N516DA

Part: BULKHEAD — DAMAGED (ZONE 100) · airframe 13,695 hrs · 3,328 cycles

AIRCRAFT 5016, HAD A BIRD STRIKE WHICH CAUSED DAMAGE TO FR1 BULKHEAD PANEL ( D53113091201 ), Y675 VERTICAL POST (P/N: D53113105201), Z-989 STIFFENER (P/N: D53133181200), Z-1159 STIFFENER (P/N: D53113100212). CORRECTIVE ACTION: FABRICATED AND INSTALLED THE TWO DAMAGE STIFFENERS Z-989 STIFFENER (P/N: D53133181200), Z-1159 STIFFENER (P/N: D53113100212) PER ER/A 631135-14, 630975-14. (LP 1360193, 1359716)

Part: STRUCTURE — DAMAGED (ZONE 100) · airframe 13,695 hrs · 3,328 cycles

AIRCRAFT 5016, DURING BIRDSTRIKE INSPECTION FOUND DAMAGE TO FR1 BULKHEAD PANEL (P/N: D53113091201), Y-675 VERTICAL POST (P/N: D53113105201), Z-989 STIFFENER (P/N: D53133181200), Z-1159 STIFFENER (P/N: D53113100212). WHILE COLDWORKING THE DENTED AREA COMMON TO FWD FLANGE OF POST (PN D5311310520093), MTC FOUND A CRACK ON THE FORWARD FLANGE THAT IS 1.5 INCH IN LENGTH. CORRECTIVE ACTION: REMOVED DAMAGE AREAS AND FABRICATED REPAIR PARTS AND INSTALLED PER ER/A 631012-14 AND 630944-14). (LP 1356323)

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 12,774 hrs · 3,096 cycles

ESCAPE PATH OVERHEAD AISLE EMERGENCY LITE INOP. REMOVED AND SWAPPED GROUND AND POWER ELCTRICAL CONNECTORS FROM ONE SIDE TO THE OTHER. PER A321 AMM 33-51 LIGHT IS OPERATIONAL. (LP 7826479)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 4,646 hrs · 1,101 cycles

SHIP 5016 -ATB- AIR TURN BACK DUE TO RIGHT ENGINE VIBES PEAKED AT 5.3 IN CLIMB. THROTTLE WAS RETARDED TO 70% TO COME BELOW 5.0 ON VIBES. CORRECTIVE ACTION: PERFORMED GVI AND BORESCOPE INSPECTIONS WITH NO FINDINGS. REPLACED AODV PER A321NEO AMM 79-21. OK FOR SERVICE. (4271285)

Part: SHIM — OUT OF POSITION (FLAP TRACK) · airframe 69,836 hrs · 52,740 cycles

REPAIR FOR MIGRATED SHIM, INSPECTION OF LT WING INBD FLAP INBD FLAP TRACK REVEALED A MIGRATED LAMINATED SHIM. THE CONDITION IS TYPICAL OF THAT DOCUMENTED PER BAC S/B 727-57-0178 AND AD 90-07-05. THE SHIM WAS MIGRATED BEYOND THE ALLOWABLE LIMITS OF THE S/B AND WAS REPLACED PER THE S/B INSTRUCTIONS AND PER ER/A 384219-14AD.

Part: TRANSCEIVER — MALFUNCTIONED (WEATHER RADAR) · airframe 69,688 hrs · 52,631 cycles

ATB, WX RADAR C/B POPPED TWICE. REPLACED WX RADAR R/T TEST PATTERN NORMAL - OPERATED IN WX MOD OBTAINED TARGETS, ALL OPS NORMAL.

Part: SKIN — CRACKED (S-4R,FS 681-740) · airframe 69,595 hrs · 52,579 cycles

FUSELAGE / SKIN / FS 681-740 / STRG. 4R / SKIN LAP SPLICE : CRACK REPAIR LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 681 & 740 REVEALED CRACK INDICATIONS. INTERNAL MFEC INSPECTION REVEALED SEVERAL CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN ALONG THE LENGTH OF THE PANEL. THE ENTIRE LAP JOINT ALONG THE PANEL LENGTH WAS CUTOUT TO REMOVE ALL CRACKS. THE AREA WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 383973-14AD.

Part: SKIN — CRACKED (S-4R,FS481-681) · airframe 69,595 hrs · 52,579 cycles

FUSELAGE / SKIN / FS 481-681 / STRG. 4R / SKIN LAP JOINT : CRACK REPAIR LFEC INSPECTION OF THE STRINGER 4R SKIN LAP JOINT REVEALED CRACK INDICATIONS BETWEEN FS 481 & 681. INTERNAL MFEC INSPECTION REVEALED 8 CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL ALONG THE PANEL LENGTH. THE ENTIRE LAP JOINT WAS CUTOUT FROM FS 481-681 AND REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER PER ER/A 383969-14AD.

Part: SKIN — CRACKED (FS 1080, S-4R) · airframe 69,595 hrs · 52,579 cycles

FUSELAGE / SKIN / FS 1070-1090 / STRG. 4R / SKIN LAP JOINT: CRACK REPAIR LFEC INSPECTIONS OF THE STRINGER 4R SKIN LAP JOINT REVEALED A CRACK INDICATION. INTERNAL MFEC INSPECTION DETERMINED A SINGLE CRACK IN THE LOWER SKIN AT THE LOWER FASTENER ROW BETWEEN FS 1070 & 1090. THE CRACK WAS REMOVED WITH A CUTOUT IN THE LAP JOINT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B727 SRM 53-30-3, FIG. 5 AND ER/A 383975-14AD.

Part: MOUNT — CRACKED (NR 3 ENGINE) · airframe 68,515 hrs · 51,843 cycles

INSPECTION OF THE FWD ENGINE MOUNT SUPPORT FITTING ON THE NR 3 ENGINE PYLON PER AD 97-05-08 REVEALED A CRACK IN HOLE LOCATION -D-. THE HOLE WAS OVERSIZED TO REMOVE THE CRACK AND AN ADDITIONAL INSURANCE CUT TAKEN. THE REWORK WAS ACCOMPLISHED PER FED EX S/B 2000-5410A01 AND ER/A 382909-14AD.

Part: STIFFENER — CRACKED (WING) · airframe 68,481 hrs · 51,820 cycles

NR 7 SLAT I/B TRACK I/B SPAR STIFFENER CRACKED. REPLACING STIFFENER PER M/M 57-20-021-8.

Part: CASTING — CRACKED (SPOILER) · airframe 68,481 hrs · 51,820 cycles

NR 7 SPOILER LWR CASTING REPAIR CRACKED AT LWR WING ATTACH. REPAIRED PER MM 57-20-022-8.

Part: SWITCH — INTERMITTENT (L/E FLAP) · airframe 67,661 hrs · 51,315 cycles

L/E FLAP LIGHT ILLUMINATED WHEN WING ANTI ICE SELECTED ON. REPLACED NR 4 AND NR 5 L/E FLAP POSITION XMITTERS.

Part: ACTUATOR — LEAKING (#3 KRUEGER FLAP) · airframe 67,486 hrs · 51,209 cycles

LOST A SYSTEM HYDRAULICS ON CLIMBOUT FROM ABQ. LOST PRESSUREAND QUANTITY BOTH TO ZERO. _REPLD NBR 3 L/E FLAP ACTUATOR

Part: BULKHEAD — CRACKED (FS 351.2, LBL 5) · airframe 67,054 hrs · 50,921 cycles

FUSELAGE / BULKHEAD / FS 351.2 / LBL 5 : WEB CRACK REPAIR THE FS 351.2 BULKHEAD WEB WAS FOUND CRACKED AT LBL 5 AT A DAMAGED NLG UPLOCK FITTING ATTACH POINT. THE WEB AND LOCAL BULKHEAD CHORD WERE CUT TO REMOVE THE DAMAGE. THE WEB WAS REPAIRED WITH TWO ALUMINUM DOUBLERS AND THE CHORD WITH AN ALUMINUM REPAIR ANGLE PER ER/A 381651-14, REV A.

Part: ACTUATOR — LEAKING (NLG WW) · airframe 67,054 hrs · 50,921 cycles

ON LANDING COMPLETE A SYSTEM HYD FAILURE. FOUND OVER CENTER ACTUATOR BULKHEAD FITTING BROKEN AND ACTUATOR LEAKING. CA REPLACED SAME.

Part: SUPPORT — CRACKED (STA.351.5BULKHD) · airframe 67,054 hrs · 50,921 cycles

ON FINAL WHEN LDG GEAR EXTENDED -A-SYS HYD FAILURE-COMPLETE-GEAR DOWN AND LOCKED FLAPS 30DGS-RAISED FLAP ELEC. TO 15DGS AND LANDED A/C- FOUND NOSEGEAR UPLCKACT.BRACKET CRACKED AND ACT.LINES DAMAGED-RPLCD BRACKET ACTUATOR LINES AND C/W ERA REPAIR TO STA351.5 WEB. AND CORD-RPLCD WATER SEPERATOR BAGS EDPPOS.1/2AND FILTERS.

Part: ACTUATOR — LEAKING (L/E FLAP) · airframe 66,906 hrs · 50,826 cycles

ON FINAL APPROACH PRIOR TO GEAR EXT WITH FLAPS 5 DEG AND HAD INDICATION OF A LOSS OF A SYSTEM HYD. REPLACED A SYSTEM FILTERS. REPLACED LEADING EDGE FLAP ACTUATOR FOR LEAKING

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 66,773 hrs · 50,742 cycles

LEFT AFT OVERWING LIGHT INOP. REPLACED BATTERY PACK, CHECKS NORMAL.

Part: LIGHT — WILL NOT TEST (CABIN) · airframe 65,734 hrs · 50,054 cycles

EMERG LIGHT AT REAR EXIT WOULD NOT TEST - REPLACED LIGHT RACK

Part: BATTERY — DISCHARGED (COCKPIT) · airframe 65,488 hrs · 49,890 cycles

EMERGENCY EXIT LIGHT OVER COCKPIT DOOR INOP. REPLACED EMERGENCY EXIT LIGHT BATTERIES, OPS CKS OK.

Part: SKIN — GOUGED (FUSELAGE) · airframe 65,394 hrs · 49,825 cycles

THE FUSELAGE SKIN JUST FWD OF THE FWD EDGE OF THE L1 DOOR CUTOUT WAS FOUND GOUGED MIDWAY BETWEEN THE UPPER AND LOWER HINGE CUTOUTS. BOTH HINGE CUTOUTS WERE PREVIOUSLY REPAIRED PER B727 S/B 53-0198. THE NEW DAMAGE WAS REMOVED WITH A 1 INCH CUTOUT. THE HINGE REPAIRS WERE REMOVED AND EXTENDED TO INCORPORATE THE NEW DAMAGE. THE REPAIR WAS ACCOMPLISHED PER ER/A 379825-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 65,394 hrs · 49,825 cycles

INSPECTIONS OF THE INNER CHORD, OUTER CHORD AND THE WEB OF THE C1 DOOR OPENING AFT FRAME REVEALED A 1.25 INCH CRACK IN THE OUTER CHORD BELOW THE NR 6 DOOR STOP, AN EXISTING STEEL SPLICE REPAIR FOR THE INNER CHORD, AND AN EXISTING ALUMINUM WEB REPAIR. THE EXISTING REPAIR WERE REMOVED FOR INSPECTION OF UNDERLYING REPAIRS. AN ALUM DOUBLER WAS REINSTALLED ON THE WEB, ANGLES ON THE INNER CHORD, AND A STEEL ANGLE ON THE OUTER CHORD. REPAIRS WERE PER ER/A 379752-14AD, REV A.

Part: ANGLE — CRACKED (NR8 SLAT) · airframe 65,394 hrs · 49,825 cycles

FOUND ON MV2 CHECK, .75 INCH CRACK NR 8 SLAT COVE SKIN ANGLE BELOW THE ANTI-ICE DUCT. REPAIRED PER MM 57-54-000-8.

Part: DUCT — RUPTURED (NR 1 PYLON) · airframe 64,342 hrs · 49,092 cycles

ENG NR 1 STRUT OVERHEAT LIGHT ILLUMINATED IN CLIMB PASSING FL 250. COMPLETED WITH POM PROCEDURES, LIGHT REMAINED EXTINGUISH WITH THROTTLE AT IDLE. NR 1 BLEED SWITCH HAS NO EFFECT. DIVERTED TO DFW. FOUND HI STAGE PNEUMATIC -Y- DUCT IN PYLON RUPTURED. REPLACED SAME, ALSO REPLACED NR 1 ENG BLEED S/O VALVE AS PRECAUTIONARY. RAN ENG LEAK CKS GOOD.

Part: BATTERY — INOPERATIVE (CARGO BAY) · airframe 63,655 hrs · 48,618 cycles

FOUND RT AFT CARGO DOOR EMERGENCY LIGHT INOP. REMOVED AND REPLACED M957 BATTERY PACK. EMERGENCY LIGHTS OPS GOOD.

Part: ANGLE — CRACKED (TE FLAP) · airframe 63,353 hrs · 48,411 cycles

DURING SHOP VISIT, THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED 37 INCHES FROM THE I/B END. THE ANGLE WAS REPAIRED BY REPLACING A SECTION OF THE ANGLE AND SPLICING IT WITH A DOUBLER PER MM 57-52-0, FIG 802.

Part: ANGLE — CRACKED (TE FLAP) · airframe 63,353 hrs · 48,411 cycles

DURING SHOP VISIT, THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED 55 INCHES FROM THE I/B END. THE ANGLE WAS REPAIRED BY REPLACING A SECTION AND SPLICING PER MM 57-52-0, FIG 802.

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT CABIN EMERGENCY EXIT SIGN OVERHEAD INOP DURING LIGHTS TEST. REPLACED BATTERY PACK, OPS GOOD.

Part: SKIN — CRACKED (STR 22R STA 1233)

3/4 CRACK IN FUSELAGE SKIN STR 22R STA 1233. REPAIRED PER SRM 53-30-3 FIG 25.

Part: FSLG SKIN — CRKD (STA 1090)

FUSELAGE SKIN CRACKED FS1090 BELOW STRINGER 17L. REPAIRED PER SRM 53-30-3 FIG 26.

Part: RIB — CRACKED (#2 SLAT)

FOUND ON D1 LETTER CK, 1 INCH CRACK NR 2 SLAT NOSE RIB I/B SIDE OF ACTUATOR. REPAIRED PER MM 57-54-0.

Part: BATTERY PACK — DISCHARGED (CABIN)

ON L/O, FOUND LEFT EXTERIOR OVERWING EMERGENCY EXIT LIGHT STROBING. REPLACED BATTERY PACK, CKS OK.

Part: TRANSMITTER — FAILED (TE FLAPS)

OUTBOARD FLAPS SPLIT WHEN FLAPS RETRACTED FROM 5 DEGS. REPLACED RIGHT OUTBOARD FLAP TRANSMITTER.

Part: INDICATOR — MALFUNCTIONED (TE FLAPS)

WHEN FLAPS WERE POSITIONED TO FLAPS 2, THE LEFT AND RIGHT OUTBOARD SHOWED SLIGHT ASYMMETRY (ABOUT 1 NEEDLE WIDTH) RAN CHECKLIST AND LOWERED FLAPS WITH ALTERNATE FLAP SWITCHES. FLAPS LOWERED TO 30 ON BOTH OUTBOARD, BUT INBOARD NOW SHOWED A SLIGHT SPLIT(ABOUT 5). HOWEVER, THE NEEDLE EVENTUALLY VIBRATED (OR FLICKERED) TO NORMAL(30,30). REPLACED OUTBOARD FLAP INDICATOR. RAN FLAPS. INDICATION AND FLAPS CHECKED NORMAL.

Part: TIRE — FAILED (NR 1)

NR 1 TIRE BLOWN. REPLACED NR 1 WHEEL AND BRAKE. ALSO REPLACED NR 2 WHEEL.

Part: SWITCH — DIRTY (STAB TRIM)

TAKEOFF WARNING HORN SOUNDED DURING POWER UP AND TAKEOFF WAS ABORTED AT 10 KTS. WARNING HORN ITEMS CYCLED AND SOUNDED AGAIN ON SECOND ATTEMPT. FOUND UPPER STAB TRIM SWITCH STICKING. CLEANED AND LUBED SWITCH. TAKEOFF WARNING TEST NORMAL.

Part: DUCT — BROKEN (LOWER BODY)

LOWER AFT BODY OVERHEAT LIGHT ON. REPLACED BLOWN DUCT UNDER APU IN KEEL BEAM.

Part: SKIN — CORRODED (BS 950)

FUSELAGE SKIN FS 950C-950D, STRINGER 28L : REPAIR FOR CORROSION CUTOUT. THE FUSELAGE SKIN WAS FOUND CORRODED AT STRINGER 28L BETWEEN FS 950C AND 950D. THE DAMAGE WAS REMOVED WITH A 6.3 BY 1.5 CUTOUT IN THS SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 366214-14, REV A.

Part: FLOORBEAM — CORRODED (BS 1070)

CORROSION FOUND ON FLOORBEAM STA 1070 AT LBL 55 SEAT TRACK ATTACH POINT (MARKED). REPAIRED PER SRM 53-20-11 FIG 804A.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

EMER TRACK LTS DAMAGED AT 26C. RELAMPED AND REPLACED LENS. ON TEST FOUND AFT FLOOR TRACK LTS INOP. FOUND AFT TRACK LIGHTING PWR SUPPLY BAD. REPLACED PWR SUPPLY. TEST GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT OVERHEAD EMERGENCY EXIT SIGN INOP. REPLACED BATTERY PACK, OPS CK GOOD.

Part: FITTING — LOOSE (RT ELEVATOR)

HORIZONTAL STABILIZER, RT ELEVATOR, REPAIR FOR LOOSE HINGE FITTING. THE STA 81.44 HINGE FITTING ON THE RT ELEVATOR WAS FOUND. LOOSE DURING INSPECTIONS REQUIRED PER AD 96-06-05. THE LOOSE FITTING WAS TIGHTENED PER PROCEDURES IN BAC S/B 727-55-0089 AND DOCUMENTED PER ER/A 363884-14AD.

Part: DOORFRAME — CRACKED (BS 620)

THE C-1 CARGO DOOR OPENING AFT FRAME AT STA 620 WAS FOUND CRACKED JUST BELOW THE CARGO FLOOR LINE. THE DAMAGE CONSISTED OF AN APPROX 3.0 CRACK IN THE WEB AND A SEVERED INBOARD CHORD. THIS AREA WAS REPAIRED WITH A DOUBLER AND STRAPS, APPROVED BY FAA/DER FORM 8110-3, DER DESIGNATION SO-775, DTD 6-24-97.

Part: BATTERY — DISCHARGED (CABIN)

LT WING AFT EXTERIOR EMERGENCY LIGHT INOP. RELAMPED.

Part: ANGLE — CORROSION (PANEL 3448R)

FOUND CORROSION ON LOWER ATTACH ANGLE FOR ACCESS PANEL 3448R. REPAIRED PER MM 53-30-1.

Part: ANGLE — CRACKED (NR 6 LE SLAT)

FOUND A .50 INCH CRACK NR 6 L/E SLAT COVE SKIN ATTACH ANGLE AT OUTBOARD UPSTOP PAD. REPAIRED PER M/M 57-54-0, PAR. 12.

Part: LIGHT — MISSING (FLOOR TRACK)

EMERGENCY TRACK LIGHT FIXTURE MISSING. REPLACED SAME, NOW OK.

Part: SKIN — CRACKED (L1 DOOR)

FOUND ON A-1 LETTER CHECK, FORWARD SERVICE DOOR SKIN CRACKED AT UPPER FORWARD CORNER .50 INCH AT 2 RIVETS. REPAIRED PER M/M 52-12-0.

Part: SKIN — CRACKED (NR 7 SLAT)

FOUND ON A-1 LETTER CHECK, NR 7 SLAT COVE SKIN ATTACH ANGLE CRACKED .25 INCH AT TIA DUCT. REPAIRED PER M/M 57-54-0.

Part: RIB — CRACKED (NR 4 SLAT)

FOUND ON A-1 LETTER CHECK, CRACK IN NR 4 L/E SLAT NOSE RIB RADIUS OUTBOARD SIDE OF OUTBOARD TRACK. REPAIRED PER M/M 57-54-0.

Part: RETRACT MECH — OUT OF RIG (NLG DOOR)

AFTER TAKEOFF WITH GEAR HANDLE IN OFF POS, FELT AND HEARD LOUD THUMP 4 OR 5 TIMES AT APPROX 2 MIN INTERVALS. PROBLEM WENT AWAY WITH HANDLE IN UP POSITION. RIGGED AND ADJUSTED NOSE GEAR DOORS PER MM, OPERATION NORMAL.

Part: SPAR CHORD — CRACKED (NR 2 TE MIDFLAP)

DURING SHOP VISIT, THE NR 2 MIDFLAP AFT LOWER CHORD WAS FOUND CRACKED AT INBOARD AFT FLAP TRACK. THE CHORD WAS REPAIRED PER MM 57520.

Part: SPAR CHORD — CRACKED (NR 2 TE MIDFLAP)

DURING SHOP VISIT, NR 2 MIDFLAP AFT LOWER CHORD WAS FOUND TO BE CRACKED 55 INCHES FROM INBOARD END. THE CHORD WAS REPAIRED PER MM 57520.

Part: SPAR CHORD — CRACKED (NR 2 TE MIDFLAP)

DURING SHOP VISIT, THE NR 2 MIDFLAP AFT CHORD WAS FOUND CRACKED AT CUTOUT FOR INBOARD AFT FLAP DRIVE ROD. THE CHORD WAS REPAIRED PER MM 57520.

Part: SKIN — CRACKED (CARGO DOOR)

INNER DOOR SKIN CRACKED AT LIGHTNING HOLE. REPAIRED CRACK PER SRM 52-00-3 FIG 3. FOUND DURING SHOP INSPECTION NR 1 CARGO DOOR.

Part: SPAR — CRACKED (NR 3 TE MIDFLAP)

DURING HMV INSP, NR 3 MIDFLAP WAS FOUND WITH AFT SPAR CHORD CRACKED AT I/B QUADRANT CUTOUT. REPAIRD PER MM 57-52-0 PAGE 807.

Part: DOUBLER — CRACKED (NR 3 TE MIDFLAP)

DURING HMV SHOP INSP, NR 3 MIDFLAP AFT SPAR CHORD DOUBLER CRACKED AT I/B AFT FLAP TRACK. REPAIRED PER MM 57-52-0 PAGE 807.

Part: FRAME — MISDRILLED (BS 761)

DURING ACCOMPLISHMENT OF THE MODIFICATION TO THE OVER-WING EXIT FRAME AT STA 761 ON THE LEFT SIDE, THE ADDED FASTENER HOLES THROUGH THE REPAIR ANGLE WEB AND FRAME WERE OVERSIZED TO .25 INCH.

Part: RIB — CRACKED (NR 2 LE SLAT)

RIB CRACKED-NR 2 SLAT RIB MARKED NR 11 CRACKED AT LOWER ATTACH ANGLE. CORRECTION-FABRICATED REPAIR PER M/M 57-54-0, PG 805.

Part: RIB — CRACKED (NR 6 LE FLAP)

ATL - HMV, NR 6 SLAT I/B RIB AT INBOARD SLAT TRACK CRACKED IN LWR RADIUS. REMOVED FASTENERS FROM REPAIR AREA, FABRICATED REPAIR PER 57-54-0 FIG 805.

Part: SKIN — WORN (NR 4 SLAT)

UPON HMV, FOUND SKIN WORN ON SECTION OF SKIN UNDER LIFT FENCE NR 4 SLAT. REPAIRED PER MM 57-54-0 PG 817.

Part: GATE BEAM — CRACKED (PAX DOOR)

AT HMV, FWD ENTRY DOOR UPPER GATE BEAM CRACKED AT AFT CORNER STOP LUG. REPLACED UPPER GATE BEAM AND INSTALLED REPAIR PER MM 52-11-01.

Part: FLAP — CRACKED (NR 3)

DURING INSPECTION, FOUND NR 3 KRUEGER FLAP WITH TIME LIMITED REPAIR AT O/B GATE HINGE CUTOUT. REPAIRED PER MM 57-53-0.

Part: BUSHINGS — LOOSE (MLG STRUT DOOR)

ATL - HMV, NR 4 FLAP TRACK FWD HINGE FITTING FOR MLG STRUT DOOR HAS LOOSE BUSHINGS. REMOVED BUSHINGS, REAMED BORE TO .750, ACCOMPLISHED BUSHING REPLACEMENT PER MM 57-43-0.

Part: BUSHINGS — LOOSE (MLG STRUT DOOR)

ATL - HMV, NR 5 FLAP TRACK, FWD HINGE FITTING FOR MLG STRUT DOOR HAS LOOSE BUSHINGS. REMOVED BUSHINGS, REAMED BORE TO .750, ACCOMPLISHED BUSHING REPLACEMENT PER MM 57-43-0.

Part: SKIN — DAMAGED (FS 761)

WING SKIN, CENTER TANK UPPER SKIN STA 761 LBL 65, TWO EXISTING FASTENER HOLES IN THE WING CENTER SECTION UPPER PANEL WERE DAMAGED ON THE UNDERSIDE REQUIRING OVERSIZING. THE TWO HOLES ARE LOCATED AT FS 761 AT APPROX LBL 65. THE REPAIR OVERSIZES BOTH HOLES IN THE WING SKIN ONLY AND INSTALLS INTERFERENCE FIT BUSHINGS.

Part: SPAR — CRACKED (RT AILERON)

DURING INSPECTION, RT WING AILERON WAS FOUND WITH REAR SPAR CRACKED. REPAIRED PER SRM 51-40-3.

Part: SKIN — CRACKED (FS 1158-1183)

FUSELAGE SKIN REPAIR AT AFT LAVATORY SERVICE PANEL CUTOUT, FS 1158 TO FS 1183, BETWEEN STRINGERS 20L AND 24L. DURING THE ACCOMPLISHMENT OF EO 4-69078-3AD, THE INTERNAL BONDED DOUBLER WAS FOUND CRACKED AND CORRODED IN THE UPPER FWD CORNER OF THE AFT LAVATORY SERVICE PANEL. THE REPAIR CUTS OUT THE DAMAGE FROM THE STRINGER 20L SKIN LAP TO STR 23L FROM THE BS 1183 BUTT SPLICE TO APPROX FS 1158. THE REPAIR THEN INSERTS A SKIN REPLACEMENT SECTION AND A DOUBLER, SO THAT MTC CAN CONTINUE WITH EO 4-69078-3AD. REPAIRS ACCOMPLISHED PER DL ERA 302536-14.

Part: SKIN — CORRODED (BS 710/720)

HEAVY CORROSION WAS FOUND JUST FORWARD OF STA 720 AND OUTBOARD OF STR 28R AND, ALSO, AFT OF STA 710 AND OUTBOARD OF STR 27L. THERE ARE THREE EXISTING DOUBLERS IN THIS REPAIR AREA. THIS ER/A WILL REMOVE THE DAMAGED SECTION OF SKIN AND REPAIR THE DAMAGE WITH A SKIN SPLICE. REPAIRS ACCOMPLISHED PER DL ERA 302541-14AD.

Part: RIB — CRACKED (NR 7 LE SLAT)

ATL - HMV, RIB CRACKED NR 7 LE SLAT NR 10 RIB CRACKED ON TOP FLANGE. ROUTED OUT DAMAGE AND FABRICATED DOUBLER PER MM 57-54-0 PG 819. FABRICATED FILLER, INSTALLED DOUBLER AND FILLER PER M/M 57-54-0 PG 819.

Part: ANGLE — CRACKED (WING TE)

ANGLE CRACKED, WING TRAILING EDGE BELOW NR 8 SPOILER ATTACH BRACKET FOR ACTUATOR. STOP DRILLED CRACK, INSTALLED REPAIR PER M/M 57-20-22 PG 809.

Part: TRUNNION FTG — CORRODED (LT MLG TRUNNION)

UPON HMV, FOUND LT MLG FWD TRUNNION FITTING INNER FACES CORRODED. REMOVED BUSHINGS...BLENDED SURFACES WITHIN LIMITS PER M/M 57-43-0.

Part: FITTING — CORRODED (RT MLG)

RT MLG FWD TRUNNION FITTING INSIDE FACES CORRODED. ALSO, EVIDENCE OF CORROSION UNDER BUSHINGS. REMOVED BUSHINGS AND CORROSION, BORED HOLES, SPOTFACED HOLES WITHIN MM 57-43-0 LIMITS. MACHINED LOWER O/B BUSHINGS PER DRAWING NR 69-49502-7 AND MM 57-43-0 PG 403 NR 2. CADPLATED, ROTOPEENED, TREATED, PRIMED, INSTALLED BUSHINGS. MANUFACTURED, TREATED AND INSTALLED FILLERS. APPLIED TOP COAT, BMS 3-23 AND BMS 3-26 PER PS 900-2 NR 4.

Part: TRUNNION — CORRODED (NLG)

NOSE GEAR RT TRUNNION BORE CORRODED. CLEANED ATTACH BOLT HOLES, MACHINED BORE TO 2.525 TO REMOVE CORROSION. ROTOPEENED, TREATED, PRIMED, MFG BUSHINGS AND INSTALLED BUSHINGS PER MM 53-40-0.

Part: ANGLE — CRACKED (NR 2 LE FLAP)

ATL - HMV, ANGLE CRACKED NR 2 K-FLAP ACT MOUNT, INBD LOWER ANGLE IS CRACKED. REMOVED ANGLE, STOP DRILLED CRACK, DRILLED REPAIR DOUBLER PER MM 57-20-21 PG 811 AND INSTALLED REPAIR DOUBLER PER MM 57-20-21.

Part: ATTACH MOUNT — CORRODED (NLG)

NOSE LANDING GEAR LEFT ATTACH MOUNT CORRODED. CLEANED BOLT HOLES, MACHINED BORE TO 2.617, REMOVED CORROSION AND ROTOPEENED. TREATED, MANUFACTURED BUSHINGS, CAD BUSHING AND INSTALLED BUSHINGS PER MM 53-40-0.

Part: STIFFENER — CRACKED (LT WING)

FOUND ON F-1 LETTER CHECK - FRONT SPAR STIFFENERS CRACKED AT NR 4 LEADING EDGE SLAT, INBOARD TRACK ROLLER BOX. REPAIRED PER M/M 57-20-21.

Part: EEL — INOPERATIVE (CABIN)

INTERIOR EMERGENCY EXIT SIGN ABOVE LEFT FWD ENTRY DOOR DID NOT ILLUMINATE ON EMERGENCY EXIT LIGHTS CHECK. REPLACED EMERGENCY EXIT LIGHT ASSY AND BATTERIES. GRD CHECKS OK ON TEST.

Part: PACK — OVERHEAT (LEFT)

ON SHORT FINAL AND LANDING, HAD LEFT PACK OVERHEAT WITH SOME BURNING ODOR IN CABIN. FOUND COOLING FAN C/B TRIPPED. RESET C/B OPERATION TEST, NO TROUBLE FOUND, RETURNED TO SERVICE.

Part: BLKHD BEAM — CRACKED (FS 1183)

DURING LETTER CHECK, FOUND FS 1183 BULKHEAD VERTICAL BEAM AT RBL 8 WITH A 1 INCH CRACK. REPAIRED PER MM 53-11-0.

Part: SKIN CLIP — CORRODED (FS 1090)

DURRING LETTER CHECK, FOUND FS 1090 FRAME TO SKIN SHEAR TIE CORRODED ON ITS FWD SIDE AT STRINGERS 29R AND 28R. REPAIRED PER M/M 53-11-0 FIG 815.