N71828

Part: CHARGER — INOPERATIVE (CABIN) · airframe 49,540 hrs · 23,959 cycles

THE BATTERY CHARGER FOR EMERGENCY EXIT LIGHTS AT THE L-2 DOOR WAS FOUND INOPERATIVE. THE CHARGER WAS REMOVED AND REPLACED IAW MM 33-53-00, PAGE 401.

Part: CONTROL CABLE — OUT OF ADJUST (TAILCONE) · airframe 46,699 hrs · 22,450 cycles

THE EXTERIOR TAIL CONE RELEASE HANDLE PULLED LOW AT 10 POUNDS. THE TAIL CONE CABLE TENSION WAS ADJUSTED AND THE HANDLE CLIPS WERE REPLACED.

Part: FRAME — CRACKED (STA 1418) · airframe 46,699 hrs · 22,449 cycles

INSPECTION FOUND A 2" CRACK IN TAIL COMPARTMENT BELTFRAME AT STA 1418, LONGERON 2R AND 2L. REPAIRED BELTFRAME IAW SRM 53-03-31A.

Part: LONGERON — CRACKED (STA 1418) · airframe 46,699 hrs · 22,449 cycles

INSPECTION FOUND A 1.5" CRACK IN LONGERON 2R AT STA 1418. REPAIRED LONGERON IAW SRM 53-02, FIGURE 18.

Part: BATTERY — DEFECTIVE (CABIN) · airframe 45,394 hrs · 21,776 cycles

THE FORWARD ENTRY PORTABLE EMERGENCY LIGHT ASSEMBLY BATTERIES WOULD NOT CHARGE. THE LIGHT ASSEMBLY NICAD BATTERIES WERE REPLACED AND OPERATION CHECKED GOOD.

Part: BALLAST — BURNED (GALLEY) · airframe 43,431 hrs · 20,701 cycles

SMOKE ENTERED THE COCKPIT FROM BEHIND THE F/O'S SEAT WHILE ON FINAL APPROACH TO IAH. THE AIRCRAFT LANDED SAFELY AND TAXIED TO THE GATE UNDER ITS OWN POWER. THE SMOKE HAD CLEARED. MAINTENANCE FOUND THE FORWARD GALLEY WORK LIGHT BALLAST AT FAULT. THE BALLAST WAS REMOVED AND REPLACED. POWER WAS APPLIED TO THE SYSTEM AND OPERATION CHECKED GOOD WITH NO OTHER DEFECTS NOTED.

Part: VALVE — LEAKING (NLG) · airframe 42,070 hrs · 19,975 cycles

WHEN THE LANDING GEAR WAS EXTENDED ON APPROACH TO SJC, THE MAIN GAER INDICATED DOWN AND LOCKED, BUT THE NOSE GEAR INDICATED UNSAFE. QRH PROCEDURES WERE COMPLIED WITH, BUT THE NOSE GEAR INDICATION REMAINED UNSAFE. WHEN THE TILLER WAS MOVED TO THE RIGHT THE NOSE GEAR INDICATED DOWN AND LOCKED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NLG PISTON LEAKING FROM THE AXLE AND THE METERING VALVE WAS LEAKING. THE METERING VALVE AND SEALS WERE REPLACED IAW MM 32-21-02 AND OVERHAUL MANUAL 32-20-01. A NLG FUNCTIONAL TEST WAS PERFORMED IAW MM 32-20-00, PAGE 201 AND ALL CHECKS WERE GOOD.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND FLOORBEAM CORRODED JUST INSIDE R-1 DOOR AT STA 200, RBL 54. THE FLOOR SUPPORT WAS REPAIRED IAW SRM 53-05, FIGURE 55 AND EA 9-5311-2-AD67B.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND SIDEWALL SUPPORT ANGLE CORRODED AT STA 1117 - 1136. THE SUPPORT ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-01.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LT CUSP WEB CORRODED AT STA 1130 - 1270, LBL 45 TO LBL 55. THE CUSP WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-30-04, 51-10-03 AND 51-30-05.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT STA 200, RBL 44 TO RBL 54. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-05.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LEFT O/B SEAT TRACK CORRODED AT STA 1136, LBL 54 (LOWER LEG OF TRACK AT CUSP WEB). THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND TWO FLOOR SUPPORT WEBS CORRODED FROM STA 140 - 200, RBL 54. THE FLOOR SUPPORT WEBS WERE REMOVED AND REPLACED IAW SRM 51-30-01.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND CORROSION UNDER SEALANT AT SHEAR TIE IN AFT CARGO AREA AT FS 1079 BETWEEN LONGERON 29R AND 30. THE SHEAR TIE WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 51-10-04 AND 51-30-05.

Part: ANGLE — CRACKED (DORSAL FIN) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND A .5 INCH CRACK IN LT SIDE DORSAL FIN TO FUSELAGE ANGLE. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-4 AND 51-10-4.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LT CUSP WEB CORRODED AT STA 465 - 712 AS SEEN FROM MID AND FORWARD CARGO BAYS. A DOUBLER AND FILLER REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 4 AND 51-10-03.

Part: ACCESS PANEL — CRACKED (NR 1 SLAT) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND A 1 INCH CRACK IN NR 1 RIGHT SLAT LOWER CUTOUT DOOR. THE CUTOUT DOOR WAS REMOVED AND REPLACED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND RIGHT O/B SEAT TRACK CORRODED AT STA 427 - 788, RBL 54. THE SEAT TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-1, 51-10-04, 51-10-03, AND 53-05, FIGURE 4.

Part: TAB — DENTED (LT AILERON) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LT AILERON CONTROL TAB AFT EDGE DENTED AND DELAMINATED. THE CONTROL TAB WAS REMOVED, REPAIRED, AND REINSTALLED IAW MM 27-10-02, SRM 57-03, AND 57-50-01.

Part: WEB — CRACKED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND A .5 INCH CRACK IN CUSP WEB AT FS 112, RBL 47. THE CRACK WAS STOP DRILLED IAW 53-01, FIGURE 2 AND A DOUBLER WAS INSTALLED IAW SRM 53-01, 51-10-03, AND 53-01 FIGURE 4.

Part: FLOORBOARD — DELAMINATED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND CABIN RIGHT O/B FLOOR PANEL DELAMINATED AT STA 275 TO 313. THE CABIN FLOOR PANEL WAS REMOVED IAW SRM 51-30-04. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-22-0, FIGURE 4, 51-10-03, AND 53-01, FIGURE 2. THE FLOOR PANEL WAS REINSTALLED IAW ECRA 5100-01844.

Part: PAN — CORRODED (CARGO DOOR) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND MID CARGO DOOR LOWER PAN CORRODED. THE CORROSION WAS REMOVED AND A DOUBLER AND SPACER WERE INSTALLED IAW EA 9-5310-2-A0665 AND ECRA 5310-03027.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LT SEAT TRACK CORRODED AT STA 1110 - 1220, LBL 44. THE TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-10-04, 51-10-03, 51-30-01, AND SRM 53-05, FIGURE 4F.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND LOWER SURFACE OF LT CUSP WEB IN AFT CARGO AREA CORRODED AT STA 1309. THE CORRODED AREA WAS REMOVED AND A NEW SECTION OF CUSP WEB WAS INSTALLED IAW SRM 51-30 AND 51-10-03.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED AT STA 1140, LBL 54. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-02 AND 51-10-03.

Part: PAN — BENT (CARGO DOOR) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND AFT CARGO DOOR BOTTOM LIP BENT. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 4.

Part: WEB — CRACKED (AIRSTAIR) · airframe 41,719 hrs · 19,807 cycles

INSPECTION FOUND A 1 INCH CRACK IN AFT AIRSTAIRS TOP STEP SUPPORT WEB. THE CRACKED AREA WAS CUT OUT AND BLENDED IAW SRM 53-01, FIGURE 2. A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURES 1 & 2, 51-10-04, AND 51-10-03.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

LEFT INBOARD SEAT TRACK IS CORRODED AT STA 1210 TO 1240 LBL 22. REMOVED AND REPLACED DAMAGED SECTION OF SEAT TRACK PER SRM 51-10-03, 53-05 FIG 4B-1, 51-10-04, 53-05 FIG 4F, 53-30-01, AND 53-30-5.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

LEFT OUTBOARD GALLEY FITTING ATTACH OUTBOARD OF TRACK CORRODED AT FS 1174. REMOVED AND REPLACED FITTING PER SRM 51-10-04, 51-360-02, AND 51-30-05.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

STATION 896 TO 905 LEFT CUSP WEB AT LBL 55 IS CORRODED. REMOVED SEAT TRACK SECTION, FABRICATED AND INSTALLED FILLER PER SRM 51-30-01 AND 53-01 FIG 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MAIN CABIN LEFT O/B SEAT TRACK AT LBL 54 IS CORRODED AT STA 1174 TO 1387. REMOVED AND REPLACED SEAT TRACK SECTION PER SRM 53-01 FIG 1, 51-10-03, AND 51-30-01.

Part: STRUCTURE — CRACKED (RT MLG DOOR) · airframe 41,718 hrs · 19,807 cycles

RIGHT MAIN LANDING GEAR DOOR UPPER CORNER CRACKED (1). REMOVED AND INSTALLED NEW CORNER PER SRM 52-84-0, 51-10-03, AND 51-30-02.

Part: WEB — CORRODED (FUSELAGE) · airframe 417,178 hrs · 19,807 cycles

CUSP WEB IS CORRODED AT STA 1041 LBL 54 ON UPPER SURFACE OF FRAME. REMOVED DAMAGED AREA AND INSTALLED REPAIR DOUBLER PER SRM 51-10-03, 51-30-02, AND 53-01 FIG 4.

Part: PAN — CRACKED (CARGO DOOR) · airframe 41,718 hrs · 19,807 cycles

FORWARD CARGO DOOR FORWARD LOWER SIDE PAN T/E BENT AND CRACKED (3). INSTALLED REPAIR DOUBLER PER SRM 52-01, 51-30-02, AND EC/RA5330-02819.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MID CARGO RIGHT SIDE FLOOR SUPPORT ATTACH TO TIEDOWN TRACK CORRODED. REMOVED CORRODED SECTION AND REPLACED PER SRM 51-10-03, 51-10-04, AND 51-30-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOOR SUPPORT CORRODED AT STA 1165 LBL 54. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02, 51-10-03, 51-10-04, AND 51-30-02.

Part: FITTING — CRACKED (FUSELAGE FRAME) · airframe 41,718 hrs · 19,807 cycles

FRAME FITTING UNDER SEAT TRACK CRACKED (1) AT STA 905 RBL 42. REMOVED AND REPLACED DAMAGED SECTION PER SRM 51-30-05, 51-10-03, AND 51-10-04.

Part: WEB — CRACKED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

STATION 807 LEFT CUSP HAS A VISIBLE 2 INCH CRACK O/B OF SEAT TRACK AT LBL 56. REPAIRED LT CUSP WEB PER SRM 53-01 FIG 4 AND 51-30-02.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 41,718 hrs · 19,807 cycles

AFT CARGO DOOR FWD LIP OF DOOR FASTENER HOLES DAMAGED AND SKIN GOUGED. REPAIRED PER EA 9-5231-2-A0659 AND REMOVED AND REPLACED PER SRM 51-30-02.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MAIN CABIN RIGHT SIDE STATION 237 CUSP WEB CRACKED AND CORRODED. REMOVED AND REPLACED CUSP WEB AND FRAME FOOT PER SRM 51-30-01 AND 51-30-05.

Part: FLOOR SUPPORT — DAMAGED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

AFT CARGO FWD BULKHEAD LOWER FLOOR SUPPORT HAS SEVERAL TOOL MARKS BETWEEN LONG 28 RIGHT AND 28 LEFT. REMOVED AND REPLACED FLOOR SUPPORT AND INSTALLED SPLICE PER SRM 51-30-02 AND 53-01 FIG 1.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 41,718 hrs · 19,807 cycles

FORWARD CARGO DOOR OUTER SKIN IS CRACKED (5). STOP DRILLED CRACK AND INSTALLED REPAIR DOUBLER PER SRM 53-01, 52-05 FIG 32, AND 51-10-03.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MID CARGO RIGHT SIDE TIE DOWN TRACK CORRODED. REMOVED AND REPLACED DAMAGED SECTION OF TRACK PER SRM 51-10-03, 51-30-02, AND 51-30-01.

Part: CLIP — CRACKED (VERTICAL STAB) · airframe 41,718 hrs · 19,807 cycles

VERTICAL STAB LOWER AFT SPAR LEFT SIDE CLIP IS CRACKED (1). REMOVED AND REPLACED CLIP PER SRM 51-30 AND 51-30-05.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CUSP WEB IS CORRODED AT STA 1079 TO 1098 AT RBL 55. REMOVED AND REPLACED DAMAGED WEB SECTION PER SRM 51-30-01, 51-10-04, 51-10-03, AND 53-01 FIG 4.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CUSP WEB RIGHT SIDE IS CORRODED FROM STA 503 TO 750. REPLACED CUSP WEB PER SRM 51-30-02.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

AFT CARGO RIGHT AFT TIE DOWN TRACK IS CORRODED BETWEEN FS 1211 AND 1320. REMOVED AND REPLACED DAMAGED SECTION OF TRACK PER SRM 51-30-01, 51-10-01, AND 51-10-03.

Part: ANGLE — CRACKED (VERTICAL STAB) · airframe 41,718 hrs · 19,807 cycles

DORSAL FIN FUSELAGE RT SIDE ANGLE IS CRACKED AT CENTER (1). REMOVED AND REPLACED ANGLE PER SRM 51-30-02, 51-10-04, 51-10-03,AND 51-30-04.

Part: DOOR — CRACKED (CARGO BAY) · airframe 41,718 hrs · 19,807 cycles

FORWARD CARGO BARRIER DOOR SUPPORT BEAM IS CRACKED AT FASTENER HOLE (1). STOP DRILLED CRACK AND INSTALLED REPAIR DOUBLER PER SRM 53-01 FIG 1, FIG 2, AND 51-30-02.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FORWARD CARGO RT TIE DOWN TRACK CORRODED BETWEEN FS 218 AND 370. REMOVED AND REPLACED TIE TRACK PER SRM 51-30-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

STATION 185 TO 195 CABIN FLOOR SUPPORT AT LBL 50 IS CORRODED. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02, 51-10-04, 53-14-01, AND 51-10-03.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

RIGHT HAND SEAT TRACK AT RBL 44 CORRODED FROM STA 200 TO 256. REMOVED AND REPLACED SECTION OF SEAT TRACK PER SRM 53-05 FIG F AND51-30-1.

Part: FLOOR SUPPORT — DAMAGED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CABIN SUB FLOOR IS PUNCTURED AND TRAVELS UNDER FLOOR SUPPORT STA 180 LBL 54. FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 53-04 FIG 4 AND 51-10-03.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOOR SUPPORT AT LBL 44 IS CORRODED AT STA 160 TO 200. REMOVED CORROSION AND FABRICATED REPAIR PER SRM 51-10-03, 51-30-05, AND 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MID CARGO AFT BULKHEAD RIGHT FLOOR SUPPORT BETWEEN LONGERON 24 RT AND 27 RT, IS CORRODED. BLENDED OUT CORROSION AND INSTALLED REPAIR DOUBLER. PER SRM 53-01 AND 51-30-02.

Part: WEB — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

WEB CORRODED RT SIDE AT BS 484 TO 505. REMOVED CORRODED SECTION. INSTALLED REPAIR DOUBLER PER SRM 51-30-02, 53-01 FIG 1 AND 53-01 FIG 4.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

MID CARGO RT TIE DOWN TRACK BETWEEN BS 893 AND 788 CORRODED. CUT OUT CORRODED AREA AND INSTALLED REPAIR PER SRM 51-30-01, 57-10-02, 51-30-04, 51-10-03, AND 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOOR SUPPORT IS CORRODED STA 1155, LBL 22 TO LBL 44. REMOVED AND REPLACED SUPPORT PER SRM 51-10-3, 53-30-1, 51-10-04, AND 51-30-054.

Part: SKIN — BENT (PAX DOOR) · airframe 41,718 hrs · 19,807 cycles

FORWARD ENTRY DOOR LOWER FORWARD CORNER DOOR SKIN DOUBLER METAL IS PEELED BACK. FABRICATED AND INSTALLED NEW DOUBLER PER SRM 52-05 FIG 32.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CABIN FLOORBEAM CORRODED AT STA 200 AT BL 0 TO RBL 44. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02, 51-10-03, 53-01 AND 51-106-04.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOORBEAM CORRODED AT LBL 6 TO RBL 200. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02, 51-10-04, 51-10-03, AND 51-30-05.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 41,718 hrs · 19,807 cycles

MID CARGO AFT BULKHEAD LOWER FLOOR SUPPORT CORRODED BETWEEN LONG 27L AND 27R. REMOVED CORRODED ANGLE, FABRICATED NEW ANGLE AND INSTALLED PER SRM 53-01 FIG 1, 51-30-02, 51-10-02, ADN 51-30-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CABIN FLOOR SUPORT CORRODED AT STA 150 TO 200 AT RBL 44. REMOVED AND REPLACED CORRODED FLOOR SUPPORT PER SRM 51-30-02 AND 51-30-03.

Part: DOOR — CHAFED (CARGO BAY) · airframe 41,718 hrs · 19,807 cycles

AFT CARGO LIP AT STOP PADS ARE CHAFED AND WORN (12). INSTALLED REPAIR DOUBLER PER EC/RA 5330-02819.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

CABIN SUBFLOOR IS CORRODED AND TRAVELS UNDER SEAT TRACK RBL 44 AT STA 200 TO 210. REMOVED DAMAGED MATERIAL, FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 51-10-01, 53-01, 53-11-01, AND EC/RA 5320-01201.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOORBEAM CORRODED AT LBL 12 AT STA 200. REMOVED AND REPLACED SUPPORT PER SRM 51-10-3 AND 51-30-05.

Part: ACCESS PANEL — CHAFED (RT WING) · airframe 41,718 hrs · 19,807 cycles

RIGHT WING LEADING EDGE ACCESS PANEL 1258 SURFACE HAS TOOL MARKS AND IS CHAFED. INSTALLED REPAIR DOUBLER PER SRM 51-30-02.

Part: PANEL — DAMAGED (RT WING) · airframe 41,718 hrs · 19,807 cycles

RIGHT WING L/E ACCESS NR 1244 HAS TOOL MARKS AT SCREW HOLE. INSTALLED DOUBLER IN ACCORDANCE WITH SRM 57-06A FIG 2, 51-10-3, AND 57-01.

Part: DOOR — CRACKED (CARGO BAY) · airframe 41,718 hrs · 19,807 cycles

FORWARD CARGO BARRIER DOOR OUTER SKIN LOWER SIDE CRACKED AROUND HANDLE CUTOUT. FABRICATED AND INSTALLED DOUBLER PER SRM 51-30-05 AND 52-01 FIG 4.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOOR PANEL SUPPORT CORRODED AT LBL 54 AT STA 160 TO 200. REMOVED AND REPLACED FLOOR SUPPORT PER SRM 51-30-02, 51-30-05, 51-10-04, AND 51-10-03.

Part: DOOR — GOUGED (CARGO BAY) · airframe 41,718 hrs · 19,807 cycles

AFT PIT BARRIER DOOR LOWER FWD CORNER HAS SEVERAL GOUGES. REPAIRED GOUGES AND INSTALLED DOUBLER PER SRM 51-10-3, 53-01 FIG 4, AND 51-30-8.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 41,718 hrs · 19,807 cycles

FLOOR SUPPORT CORRODED AT LBL 50 STA 160 TO 170. REMOVED AND REPLACED SUPPORT IN ACCORDANCE WITH SRM 51-30-02 AND 51-30-05.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

INSPECTION FOUND OVERHEAD EMERGENCY LIGHTS AT THREE ROWS IN COACH SECTION WOULD NOT OPERATE. THE POWER SUPPLY WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION FOUND EMERGENCY LIGHT IN FIRST CLASS CABIN AT STA 252 INOPERATIVE. THE LIGHT ASSEMBLY WAS REPLACED.

Part: SUPPORT — BROKEN (NR 2 ENGINE)

NUMBER 2 ENGINE FIRE LIGHT ILLUMINATED AFTER TAKEOFF. ACCOMPLISHED ABNORMAL CHECKLIST. LIGHT REMAINED ON. FOUND FIRE DETECTOR SUPPORT BROKEN AND LOOP CONNECTORS CORRODED AND DAMAGED. REPLACED A AND B LOOP CONNECTORS AND TESTED SYSTEM. REPLACED NR 1 AND 2 FIRE BOTTLES AND SQUIBS PER MM 26-20-01, 26-20-02, AND 26-20-03.

Part: BEAM — CRACKED (SERVICE DOOR)

INSPECTION FOUND A 1.25 INCH CRACK AT FORWARD END OF FORWARD SERVICE DOOR NR 4 BEAM. A NR 4 BEAM WAS INSTALLED IAW EA 5240-01192.

Part: SKIN — TORN (BS 370)

INSPECTION FOUND FUSELAGE SKIN TORN AND MISSING A 1 X 1.5 SECTION JUST FORWARD OF FORWARD BAGGAGE BIN DOOR AT STA 370, LONGERON 26R. THE DAMAGED SECTION OF SKIN WAS CUT OUT, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-05 AND ECRA 5331-01020.

Part: PAN — CORRODED (CARGO DOOR)

INSPECTION FOUND FORWARD BAGGAGE BIN DOOR PAN CORRODED. A LOWER PAN SPLICE REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 44.

Part: CABLES — OUT OF ADJUST (TAIL CONE)

THE TAILCONE PULL FORCE FROM THE OUTSIDE, INSIDE, AND AFT ENTRY DOOR HANDLES WAS EXCESSIVE. THE TAILCONE CABLES WERE RIGGED IAW MM 53-53-00.

Part: TEMP SELECTOR — INOPERATIVE (RT COCKPIT)

THE COCKPIT AND CABIN FILLED WITH SMOKE SHORTLY AFTER TAKEOFF. THE RIGHT PACK RAN TO FULL HOT. MANUAL CONTROL WAS USED WITH NO RESPONSE. THE RT PACK WAS TURNED OFF AND AFTER FIVE MINUTES IT WAS REINSTATED. THE RIGHT PACK THEN BEGAN TO WORK PROPERLY. THE RT PACK WENT TO FULL HOT AGAIN AFTER APPROXIMATELY ONE HOUR AT CRUISE WITH MANUAL SELECTED. MANUAL WAS USED TO SELECT COOLER TEMPERATURE AND THE AIRCRAFT LANDED AT IAH. MAINTENANCE FOUND THE CABIN TEMP SELECTOR AT FAULT. THE TEMP SELECTOR WAS REPLACED. THE RT PACK WAS OPERATED WITH NO DEFECTS NOTED.

Part: SENSOR — DAMAGED (LT MLG DOOR)

THE LT MLG RED LIGHT REMAINED ILLUMINATED AFTER TAKEOFF FROM IAH. THE GEAR WAS CYCLED, BUT THE RED LIGHT REMAINED ON WITH THE GEAR DOOR OPEN LIGHT ON. WHEN GEAR HANDLE WAS PLACED DOWN DURING RETURN TO IAH ALL THREE GREEN GEAR LIGHTS CAME ON. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LT MLG DOOR PROXIMITY SENSOR AND TARGET DAMAGED. THE SENSOR AND TARGET WERE REMOVED AND REPLACED AND ADJUSTED IAW MM 32-60-00. A GEAR SWING WAS PERFORMED IAW MM 32-10-00 WITH OPERATION AND INDICATIONS CHECKING GOOD.

Part: ENGINE — FOD (NR 1)

THE NR 1 ENG AUTO SHUTDOWN WHILE CRUISING AT 31,000 FT. THE A/C WAS DIVERTED TO PHX WHERE IT LANDED WITHOUT INCIDENT. INSPECTION FOUND ICE BUILD-UP IN FORWARD LAV PANEL. BLUE ICE WAS SUSPECTED AS CAUSE OF ENGINE FAILURE. THE 6TH, 7TH, 8TH AND 13TH STAGES OF NR 1 ENG COMPRESSOR WERE BORESCOPED WITH NO DAMAGE FOUND. THE NR 1 ENG WAS RUN TO TAKEOFF POWER AND ALL PARAMETERS WERE NORMAL. THE FORWARD LAV WAS FLUSHED SEVERAL TIMES AND SERVICED WITH BLUE WATER, NO LEAKS WERE DETECTED. NO SPECIFIC PART WAS IDENTIFIED AS FAILED. THE FILL CHECK VALVE, TOILET TANK DRAIN VALVE, LAV FLUSH MOTOR AND LAV WASTE DRAIN VALVE WERE REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE.

Part: DOOR PAN — CRACKED (CARGO DOOR)

HOU - INSPECTION FOUND A .50 INCH CRACK IN FORWARD CARGO DOOR OUTER PAN. THE DOOR PAN WAS REPAIRED IAW SRM 52-03. (X)

Part: SUBFLOOR WEB — CORRODED (BS 160)

HOU - INSPECTION FOUND CORROSION ON SUBFLOOR WEB BELOW GALLEY NR 1 DRAIN PAN AT STA 160 (RT OTBD FLOOR, 4 INCH BY 5 INCH AREA, COMPLETELY THROUGH SKIN). THE CORROSION WAS REMOVED AND A DOUBLER WAS INSTALLED IAW SRM 53-01. (X)

Part: FLOOR SUPPORT — CORRODED (BS 1155)

HOU - INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 1155. A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-30-3. (X)

Part: DOOR PAN — CRACKED (CARGO DOOR)

HOU - INSPECTION FOUND A .50 INCH CRACK IN FORWARD CARGO DOOR INNER PAN. THE DOOR PAN WAS REPAIRED IAW SRM 52-05. (X)

Part: FLOOR SUPPORT — CORRODED (BS 200)

HOU - INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 200. THE SUPPORT WAS REMOVED AND A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-30-2. (X)

Part: BRACKET — CRACKED (RT MLG WW)

HOU - INSPECTION FOUND A 1 INCH CRACK IN RIGHT WHEELWELL AFT INBOARD CORNER BRACKET. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-01. (X)

Part: CUSP MEMBRANE — CRACKED (BS 1300)

HOU - INSPECTION FOUND RT CUSP MEMBRANE CRACKED AT STA 1300. THE CRACK LENGTH WAS NOT IDENTIFIED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 96, SHEET 4. (X)

Part: LATCHES — OUT OF RIG (TAILCONE)

HOU - THE FORCE REQUIRED TO RELEASE TAILCONE USING THE INTERIOR HANDLE EXCEEDED THE MAXIMUM LIMIT OF 35 POUNDS. THE TAILCONE LATCHES WERE ADJUSTED PER MM 53-33-00. (X)

Part: CUSP MEMBRANE — CRACKED (BS 1300)

HOU - INSPECTION FOUND LT CUSP MEMBRANE CRACKED AT STA 1300. THE CRACK LENGTH WAS NOT IDENTIFIED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-05, FIGURE 96. (X)

Part: SKIN — DENTED (BS 240)

HOU - INSPECTION FOUND A 1 INCH WIDE BY .25 INCH DEEP DENT IN LEFT FUSELAGE SKIN ABOVE CUSP LINE AT STA 240. A REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 38. (X)

Part: DOUBLER — CORRODED (AFT BAGGAGE BIN)

HOU - INSPECTION FOUND LOWER DOOR JAMB Z-ANGLE DOUBLER CORRODED IN AFT BAGGAGE BIN. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-4 AND SRM 51-30-5. (X)

Part: RETAINING CLIPS — OUT OF ADJUST (TAILCONE HANDLE)

HOU - THE FORCE REQUIRED TO PULL TAILCONE INTERIOR RELEASE HANDLE FROM RETAINING CLIPS WAS EXCESSIVE. THE RETAINING CLIPS WERE ADJUSTED PER MM 53-33-00. (X)

Part: RETAINING CLIPS — OUT OF ADJUST (TAILCONE)

HOU - THE FORCE REQUIRED TO PULL EXTERIOR TAILCONE RELEASE HANDLE FROM RETAINING CLIPS WAS LOW. THE RETAINING CLIPS WERE ADJUSTED PER MM 53-53-00. (X)

Part: HYD PUMP — CRACKED (NR 1 ENGINE)

FLT NR 431 - MSY - THE LEFT HYDRAULIC SYSTEM FLUID QUANTITY AND PRESSURE DROPPED TO ZERO WHILE IN FLIGHT. THE AIRCRAFT LANDED AT MSY WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP CASE CRACKED. THE PUMP WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD. (M)

Part: SUPPORT SHELF — BROKEN (NR 2 ENGINE)

FLT NR 723 - OMA - THE NR 2 ENGINE EXPERIENCED A LOSS OF POWER WHILE EN ROUTE FROM CLE TO LAS. THE ENGINE THROTTLE WAS REDUCED TO IDLE AND THE AIRCRAFT WAS DIVERTED TO OMA WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND METAL IN THE NR 2 ENGINE TAILPIPE. THE NR 2 ENGINE WAS REMOVED AND REPLACED. INVESTIGATION REVEALED AN 8TH STAGE STATOR SUPPORT SHELF HAD BROKEN OUT AND WAS THE PRIMARY CAUSE OF ENGINE FAILURE. (M)

Part: EEL BATT CHARGER — INOPERATIVE (CABIN)

FLT NR 0204 - EWR - THE EMERGENCY LIGHTS IN FIRST CLASS CEILING AND ROWS 28-29 CEILING WERE FOUND INOPERATIVE. THE BATTERY CHARGER FOR THE FIRST CLASS CEILING LIGHTS WAS REMOVED AND REPLACED. THE BATTERIES FOR THE CEILING LIGHTS AT ROWS 28-29 WERE REPLACED. OPERATION OF THE EMERGENCY CEILING LIGHTS WAS RESTORED. (M)