N400DA

Part: CHANNEL — CRACKED (BS 1263,)

THE AFT CHANNEL AT FS 1263 ON THE RT TORQUE BOX OF THE VENTRAL STAIRWAY WAS FOUND WITH A TYPICAL CRACK PER B727 S/B 53-0129. THE CRACK PART WAS REMOVED AND REPLACED WITH A NEW CHANNEL PER ER/A 368109-14AD.

Part: ANGLE — CRACKED (NR 2 LE SLAT)

REF SHIP 400 TPA LTR CHK C-1, NR 2 L/E SLAT ANTI-ICE T-DUCT CUT OUT ANGLE CRACKED. REPAIRED PER MM 57-54-0.

Part: SKIN — CRACKED (BS 1237)

A .875 INCH CRACK ON EMPENNAGE SKIN AT STR 22R AND STA 1237. REPAIRED PER SRM 53-30-3 FIG 25.

Part: CONTROL CABLE — FAILED (NLG DOOR)

AFTER TAKEOFF, PILOT HEARD LOUD NOISE FROM NOSE WHEEL AREA AND NOTICED NLG LIGHT INDICATION. AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. FOUND LOWER NLG DOOR CABLE WITH SEVERAL STRANDS BROKEN AND BIRD CAGED, NLG DOORS WERE NOT FULLY CLOSED. REPLACED CABLE ASSY, TENSIONED AND RIGGED SYSTEM AND PERFORMED GEAR SWING PER MM.

Part: SKIN — CRACKED (BS 360-380)

LFEC INSPECTION OF THE STRINGER 4R LAP SPLICE INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. HFEC INTERNAL INSPECTION CONFIRMED 3 CRACKS BETWEEN FS 360 AND 380. THE CRACKED AREA OF SKIN LAP WAS CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366753-14, REV A.

Part: SKIN — CRACKED (BS 481-680)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 481 & 680 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL. INTERNAL HFEC INSPECTION CONFIRMED 94 CRACKS ALONG THE PANEL LENGTH. THE SKIN LAP SPLICE WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366751-14, REV A.

Part: SKIN — CRACKED (BS 681-740)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 681 AND 740 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 48 CRACKS ALONG THE PANEL LENGTH. THE ENTIRE SKIN LAP WAS CUT OUT OF THE PANEL AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366752-14, REV A.

Part: SKIN — CRACKED (BS 400-420)

LFEC INSPECTION OF THE STRINGER 4L SKIN LAP SPLICE INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. HFEC INTERNAL INSPECTION OF THE ENTIRE PANEL CONFIRMED 7 CRACKS BETWEEN FS 400 AND 420. THE DAMAGED SECTION OF LAP SPLICE WAS CUT OUT AND REPAIRED WITH AN EXTERNAL DOUBLER PER B727 SRM 53-30-3, FIG 5 AND DOCUMENTED PER ER/A 366754-14.

Part: BATTERY PACK — DISCHARGED (CABIN)

TWO AISLE EMERGENCY EXIT SIGNS INOP AT AFT GALLEY AND AFT ENTRY DOOR. REPLACED BATTERY PACKS, OPS NORMAL.

Part: WEB — CRACKED (BS 1233)

A .5 INCH CRACK AT UPPER TORQUE BOX VERTICAL WEB STA 1233 RT SIDE AT UPPER ROW OF HORIZONTAL RIVETS. REPAIRED PER M/M 53-11-0 FIG 819.

Part: WEB — CRACKED (BS 1213)

A 1.5 INCH CRACK AT TORQUE BOX VERTICAL WEB STA 1213 LT SIDE AT HORIZONTAL ROW OF RIVETS. REPAIRED PER M/M 53-11-0 FIG 819.

Part: BATTERY PACK — DISCHARGED (RIGHT)

RT FWD OVERWING EMERGENCY LIGHT INOP. REPLACED CARTRIDGE AND BATTERY PACK.

Part: BATTERY PACK — DISCHARGED (RT OVERWING)

RT OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERY PACK AND CARTRIDGE.

Part: P & D VALVE — FAILED (NR 3 ENGINE)

NR 3 ENG FAILED INITIALLY FELT SLIGHT SWERVE AND EPR DROPPED WHEN THE THROTTLE WAS ADVANCED. THE ENG CONTINUED TO SPOOL DOWN TO WINDMILLING. REPLACED P/D VALVE.

Part: FLAP TRACK — CORRODED (TE FLAP)

INB'D FLAP, INB'D TRACK, TYP CORROSION AT FWD AND AFT, PAD-UP ATTACH HOLES AND FWD LUG: AD 90-07-05. FWD AND AFT PAD-UP ATTACH HOLES SUBJECT OF AD 90-07-05; REC'D BAC/FAA APPROVAL TO STEP-UP HOLES AND BUSH. FWD ATTACH LUG NOT SUBJECT OF AD; REC'D BAC APPROVAL TO BUSH AND SHIM LUG FACE.

Part: FLAP TRACK — CORROSION (TE FLAPS)

INB'D FLAP/INB'D TRACK TYP CORROSION AT FWD AND AFT PAD-UP ATTACH HOLES AND FWD LUG - AD 90-07-05 AND 90-06-09. OVERSIZE HOLES AND SHIM FWD LUG FACE.

Part: FIRE LOOP — MALFUNCTIONED (NR 1 ENGINE)

NR 1 ENGINE FIRE INDICATION IN FLIGHT. FOUND 13TH STAGE FLANGE GASKET LEAK. REPLACED GASKET. FOUND 8TH STATE DUCT LEAK. SECURED DUCT, REPLACED NR 1 FIRE LOOP CONNECTORS AND CHECKED RESISTANCE REPLACED NR 1 LWR FIRE LOOP. REPLACED NR 1 FIRE DETECTOR CONTROL UNIT. REPLACED NR 1 FIRE HANDLE. REPLACED NR 1 FIREWALL DETECTOR AND CONNECTORS. RAN ENGINE, ALL CHECKS NORMAL.

Part: FIRE WARNING — ACTIVATED (NR 1 ENGINE)

ON CLIMBOUT 12,000 FT, GOT FIRE WARNING AND FIRE BELL NR 1 ENGINE. DISCHARGED ONE FIRE BOTTLE AND SHUT DOWN ENGINE. RETURNED TO SLC. ENGINE WINDMILLED 10 MINUTES WITH POSITIVE OIL PRESSURE. T/S IN PROGRESS.

Part: FRAME — CORRODED (BS 560)

FUSELAGE FRAME AT STA 560 WAS FOUND WITH CORROSION AT S26R. A 3 INCH SECTION OF A LEG WAS REMOVED. REPAIRED PER ERA 331039-14.

Part: SKIN — WORN (RT AILERON)

UPPER SKIN HAD NUMEROUS O/S AND LOOSE FASTENERS. SPLICED SKIN SECTION PER SRM 57-50-1.

Part: SPAR — CRACKED (RT AILERON)

AFT SPAR CRACKED AT I/B EDGE. SPLICED SPAR PER SRM 51-40-3.

Part: SPAR — CRACKED (LT TE MIDFLAP)

CRACKED IN AFT SPAR RAIL 56 FROM I/B END NR 2 MIDFLAP. REPAIRED PER BOEING M/M 57-52-0 PAGE 807.

Part: RIB — CRACKED (WS 686.5)

RW INTERNAL HYDRO-PRESSED RIB TO STRINGER STA 686.50 STRINGER 2ND FRAME AFT IS CRACKED. STOPED DRILLED PER MM 57-13-00 FIG 801. REMOVED FUEL PROBE DRILLED NEW REPAIR DOUBLER PER MM 53-13 AND INSTALLED.

Part: FLOORBEAM — CORRODED (BS 380)

CABIN FLOOR BEAM CORRODED STA. 380 LBL14 TO RBL60. REPAIRED PER SRM 53-10-1 FIG. 4.

Part: STRINGER — CRACKED (OUTER WING)

HFEC INSP OUTER WING UPPER STRINGER TO RIB CRACK INCL W 5.629.0 LT SIDE 2ND STRINGER AFT OF AFT VENT BOX. STOP DRILLED CRACK AND BEGAN TO DRILL UP ALL ANGLES PER M/M 57-13-0 FIG 802. COMPLETED DRILLING UP REPAIR ANGLES PER M/M 57-13-0 FIG 802. TRIMMED, TREATED, PAINTED REPAIR PARTS PS 900-OK TO INSTALL. INSTALLED REPAIR PARTS PER M/M 57-13-0 FIG 802.

Part: STRINGER — CRACKED (WS 546)

FOUND AT HMV REF OPN 8602 HFEC INSP OUTER WING UPPER STRINGER TO PILE CRACK IND W5 546 RT WING 2ND STRINGER AFT OF AFT VENT BOX. STOP DRILLED PER MM 57-13-0 DRILLED NEW REPAIR MM 57-1 3-0 FIG 802, INSTALL PER MM 57-13-0 FIG 802.

Part: FLOORBEAM — CORRODED (BS 344)

STA 344 FLOORBEAM CORRODED LEFT TO RIGHT SIDES. REPAIRED PER SRM 51-10-8 FIG 11.

Part: SKIN — WORN (NR 4 LE SLAT)

THE NR 4 L/E SLAT EXTERNAL SKIN AND ATTACHMENT HOLES WORN WHERE FENCE FAIRING ATTACHES. BEGAN REPAIR PER MM 57-40-0 PG 817, FABRICATED REPAIR PER MM 57-40-0 PG 817. COMPLETED INSTALL OF DOUBLER PER 57-54-0 PG 817.

Part: SKIN — WORN (NR 5 LE SLAT)

THE NR 5 L/E SLAT EXTERNAL SKIN WORN AND CRACKED WHERE FENCE ATTACHES. BEGAN FABRICATED DOUBLER PER MM 57-54-0 FIG 8B, DRILLED DOUBLER PER MM 57-54-0 FIG 813, ROUTED OUT CRACKED AREA PER MM 57-54-0 FIG 813. DYE CHECK PER PS 900-6-3, SHOWS NO FURTHER DAMAGE. BURNISHED WEAR GROOVES, OK. INSTALLED REPAIR PER MM 57-54-0 FIG 813.

Part: STRINGER — CRACKED (WS 601.5)

STRINGER 11 AT WS 601.5 CRACKED (MARKED). CUT OUT ACCESS FOR REPAIR PER MM 57-13-0 FIG 803 STARTED REPAIR PER MM 57-13-0 FIG 804. OK TO INSTALL REPAIR. BEGAN INSTALLING REPAIR ANGLES. COMPLETED INSTALLATION OF REPAIR ANGLES PER M/M 57-13-0, FIG 804. INSTALLED COVER PLATE PER M/M 57-13-0, FIG 804.

Part: STRINGER — CRACKED (WS 656.5)

STRINGER NR 10 CRACKED AT WS 656.5. REPAIRED PER M/M 57-13-0 FIG 802.

Part: STRINGER — DAMAGED (FUSELAGE)

TRANS FROM SMS PERMANENT REPAIR STR 18A DAMAGE IN NORMAL FLANGE PER SRM 53-12-0. CORRECTION CONTINUED ON NR 1160 CORRECTION. REMOVED TIME LIMITED REPAIR. FABRICATED REPAIR DOUBLER AND STARTED PER MM 53-12-0. OK TO TREAT AND PAINT. REMOVED DAMAGED SECTION OF STRINGER PER M/M 53-12-0 PG 819. TREAT REPAIR AREA AND PARTS PER PS 900-3-5 NR 03. OK TO INSTALL REPAIR. STARTED REPAIR INSTALLATION. INSTALLED 8 BOLTS.

Part: FRAME — CRACKED (BS 910)

FRAME AT STA 910/913 CRACKED IN RT WHEEL WELL. REPAIRED PER MM53-11-0 PG 814.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT ABOVE L2 DOOR INOP. REPLACED LIGHT ASSY.

Part: LIGHT — INOPERATIVE (COCKPIT)

COCKPIT OVRHD EMERGENCY LIGHT INOP. REPLACED LIGHT ASSY.

Part: BATTERY PACK — DISCHARGED (CABIN)

L1 AND R1 DOOR EMERGENCY EXTERIOR LIGHTS INOP. REPLACED BATTERY, CHECKS NORMAL.

Part: LIGHT — INOPERATIVE (COCKPIT)

EMERGENCY EXIT LIGHT IN COCKPIT FOUND INOP (P/N 334701743) (S/N 3874). REPLACED ASSEMBLY WITH (S/N 5829), OPERATION CKS GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN)

LEFT OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERY AND PACK, LTS CKS NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT LEFT OVERWING LIGHT INOP. REPLACED BATTERY AND RACK, LT CKS NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

EXIT LIGHT RT AFT INOP, LT WING EMER LIGHT INOP AND RT ENTRY EMER LIGHT INOP.

Part: RIB — CRACKED (NR 2 LE SLAT)

FOUND ON F1 LETTER CK, 1 INCH CRACK AT NR 2 L/E SLAT INBOARD NOSE RIB AT ACTUATOR ROD END ATTACH. REPAIRED PER MM 57-54-0.

Part: ANGLE — CRACKED (NR 7 SPOILER)

NR 7 SPOILER LOWER WING ATTACH ANGLE CRACKED INBOARD END. FOUND DURING F-1 LTR CK TPAMM. REPAIRED PER 57-20-22.

Part: STIFFNER — CRACKED (WING FRONT SPAR)

WING FRONT SPAR VERTICAL STIFFENER CRACKED AT NR 3 SLAT INBOARD TRACK, OUTBOARD SIDE (ON WING). FOUND DURING F-1 LTR CK TPA 3/18/96. REPAIRED PER 57-20-21.

Part: ACTUATOR — CRACKED (LT MLG DOOR)

A-SYS HYD FAILURE AFTER GEAR SELECTED UP. A-SYS QTY WAS FLUX AT THE ZERO MARK. FOUND LT MLG DOOR ACTUATOR CRACKED. REPLACED SAME, OPERATION NORMAL.

Part: SWITCHES — DIRTY (NLG DOOR)

ON APPROACH, NOSE GEAR DOOR LIGHTS ON FORWARD PANEL AND FLIGHT ENGINEER'S PANEL TOOK EXCEPTIONALLY LONG, 30-50 SECONDS, TO EXTINGUISH. CORRECTIVE ACTION. CLEANED DEBRIS FROM NOSE LANDING GEAR DOOR SWITCHES. CKS OK. NO MRR. REJECTED. 08-31-05 GT 595.

Part: RIB — CRACKED (NR 2 SLAT)

FOUND DURING E-2 LETTER CHECK, NR 2 SLAT ACT ROD END ATTACH RIB CRKD .5 INCH I/B WEB, NR 3 SLAT ACT ROD END ATTACH RIB CRKD .25 INCH O/B WEB. REPAIRED PER M/M 57-54-0 PG 803 TO 804.

Part: SKIN — CRACKED (VERT STAB)

FOUND DURING E-2 LETTER CHECK, .5 INCH CRACK EXTENDING FROM RIVET AT PNL 9523. REPAIRED PER MM 54-30-0.

Part: WEB — CRACKED (BS 1263)

FOUND DURING E-2 LETTER CHECK, LIGHTENING HOLE CRACKED .25 INCH AT STA 1263 LT LOWER. REPAIRED PER MM 53-11-0.

Part: FRAME — CRACKED (R2 DOOR OPENING)

FOUND DURING E-2 LETTER CHECK, R-2 DOOR OPENING FRAME HAS .75 INCH CRACK AT FWD UPPER STOP PAD CASTING. INSTALLED DOUBLER PER M/M 53-13-0 PG 808.

Part: STRINGER — CRACKED (FS 950)

DURING INSPECTION FOUND FUSELAGE STRINGER 18A LEFT SIDE, CRACKED ON HORIZONTAL FLANGE AT FS 950. REPAIRED PER MM 53-12 PG 818 ITED LEVEL 2 REPAIR.