N512DA

Part: B-NUT — LOOSE (HYDRAULIC SYS) · airframe 72,842 hrs · 48,953 cycles

SLOW LEAK (FLUID LOSS) A HYDROL SYSTEM PUMPS SHUT DOWN PRIOR TO TOTAL FLUID LOSS. SERVICED A HYD RESERVOIR 8 PTS. FOUND B-NUT LEAKING PYLON NR 1. SECURED B-NUT LEAK CKS OK. SECURED PYLON PNL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 72,258 hrs · 48,560 cycles

EMERGENCY EXIT LIGHT SEAT 22D INOP. REPLACED LIGHT ASSY AT SEAT 22D. MCO AND PLAC REMOVED.

Part: STIFFENER — CRACKED (LT WING) · airframe 71,995 hrs · 48,377 cycles

IB SPAR STIFFENER IS CRACKED AT NR 2 SLAT IB TRACK. REPAIR PER M/M 57-20-021-8

Part: PANEL — FAILED (COCKPIT) · airframe 71,508 hrs · 48,063 cycles

AT FL 330 CREW NOTICED ELECTRICAL FUMES/SMOKE EMINATING FROM OVERHEAD PANEL THROUGH CONTROL STAND LIGHT OPENING. STALL WARNING FAIL BATTERY C/B WAS POPPED, STALL WARNING PANEL WAS WARM TO TOUCH, WIND SHEAR FAIL LIGHT ALSO ILLUMINATED. FOUND PRINTED CIRCUIT BOARD IN STALL WARNING PANEL BURNED PANEL ORDERED AGP FROM LAX. REPLACED SAME.

Part: CONTROLLER — INOPERATIVE (A/C BAY) · airframe 71,405 hrs · 47,998 cycles

AT 12000 FT MSL CABIN BEGAN CLIMBING AS PSID INCREASED PAST 3.5 PSID WITH SINGLE PACK. DUCT PRESSURE WAS GOOD AT 34 PSI AT 1.4 EPR. CARGO VALVE CONFIRMED CLOSED. CABIN HAD MAX CLIMB AT 5.5 PSID OF 800 FPM. MAX CABIN ALT 5,500 FT. RETURNED TO CVG. FOUND RT A/C PACK 35 DEG TEMP CONTROLLER AT FAULT. REPLACED CONTROLLER. ALSO REPLACED LEFT PACK COCKPIT TEMP SELECTOR AND RADIO RACK COOLING VALVE. PRESSURIZATION NOW CHECKS NORMAL.

Part: ACTUATOR — LEAKING (LT MLG DOOR) · airframe 70,057 hrs · 47,142 cycles

AFTER GEAR RETRACTION LT GEAR DOOR LIGHT REMAINED ON FOLLOWED BY LOSS OF A SYS HYD. FOUND LT GEAR DOOR ACTUATOR LEAKING. REPLACED ACTUATOR.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 69,739 hrs · 46,933 cycles

FOUND RT SIDE OVERWING EMERGENCY EXIT IDENTIFIER LIGHTS INOPERATIVE. REPLACED BATTERY OF M1086 EMER EXIT POWER SUPPLY. CKS GOOD

Part: LIGHT — INOPERATIVE (LT OVERWING) · airframe 69,641 hrs · 46,865 cycles

RT OVERWING EMERGENCY LIGHT INOP. FOUND WIRE OPEN BETWEEN PIN 6 OF D2466 AT BATTERY PACK TO SPLICE SP2482. RAN NEW WIRE BETWEEN CANNON PLUG AND SPLICE. LIGHT OPN CKS GOOD. REINSTALLED SIDEWALL PANEL REMOVED TO REPLACE WIRE.

Part: LIGHT — CORRODED (OVERWING) · airframe 69,115 hrs · 46,526 cycles

RIGHT FORWARD OVERWING EMERGENCY LIGHT IS INOP. T/S SYSTEM AND CLEANED CORROSION FROM LIGHT SOCKETS AND REPLACED BULBS. NOW CHECKS NORMALLY.

Part: STIFFENER — CRACKED (LE FLAP)

A .5 INCH CRACK IN I/B ATTACH ANGLE/ SPAR STIFFENER FOR NR 4 SLAT ACT. REPLACED STIFFENER PER 57-20-21.

Part: FRAME — DENTED (BS 580,600 & 660)

FRAMES DAMAGED AT STA 580, 600, 660 AND 700 AT STRINGER 22L. NEW SECTIONS BEING SPLICED IN ER/A 333911-14 REV A.

Part: TRACK — CORRODED (TE FLAP)

DURING OVERHAUL THE I/B FLAP, I/B TRACK ASSY (P/N 65-19270-12) CORROSION WAS FOUND AT THE MLG AND SPOILER BEAM ATTACH PAD AREAS AND WEAR WAS FOUND AT THE FWD ATTACH LUGS AND THE MLG DOOR HINGE FITTING ATTACH HOLES AND THE TOGGLE DETENT HOLE. SUBJECT PART WAS REPAIRED PER BFG ER 23-0511.

Part: TRACK — CORRODED (TE FLAP)

DURING OVERHAUL OF THE I/B FLAP, I/B TRACK ASSY, (P/N 65-19269-18), CORROSION WAS FOUND AT THE MLG AND SPOILER BEAM ATTACH PAD AREAS AND WEAR AT THE FWD ATTACH LUG. PART WAS REPAIRED PER ER/A 372298-14AD REVISION B.

Part: SKIN — GOUGED (BS 990)

GOUGE FOUND IN THE SKIN AT THE AFT EDGE OF THE C-2 DOOR CUTOUT AT FS 990. THE DAMAGE AREA IS LOCATED JUST BELOW STR 24R. DAMAGE IN SKIN, DOUBLER AND TRIPLER BUT NOT THE INTERNAL BEAR STRAP ER/A 333860-14 REV A.

Part: SPAR — CRACKED (LT ELEVATOR)

STABILIZER / LT ELEVATOR / REAR SPAR : CRACK REPAIR. THE L/H ELEVATOR WAS FOUND WITH CRACK EXTENDING.125 INCH BEYOND THE 2ND FROM I/B END HINGE BRACKET. THE CRACK IS TYPICAL OF B727 S/B 55-0089 AND AD 96-06-05. THE CRACK WAS STOP DRILLED PER ER/A 367822-14AD AND WILL BE INSPECTED WITHIN 1600 FLIGHT HOURS WITH PERMANENT MODIFICATION PER THE S/B WITHIN 3200 FLIGHT HOURS.

Part: SPAR WEB — CRACKED (CENTER WING)

WING CENTER SECTION REAR SPAR WEB, RBL 13 CRACK REPAIR. THE CENTER WING REAR SPAR WEB WAS FOUND WITH A 1.5 TYPICAL CRACK IN A CHEM-MILL RADIUS NEAR THE UPPER SPAR CAP AT RBL 13. THE CRACK WAS ROUTED OUT OF THE SPAR WEB AND REPAIRED WITH AN ALUMINUM DOUBLER PER ER/A 367140-14AD, REV A.

Part: STIFFENER — CRACKED (RT WING)

REF SHIP 512 TPA LTR CHK D-1 12-07-98, L/E SPAR STIFFENER CRACKED AT NR 6 SLAT I/B TRACK I/B STIFFENER. REPLACED PER MM 57-20-21.

Part: RIB — CRACKED (NR 5 LE SLAT)

REF SHIP 512 TPA LTR CHK D-1 12-07-98, NR 5 L/E SLAT I/B ACTUATOR ATTACH RIB CRACKED. REPAIRED PER MM 57-54-0 AND ERA 366246-14.

Part: ACTUATOR — FAILED (NR 4 LE SLAT)

LOST ALL A-SYSTEM HYDRAULIC FLUID. REPLACED NR 4 SLAT ACTUATOR.

Part: STRINGER — CRACKED (VERT FIN)

FOUND ON C2 LETTER CHECK, VERTICAL FIN STRINGER CRACKED AT RIB ATTACH BOLT S-8 AT STA 157.200 RT SIDE. REPAIR PER M/M 53-30-0.

Part: BATTERY — DISCHARGED (CABIN)

CABIN EMERGENCY LIGHTS INOP. REPLACED BATTERY PACK.

Part: SKIN — CORRODED (BS 1010)

THE SKIN JUST AFT OF THE FS 1010 BUTT SPLICE JUST ABOVE STRINGER 29L WAS FOUND TO BE CORRODED AND WAS SUBSEQUENTLY CUT OUT. THE DAMAGE CUT OUT MEASURED 1.75 X 1.25. THERE IS AN EXISTING REPAIR ADJACENT TO THE CUT OUT BETWEEN STR 29L AND STR 30 COVERING A DAMAGE CUTOUT OF 4.5 X 4.25. THIS REPAIR DOUBLER ENDS AT THE STA 1010 BUTT JOINT. THIS ER/A WILL REMOVE THE ADJACENT REPAIR DOUBLER AND DISCARD IT, CUTOUT DAMAGE AT NEW LOCATION, AND INSTALL A DOUBLER TO COVER BOTH CUT OUT LOCATIONS, WITH THREE ROWS OF FASTENERS AROUND.

Part: SKIN — CORROSION (BS 1010)

THE SKIN JUST AFT OF THE FS 1010 BUTT SPLICE JUST ABOVE STRINGER 29L WAS FOUND TO BE CORRODED AND WAS SUBSEQUENTLY CUT OUT. THE DAMAGE CUTOUT MEASURED 1.75 BY 1.25. THERE IS AN EXISTING REPAIR ADJACENT TO THE CUTOUT BETWEEN STR 29L AND STR 30 COVERING A DAMAGE CUTOUT OF 4.5 BY 4.25. THIS REPAIR DOUBLER ENDS AT THE STA 1010 BUTT JOINT.

Part: WEB — CRACKED (LT LWR TQ BOX)

LIGHTNING HOLES IN TORQUE BOX CRACKED JUST ABOVE FWD AIRSTAIR HINGE LT MARKED, 2 EA. LIGHTNING HOLE CRACKED LT SIDE OF TORQUE BOX ABOVE AIRSTAIR UPLOCK LATCH 1 AND 2. REPAIRED PER M/M 53-11-0 P 828.

Part: FITTING — PITTED (LT WING)

LT PORK CHOP FITTING PITTED. BORED HOLES OVERSIZE WITHIN M/M 57-42-0 PG 806 814 LIMITS. HFEC SHOWS NO CRACKS. ROTO AND SHOT PEENED PER M/M 57-42-0. CAP PLATED AND PAINTED PER M/M.

Part: FITTING — PITTED (RT WING)

RT PORK CHOP FITTING PITTED. BORED HOLES OVERSIZE WITHIN M/M 57-42-0 PG 806 814 LIMITS. HFEC FOUND NO CRACKS. CAP PLATED AND PAINTED PER M/M 57-42-0.

Part: DOOR — CRACKED (RT SERVICE DOOR)

A .5 INCH CRACK RT FWD SERVICE DOOR AT FWD LOWER ROLLER CUTOUT. FABRICATED AND INSTALLED DOUBLER PER ERA 362763-14.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

CENTER SEC EMERG FLOOR TRACK LIGHTING INOP. REPLACED PWR SUPPLY AND BATTERIES.

Part: LIGHT — DIRTY (CABIN)

EMERGENCY EXIT LIGHT CTR AISLE AT AFT SVC DOOR POPS C/B. REMOVED DEBRIS FROM LIGHT ASSY.

Part: BULBS — FAILED (CABIN)

SIX AIR STAIR BULBS INOP. OVERHEAD STAIR LIGHT OUT. EXIT SIGN ROW 21 BULB BURNED OUT. OVERHEAD EXIT SIGN BETWEEN L2 AND L3 HAVE BULB BURNED OUT. EXIT SIGN AT R2 HAS BULB BURNED OUT. RELAMPED ALL LIGHTS.

Part: BATTERIES — DISCHARGED (MEGAPHONE)

F/C MEGAPHONE INOP. REPLACED BATTERYS, CK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

ON L/O, FOUND LT FWD EXTERIOR OVERWING EMERGENCY EXIT LIGHT INOP DURING TEST. REPLACED BATTERY PACK. OPS CKD NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY BATTERY PACK FAILED SYSTEM TEST. REPLACED PACK.

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

REJECTED TAKOFF DUE TO NOISE OF COMPRESSOR STALL, FOLLOWED BY ENG FAIL LIGHTS. STRONG CROSS WIND AT 70 DEGS OF 19 KNTS OCCURED PRIOR TO TAKE OFF AIRSPEED INDICATION. INSPECTED 1, 2, AND 3 ENGINE INTAKE AND EXHAUSTS, RAN ENGINES PER P.F.H.B. 4-0-7-7 ALL PARAMETERS NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

FORWARD CENTER EMERGENCY LIGHT INOPERATIVE. REPLACED EMERGENCY LIGHT ASSEMBLY.

Part: BATTERY PACK — DISCHARGED (CABIN)

RT OVERWING EMERGENCY EXIT LIGHT INOP. REPLACED RT OVERWING EMERGENCY EXIT LIGHT BATTERY PACK, OPS CHECK NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

AFT AIRSTAIRS EMERGENCY LIGHT INOP. REMOVED AND REPLACED AFT AIRSTAIRS EMERGENCY LIGHT ASSEMBLY, OPS CHECK NORMAL.

Part: SKIN — PUNCTURED (FS 440)

DURING GROUND HANDLING, A HOLE WAS PUNCTURED IN THE FUSELAGE SKIN 14 INCHES BY 18 INCHES, BETWEEN FS 420 TO 440 AND S-23R TO S-26R. A PIN IN THE TOWBAR BROKE DURING TOWING AND THE AIRCRAFT STRUCK THE TUG. A TEMPORARY REPAIR WAS INSTALLED AND THE AIRCRAFT WAS FERRIED TO ATL FROM BOS. DAMAGED AREA WAS TRIMMED OUT FROM FS 440 BUTT JOINT FORWARD FOR 25.375 INCHES AND FROM THE SKIN LAP JOINT AT S-26R TO 3.5 INCHES ABOVE S-23R. ALSO, THE STRINGER AT S-23R WAS BROKEN. STRINGER WAS REPAIRED PER BOEING 727 SRM. THE REFERENCE ER/A REPLACED THE SKIN AND INSTALLED AN EXTERNAL SPLICE DOUBLER, ERA 302820-14.

Part: RIB — CRACKED (NR 7 SLAT)

THE NR 7 SLAT ACTUATOR ATTACH NOSE RIB LWR SIDE AFT CRACKED .5 INCH. FOUND DURING A-1 LTR CK TPAMM. REPAIRED PER MM 57-54-0 PAR 3B.

Part: ANGLE — CRACKED (NR 7 SLAT)

NR 7 SLAT COVE SKIN ATTACH ANGLE UNDER TAI DUCT CRACKED 1 INCH. FOUND DURING A-1 LTR CK TPAMM. REPAIRED PER MM 57-54-0 PG 807A.

Part: SKIN — CRACKED (PAX DOOR)

FOUND ON A1 LTR CK, 1.125 INCH CRACK AT MAIN ENT DOOR UPPER HINGE CUTOUT. REPAIR PER M/M 53-30-0 AND ERA 301886-14.

Part: ANGLE — CRACKED (NR 3 SLAT)

A .5 INCH CRACK NR 3 SLAT COVE SKIN ATTACH ANGLE BELOW TAI DUCT. FOUND DURING A-1 LTR CK TPAMM. REPAIRED PER M/M 57-54-0 PG 807A.