED AND REPLACED. THE SYSTEM WAS BURNED OUT AND NO SMOKE OR SMELL WAS REMAINING. (X)

Part: BLADE — BROKEN (NR 1 ENGINE)

FLT NR 423 - ELP - THE NR 1 ENG FAILED WITH AN ENGINE FIRE WARNING INDICATION WHILE EN ROUTE FROM IAH TO LAX. THE FAILURE WAS ACCOMPANIED BY VIBRATION AND LOSS OF THE LEFT HYDRAULIC SYSTEM. THE NR 1 ENGINE WAS SHUT DOWN AND THE AIRCRAFT WAS DIVERTED TO ELP WHERE IT LANDED WITHOUT INCIDENT. THE NR 1 ENGINE WAS REMOVED AND REPLACED. INVESTIGATION REVEALED THAT THE PRIMARY CAUSE OF ENGINE FAILURE WAS DUE TO THE LIBERATION OF A STAGE 1 BLADE WHICH BROKE ONE INCH BELOW MID-SPAN. THE BLADE FAILURE WAS CAUSED BY FOD. SUBMITTER STATES 'BLUE ICE WAS SUSPECTED'.

Part: SKIN — CRACKED (FUSELAGE)

HOU - INSPECTION FOUND A 3 INCH CRACK IN FUSELAGE SKIN AT LOWER NR 1 VHF FORWARD ANTENNA. THE SKIN WAS REPAIRED IAW EA 5330-01823. (M)