N12125
Registered owner: UNITED AIRLINES INC, IL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| UNITED AIRLINES INC | Operator | 2021-09-27 – 2021-09-27 | Operator named in NTSB report |
| UNITED AIRLINES, INC. (CALA) | Operator | 2021-09-27 – 2021-09-27 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
EMERGENCY LIGHTS OPS TEST WITH THE TEST SWITCH PROCEDURE, FOUND EMERGENCY LIGHT INOP AT SEAT 27ABC OVERHEAD BIN, RELAMPED, NO HELP IAW AMM 33-51-00 NO. TWO ADJACENT (OPPOSITE SIDE) LIGHT ASSEMBLIES ARE INOPERATIVE ONLY SEAT 27ABC. APPLYING MEL 3351A APPROVED. REMOVED AND REPLACED AISLE LIGHT ASSEMBLY AND LAMP IAW AMM 33-51-00. NO FIX. REF WDM 33-51-14 FOR FURTHER TROUBLESHOOTING. APPLYING MEL 3351A. APPLIED STICKERS TO PANELS CLEANED CONTACTS NO HELP. FOUND DAMAGED FLANGE IN LIGHT ASSY. REMOVED AND REPLACED BULLNOSE EMERGENCY LIGHT ASSY IAW AMM 33-51-00. NO HELP. CHECKED FOR INCOMING VDC, NO POWER FOUND. REMOVED AND REPLACED BATTERY AND POWER SUPPLY IAW AMM 33-51-07. OPS CHKD GOOD.
ODOR ONLY HAPPENED IN COCKPIT, NO ODOR IN CABIN. ONCE IN CRUISE FOR 15-20 MINS & ONCE ON DESCENT FOR 15-20 MINUTES..ODOR WENT AWAY BOTH TIMES SDR REPORTABLE DISCREPANCY TROUBLESHOOTED AIR CONDITIONING SYSTEM IN REF WITH FIM TASK 21-00-01/301 STEP 3 PROCEDURE 1 ( C1A) HAVE TO REMOVED AND EXAMINE LEFT HEPA RECIRCULATION FAN FILTER. FOUND CODE FISH AND TOASTED BREAD IN OVEN CAUSING WARM WOOD ODOR. CLEANED OUT OVEN AND R&R LEFT HEPA RECIRCULATION FAN FILTER IAW AMM 21-25-02/401 . PERFORMED HIGH POWER BURN OUT AND NO SMELL WAS NOTED. OPS CHECK GOOD. PERFORMED SMOKE/ODOR IN FLIGHT DECK AND CABIN CONDITIONAL INSPECT IAW AMM AMM 05-51-58-910-801-C1.
FOR THE INTERIM REPAIR AT RH WING LOWER SKIN EDGE GOUGE DAMAGE AT WSTA 585, ACCOMPLISH PERMANENT REPAIR PER PART 3 OF THE LATEST REVISION OF ECRA #: 5720-03512 ON OR BEFORE 30-SEPT-2026. FOR THE INTERIM REPAIR AT RH WING LOWER SKIN EDGE GOUGE DAMAGE AT WSTA 585, ACCOMPLISH PERMANENT REPAIR PER PART 3 OF THE LATEST REVISION OF ECRA #: 5720-03512 ON OR BEFORE 30-SEPT-2026. NOT RII REF ECRA 5720-03512: "FOR THE INTERIM REPAIR AT RH WING LOWER SKIN EDGE GOUGE DAMAGE AT WSTA 585, ACCOMPLISH PERMANENT REPAIR PER PART 3 OF THE LATEST REVISION OF ECRA #: 5720-03512.
L1 DOOR CUTOUT MOD. THERE ARE DISCREPANCIES BETWEEN THE INSTALLATION DRAWING AND ACTUAL FASTENER LOCATIONS FOUND DURING LAYOUT OF DOUBLER AND TRIPLER. L1 DOOR SURROUND - REPAIR / PREVENTATIVE MODIFICATION PER EA 5330-04213 AND ECRA 5330-07490 VERIFIED L1 DOOR SURROUND - REPAIR / PREVENTATIVE MODIFICATION PER EA 5330-04213 AND ECRA 5330-07490 DOUBLER & TRIPLER REPAIR INSTALLATION TO THE L1 DOOR SURROUND FW D UPPER CORNER WAS INSTALLED PER EA 5330-04213 REV D WITH DEVIAT IONS NOTED IN EC/RA #: 5330-07490. ACCOMPLISH INSPECTION REQUIRE MENTS PER PART 2 OF THE LATEST REVISION OF EC/RA #: 5330-07490 A T FUSELAGE REPAIRED AREA (SKIN PANEL, BEAR STRAP, REPAIR DOUBLER & REPAIR TRIPLER) BETWEEN BS 333-355, STRINGER 5L AND #2 DOOR S TOP ON OR BEFORE AIRCRAFT REACHING 37,500 TOTAL FLIGHT CYCLES.
1R DOOR WILL NOT ARM REMOVED FOD, DOOR ARMS AND DISARMS NORMAL.
ENG OIL PRESS RIGHT ECIAS MESSAGE AT CRUISE PER QRH THE RIGHT E NGINE WAS SHUTDOWN ADDED 21 QTS OF ENGINE OIL TO THE #2 ENGINE. CLEANED AREA AND DRY MOTORED THE #2 ENGINE TO VERIFY OIL LEAK. FOUND THE #2 ENGINE OIL PRESSURE TRANSMITTER BRAIDED OIL LINE STREAMING OIL DUE TO CHAFE BETWEEN THE BRAIDED LINE AND THE TRANSMITTER ADAPTOR. SEE PICTURES. REFERENCE IPC 79-21-05-14 ITEM 70. ITEM 50 FOR THE ORING. PARTS ARE ON AOG WITH AN ETA OF 1600 LOCAL TIME. EICAS AUTO SNAPSHOT PIC. CREW STATED #2 ENG HAD POSITIVE OIL PRESSURE AT SHUTDOWN. DID NOT EXCEED 30 MIN TO LANDING. REPLACED PIPE ASSY P/N 556-1-15490-000. REF ENGINE MANUAL 72-00-61, SUBTASK 72-00-61-420-084. ACP ENG IDLE RUN LEAK TEST , REF AMM 71-00-00. NO LEAKS NOTED ON 5 MIN IDLE RUN. COMPLIED WITH L/P 3429480. WORK ACCOMPLISHED ON ADDITIONAL L/P3430288.
DOOR 4L TOMC REQUEST TO REMOVE DOOR SLIDE BUSSEL AND INSPECT ALL MECHANISMS AND INSTALLATIONS FOR DEFECTS. REF FUP 3198159 GAINED ACCESS TO ARMING/DISARMING LEVER & ITS ASSOCITED LINKAGES FOR DETAILED INSP REF AMM 25-66-10. FOUND NO LOOSE HARDWARE, BENT/BINDING RODS OR ANY OTHER DEFECTS. GIRT BAR TRACK WAS CLEANED AND LUBRICATED AFTER FINDING DEBRIS WITHIN THRESHOLD AREA AND FLOOR FITTINGS REF ECRA 2560-02189 REV E. AFTER CLEANING, FOUND NO BINDING OR OUT OF POS THAT WOULD CAUSE ARMING/DISARMING PROBLEM. REINSTALLED DOOR 4L BUSSEL REF AMM 25-66-01-404-044. OPS CHECK GOOD.
DOOR 4R DOES NOT APPEAR TO FULLY SEAT IN DISARM POSITION REMOVED BUSSEL. ICE BUILDUP ON GIRT BAR SLIDERS MELTED IN A FEW MINUTES. DOOR DISARMED FULLY.OPENED DOOR. CLEANED DOOR SILL AREA. CLOSED DOOR. VARIFIED GIRT BAR SLIDERS FULLY ENGAGE IN ARMED. INSTALLED BUSSEL. OPENED AND CLOSED-DOOR VARIFING ARM AND DISARMING IN NORMAL. SLIDE ARM LIGHT WORKS NORMAL.
EICAS CONT PNL CAUTION ON TO PAST 100KTS. REF FOUND C/B POPPED 115 VAC BUS R SECT 2 ON P32 PANEL. PERFORMED BPCU BITE PROCEDURE IN REFERENCE TO B757 FIM 24-20 FAULT TREE 801 BPCU BITE SHOWED NO EXISTING FAULTS OR FAULTS FOR THE INBOUND LEG REST BREAKER WITH EXTERNAL POWER APPLIED AND BREAKER DID NOT TRIP AND RIGHT BUS TIE NEVER WENT TO ISLN SO BTB ECS/MSG PAGE SHOWE MAINTENANCE MESSAGES "R ENG VIB MONITOR" AND "R EEC BITE" RIGHT ENGINE VIB MONITOR AND EEC AS WELL AS C2 EMP AND LOWER EICAS DISPLAY AND RIGHT EICAS COMPUTER RUN OF THE RIGHT AC BUS SECTION 1 AND BUS IS FEED BY THE RIGHT GENERATOR BREAKERS THAT WAS FOUND TRIPPED WHEN AIRCRAFT ARRIVED AT HANGAR IS RIGHT 115VAC SECTION 1 PARTS CHANGE INFO. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1331343 SN OFF 4321 BREAKER, CIRCUI OFF 99-2422-9-9003 4321 ON 99-2422-9-9003 5806 BREAKER, CIRCUI OFF 99-2422-9-9003 4321 ON 0000 IS GOOD CIRCUIT BREAKER IN FLIGHT SUSPECT C903 FAILED ON TAKEOFF REFERENCE B757 WDM 24-21-21 AND B757 WDM 24-51-21 C903 IS NOT IN STOCK DEN VISUSLLY INSPECTED LUGS ON GCB C903 AND CIRCUIT BREAKER RIGHT 115VAC BUS SECTION 1 CIRCUIT BREAKER C319 FOUND NO SIGNS OF DAMAGE REFERENCE B757 WDM 24-51-21 REPLACED THE RIGHT GENERATOR CONTROL BREAKER C903 IN REFERENCE TO B757 AMM 24-22-03-424-006 ACCOMPLISHED 10 MINUTE IDLE RUN WITH ALL PARAMETERS AND INDICATIONS NORMAL CYCLED RIGHT GEN ON AND OFF MULTIPLE TIMES AND SWAPPED BETWEEN SOURCES WITH NO ISSUES REFERENCE B757 AMM 71-00-00
AUTO LIGHT IN LAV 1L INTERMITENT REQUIRES TOO MUCH FORCE WHEN LOCKING DOOR TO TURN ON SUSPECT DOOR SWITCH, AUX AND DOME LIGHT OPERABLE. APPROVED NEF 3320AS COMPLY WITH DDP. FOUND LIGHT IN LAV 1L AND LOCKING MECHANISM TO BE OPERATING NORMALLY.
FWD LAV NOT ENOUGH WATER SWIRAL IN FLUSH TO EMPTY WASTE LAVS SERVICED, OPS CHECKS GOOD. ALL SERVICEABLE LAVS DUMPED AND SERVICED. OPERATIONAL CHECK OK. VERIFIED MID LAV TANKS IS EMPTY PER MEL.
RIGHT WING LANDING LIGHT PANEL 611AB HAS 1 EA FASTENER MISSING. QC COMPLETING MATERIALS NEEDED FOR EPLACE.RECORDS UPDATE -- DC SPEED TAPE APPLIED, COMPLIED WITH EC/RA:#:3340-01562. ON WALK AROUND FOUND R WING LANDING LIGHT ACCESS PANEL 611AB MISSING 1 EA FASTENER ON OUTBOARD SIDE. PER ECRA 3340-01562 COMPLY WITH INTERIM REPAIR PART 1. INITIATE DIP TO INPSPECT SPEED TAPE APPLIED EVERY FLIGHT CYCLE AND COMPLETE PERMANENT REPAIR PER PART 3 WITHIN 3 FLIGHT CYCLES. PERFORMED INTALLED SCREW AS REQUIRED ON RIGHT WING TAXI LIGHT COVER .
THIS IS A SUPPLEMENTAL REPORT FOR THE SAME CONTROL NUMBER SUBMITTED ON 7/25/22.PANEL BELOW OVERHEAD BIN BY SEAT 2E FELL DOWN FILLER PANEL MISSING TABS. R/R 12 CLIPS, ALL OPS CHK OK.
FWD CARGO LT TUNNEL LAV SERVICE PANEL HOUSING CORRODED AT DUCT A TTACH FLANGE. BS 700-720. TRANSCRIBED FROM HAECO NR 9284657. REMOVED AND REPLACED DOUBLER ONLAV SERVICE PAN BS700-720 PER B DWG 143N3412 REV G AND B757-200 SR, 51-40-02. HAECO GSO MECH V9 35006 INSP QC467
(SUPPORT TASK) AFT PIT AFT ACCESSORY AREA, WASTE SERVICE PAN COR RODED AT UPPER SURFACE BETWEEN BS 1680 AND 1700 AND BETWEEN STRI NGER S-26R AND STRINGER S-29R. TRANSCRIBED FROM HAECO NR 928591 0. REMOVED AND REPLACE DOUBLERON WASTE SERVICE PAN BS1680-1700 S26R S29R PER B DWG 146N3650 REV AH AND B757-200 SRM 51-40-02. HAE CO GSO MECH V935006 INSP QC467
(B757-35-3-0009) PASSENGER OXYGEN SYSTEM, ALTITUDE PRESSURE SWIT CH FAILS OPS CHECK. TRANSCRIBED FROM HAECO GSO NRC 9285968
SUPPORT TASK, MAIN CABIN STA 760 L/H FUSELAGE FRAME AT FLOORBEAM HAS A DRILL START, TRANSCRIBED FROM HAECO GSO NRC 9285440 REPAIRED DRILL START ON MAIN CABIN STA 760 L/H FUSELAGE FRAME AT FLOORBEAM IAW UAL ECRA 5332-01026 AND HAECO REO-G23725, HAECO G SO MECH V900579 INSP QC315
SUPPORT TASK-- MAIN CABIN SHEAR WEB STA 700-720 RBL25 REQUIRES F ABRICATION. TRANSCRIBED FROM HAECO GSO NRC 9285902 REMOVED AND REPLACED -4 SHEAR WEB IAW B757-200 SRM 51-40-02 AND BOEING DWG 143N5140 REV B. HAECO GSO MECH V917499 INSP QC302
(SUPPORT TASK) MAIN CABIN DECK PLATE STA 1716 RBL50 HAS CORROSIO N ON WEB, TRANSCRIBED FROM HAECO GSO NRC 9285434 REMOVED CORROSION ON THE AFT DECK PLATE AT STA 1716 RBL50. REMAI INSP QC302 NING THICKNESS FOUND TO BE .027, REMOVED .044, ORIG .071 PER B75 7-200 SRM 53-60-51 FOUND TO BE OUT OF LIMITS. REPAIRED AREA PER 53-60-51-2R-14 WEB SPLICE CUTOUT REPAIR. HAECO GSO MECH V934114
(B757-06-3-0246) LOWER FUSELAGE SKIN INTERNAL ANTENNA DOUBLER HA S CORROSION IN BULK PIT AT STA 1510 BETWEEN S28L AND 29L (MARKED ). TRANSCRIBED FROM N/R 9284791
(SUPPORT TASK) MAIN CABIN STA 1540 BETWEEN STRINGER 8-9 L/H FRAM E CRACKED AT OVER HEAD BIN ATTACH POINT, TRANSCRIBED FROM HAECO GSO NRC 9285436 RE-INSPECTED AT 12,000 FLIGHT CYCLES FROM REPAIR INSTALLATION OR INSPECTION REQUIRED AT INTERVALS OF 12,000 FLIGHT CYCLES. 50,000 AIRFRAME CYCLES, WHICHEVER COMES FIRST. DETAILED VISUAL REPAIRED AREA PER B575-200 SRM 53-00-07-2R-8, SEE INSPECTION REQUIREMENTS GIVEN IN TABLE 203/ REPAIR 8 ZONE 3.
SUPPORT TASK- MAIN CABIN FLOOR BEAM STA 365 RBL65 CORRODED ON UP PER SURFACE, TRANSCRIBED FROM HAECO GSO NRC 9285582 TRANSCRIBED FROM HAECO NR 9285582. REMOVED CORROSION ON BEAM UPPER CHORD RBL-12 TO RBL-65 IAW B757-200 SRM 53-00-51- FLOOR BEAM UPPER SURFACE AT STA 365 RBL-65 ORIGINAL MATERIAL 2R-8 REV - B. CREATED SFR# 1028268. HAECO GSO MECH V901427 .125. MATERIAL REMOVED .018. MATERIAL REMAINING .107 OUT OF INSP QC032. LIMITS IAW B757-200 SRM 53-00-51-1A-1 REPAIRED STA 365 FLOOR
(SUPPORT TASK) MAIN CABIN FWD OF STA 700 PANEL SUPPORT HAS CORRO SION ON UPPER SURFACE. REF HAECO GSO NRC 9285442 REMOVED CORROSION ON PANEL SUPPORT FWD OF STA 700 IAW B757- STA 680-700 IAW B757-200 SRM 51-40-02 AND BAC DWG 143N5400 200 SRM 53-00-51 ORIGINAL MATERIAL THICKNESS .056, REMOVED REV-. REMOVED DOT. TRANSCRIBED FROM HAECO NR 9285442. HAECO .036, MATERIAL .020 REMAINING OUT OF LIMITS IAW B757-200 GSO MECH V917499. SRM 53-00-51. REPLACED MAIN CABIN PANEL SUPPORT FROM STA
SUPPORT TASK- MAIN CABIN FLOOR BEAM T-CAP STA 720 RBL25-45 HAS C ORROSION ON UPPER SURFACE, TRANSCRIBED FROM HAECO GSO NRC 928497 5
B757-53-3-0579 CBN AFT WET FLOOR BEAM CORRODED AT FASTENER HOLE BS 1640, BL L3, REFERENCE HAECO GSO NR 9284816
SUPPORT TASK- MAIN CABIN FLOOR STA 720-740 RBL65 HAS CORROSION O N UPPER SURFACE. TRANSCRIBED FROM HAECO GSO NRC 9284976
SUPPORT TASK- MAIN CABIN STA 700-720 RBL65 GUTTER SUPPORT REQUIR ES REPLACEMENT DUE TO OFFSET CREATED BY FLOOR BEAM REPAIR. TRANS CRIBED FROM HAECO GSO NRC 9285579
SUPPORT TASK, MAIN CABIN STA 730 RBL24 SEAT TRACK SUPPORT HAS CO RROSION, TRANSCRIBED FROM HAECO GSO NRC 9285765
TRANSCRIBED FROM HAECO NR 9284825. B757-53-3-0579/CBN AFT WET AREA FLOOR SUPPORT CHANNEL CORRODED AT FASTENER HOLE BS 1675, BL 0. DOT: T679. REMOVED AND REPLACED FLOOR SUPPORT CHANNEL IAW B757-200 SRM 51-4 0-02 AND BAC DWG 146N5230 REV-. REMOVED AND REINSTALLED GUSSET I AW B757-200 SRM 51-40-02 AND BAC DWG 146N5230 REV-. REF HAECO G SO MECH V899876, INSP QC021
B757-53-3-0579- CABIN AFT WET AREA FLOOR WEB CORRODED AT FASTENE R HOLE BS1680 BL R4, TRANSCRIBED FROM HAECO GSO NRC 9284826
TRANSCRIBED FROM HAECO NR # 9285363. SUPPT. TASK: FWD CARGO DOOR EXTERIOR SKIN HAS REPAIR DOUBLER NEAR FWD BOTTOM CORNER 10 IN. FROM DOOR FWD EDGE, 11.75 IN. BELOW HANDLE (APPROX.). DOUBLER MEASURES 11 X 8 IN. FOUND IN GOOD CONDITION WITH NO OBVI OUS DISCREPANICES. REFER TO EA 5100-02345 REV E (OPS 12871) FOR REPAIR EVALUATION INSTRUCTIONS.
SUPPORT TASK; MAIN CABIN STA 1714 RBL 1 HAS CORROSION ON WEB (DE CK PLATE), TRANSCRIBED FROM HAECO GSO NRC 9285454 BLENDED AREA TO REMOVE CORROSION, FOUND TO BE OUT OF LIMITS CREATED SDR # 1027917. TRANSCRIBED FROM HAECO NR 9285454. HAECO IAW B757-200 SRM 53-60-51-2R-2. FABRICATED REPAIR DOUBLER IAW MECH INSP QC004. B757-200 SRM 53-60-51-2R-2. ALODINED, PRIMED REPAIR DOUBLER IAW SOPM 20-41-02. INSTALLED DOUBLER IAW B757-200 SRM 53-60-51-2R-2.
REF ECRA 5380-01304, NEED TO INITIATE A DTA DIP PER PART 1 STEP #2 IN REGARDS TO A REPAIR ON THE APB CENTER WEB & FWD LOWER CHORD. ACCOMPLISH INSPECTION REQUIREMENTS PER PART 2 ON OR BEFORE THE AIRCRAFT REACHES 50,000 TOTAL CYCLES. ITEM PLACED ON DIP. PER ECRA 5380-01304: INITIATE A DTA DIP TO STATE THE FOLLOWING: TOMC-APPROVAL FROM SC1ELBYC COMMENT ?ACCOMPLISH INSPECTION REQUIREMENTS PER PART 2 ON OR BEFORE THE AIRCRAFT REACHING 50,000 TOTAL CYCLES." QC REVIEWED QC REVIEWED INIT: SEE LP 7522459 T/A: 50,000 TAFC....CM U372988 RECORDS UPDATE.CM
SKIN WRINKLE AND WORN BETWEEN STA.1720 AND STA.1743 AFT OF APB BETWEEN S-27RT AND S-27LT. ( REF. L/P 7137422 ) REF COLLECTOR ECRA 5380-01303 FOR MAJOR REPAIR ACCOMPLISHED BY BOEING CONTRACTORS. NO FURTHER MX REQ''D AT THIS TIME. REF COLLECTOR ECRA 5380-01303 FOR MAJOR REPAIR ACCOMPLISHED BY BOEING CONTRACTORS. NO FURTHER MX REQ''D AT THIS TIME.
REF ECRA 5360-01621, NEED TO INITIATE A DTA DIP PER PART 1 STEP #7 TO ACCOMPLISH INSPECTION REQUIREMENTS PER PART 2 ON OR BEFORE THE AIRCRAFT REACHES 50,000 TOTAL CYCLES. ACCOMPLISH INSPECTION REQUIREMENTS PER PART 2 ON OR BEFORE THE AIRCRAFT REACHES 50,000 TOTAL CYCLES. ITEM PLACED ON DIP. PER ECRA 5360-01621: INITIATE A DTA DIP TO STATE THE FOLLOWING: TOMC-APPROVAL FROM SC1ELBYC COMMENT ?ACCOMPLISH INSPECTION REQUIREMENTS PER PART 2 ON OR BEFORE THE / AIRCRAFT REACHING 50,000 TOTAL CYCLES." Q/C REVIEWED. Q/C REVIEWED. INIT: SEE LP 7522176 T/A: 50,000 TAFC.........CM U372988 RECORDS UPDATE......CM
REF AVO#ESC210928-0125-3 STEP 4 DETAILED VISUAL INSPECTION- FOUND AFT PRESSURE BULKHEAD BUCKLED AT BL 0 BETWEEN STR.29R AND STR.29L. PREVIOUS WRITEUP LOCATION IS AT FUSELAGE STA. 1720.
PER CREW, POSSIBLE TAIL STRIKE ON LANDING. ATTACHED PICTURES OF DMAGED AREAS PERFORMED VISUAL INSPECTIONS STEPS 4&5 REF AVO# PERFORMED DETAIL VISUAL INSPECTION REF AVO ESC210928-0125-1 STEP ESC210928-0125-1. 4. NO INTERNAL STRUCTURE DAMAGE NOTED ON THE INTERIOR SIDE BTW STA 1701 TO 1720, BTW S24L TO S24R. FRAME AT STA.1743.85 CRACKED AND DENTED ABOVE STR.24L PREVIOUS WRITEUP IS PER AVO#ESC210928-0125-3 STEP 4. REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL REF AVO# ESC210928-0125-3 STEP 4 DETAILED VISUAL OF INTERNAL STRUCTURE-FOUND STRINGER TO FRAME CLIP AT STR. 24L BENT. STRUCTURE-FOUND STA. 1743.85 FRAME SHEAR TIE BENT BETWEEN STRUCTURE-WIRE HARNESS BRACKET FASTENERS SHEARED AT FRAME STRUCTURE-FRAME 1743.85 SHEAR TIE SEPERATED FROM SKIN BETWEEN STRUCTURE-2EA BRACKET FASTENERS SHEARED ON FRAME 1743.85 BET. STRUCTURE-STR. 29L BENT AT FRAME 1743.85. STRUCTURE-FOUND FRAME CRACKED,SHEARED, STR. 29R BENT, AND FRAME STRUCTURE-FOUND FRAME 1743.85 CRACKED AND BENT, SHEAR TIE BENT STR.24L AND 25L. STA.1743.85 BETWEEN STR. 25L AND 27L. STR. 27L AND 29L. STR. 29L AND 29R. AND SHEAR TIE SEPERATED FROM SKIN BET
FUSELAGE SKIN WORN AND GOUGED AT AND BETWEEN STA.1720 - STA.1712 AT S-29RT AND S-29LT FWD OF APB ( REF. L/P 7137422 ) C/W RII INSP OF INSURANCE CUT REF DISPOSITION A.2 STEP 1 AVO ESC 210928-0125-3. TRIMMED OUT DAMAGE SKIN AT STA. 1713 TO 1720, BETWEEN S29L & PERFORMED HFEC REF 51-00-19 OF TRIM OUT AT STA 1713 TO 1720 PERFORMED INSURANCE CUT OF THE TRIMMED OUT AREA REF S-29R. REF AVO# ESC210928-0125-3 DISPOSITION A.2. BETWEEN S29L AND S29R REF AVO ESC 210928-0125-3 DISPOSITION A.2 AVO#ESC210928-0125-3 OF DISPOSITION A.2 STEP 1. STEP 1 WITH NO REPORTABLE INDICATIONS. COMPLIED WITH VERIFICATION OF MATL FOR FILLER(0.050IN 2024T3), AND DOUBLER(0.063 2024T3) POS: 9271568/ 9726287 PER SKETCH IN AVO9203. C/W STEP 4 OF THE AVO 9203. NEED TO ACCOMPLISH STEP 1 AND 5. VERIFY MATERIAL ; FILLER .050 2024T3 CLAD PO# 9271568, DOUBLER ACCOMPLISHED DETAILED VISUAL INSPECTIONS OF UNDERLYING STRUCTURE .063 2024T3 CLAD PO# 9726287 REF PART-1( 6) OF AVO9203. AT STA. 1720 PER AVO#9203. NO STRUCTURAL DEFECTS FOUND AT THIS TIME. COMPLIED WITH STEP 5 OF AVO9203. PERFORMED HFEC OF UNDERLYING ACCOMPLISHED DETAILED VISUAL INSPECTIONS OF ALL UNDERLYING STRUCTURE WITHIN 10" OF CUTOUT WITH NO DEFECTS FOUND PER NTM STRUCTURE AROUND SECTION 46 SKIN AT STA.1712-1720, S-29L -S-29R. PART 6 51-00-19. NO FURTHER STRUCTURAL DAMAGE FOUND AT THIS TIME.
APU OIL QTY EICAS S THE APU OIL QUANTITY IS LOW NOTE: APU AUTO EVENT ALSO-APU OIL ADD ON EICAS STATUS PAGE ON ARRIVAL SERVICED APU OIL, RAN APU AND TWICE WAS AUTO SHUTDOWN. BITE THE CONTROLLER FAULTED LOW OIL PRESSURE SWITCH. REPLACE OIL PRESSURE SWITCH AND ALSO REPLACED APU OIL QUANTITY TRANSMITTER, RAN APU AND RAN OK. MM REF ARE TASK 49-94-02-402-008 AND TASK 49-49-04-402-010.
DENT ON FUSELAGE LEFT SIDE BETWEEN PRESSURE RELIF VALVE AND ELEV.STATIC PORT ABOUT 36" BELOW PUNCTURE THROUGH FUSELAGE SKIN AT APPROX STA 1445 AND 1" ABOVE S-25L REMOVED DAMAGE TO THE AFFECTED SKIN AERA STA 1445 AND STR 25 L REF 53-00-01. INSPECTION WILL NEED TO VERIFY SKIN THICKNESS AFTER REMOVAL OF DAMAGE. CRACKS.. SKIN THICKNESS AT REMOVAL AREA IS 0.43" DAMAGE TO SKIN (APPROX. 3" X 3") . NO INDICATION OF SKIN PERFORMED HEFC AND SKIN THICKNESS INSPECTION AFTER REMOVAL OF CUT OUT DAMAGED AERA REF SRM 53-00-01 REPAIR 29 PARA 4 A-D. PERFORMED HFEC OF DAMAGE CUTOUT. NO CRACKS DETECTED. REF. NDT PART 6 51-00-16 COMPLIED WITH SRM 53-00-01 REPAIR 29, PAR4 E-G. VERIFIED STEPS (4) E THRU G (NDT) HFEC AND HOLE PROBE INSP. REF. REPAIR 29 SRM 53-00-01 AND NDT PART 6 51-00-16 0.063" 2024-T3 P.O.# 8546450 AND THE -3 REPAIR FILLE
PDA 2 ON ARRIVAL FOUND #1 ENG IDG SERVICE DOOR MISSING C/W ECRA 7111-02030 PART 1 INTERIM REPAIR PERMANT REPAIR PER PART 3 DUE IN 1 CYCLE ADD EMP:U166362,U114806 PERMANENT REPAIR TO BE ACCOMPLISHED WITHIN 1 FLT CYCLE. TOMC-APPROVAL FROM SC1ELBYC COMMENT INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
FOUND LIFE RAFT AT SEAT 21ABC UNRAVELING WHILE PREFORMING PRE-DEPARTURE CHECK REMOVED AND REPLACED LIFE RAFT. REF. AMM SUBTASK 25-64-00-962-005 AT STOWAGE BIN 21ABC. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1317377 SN OFF 5326 RAFT, 46 MAN, 7 OFF 29-2581-9-0002 5326 ON 29-2581-9-0002 0384.
B757-53-3-0488 HEAVY BLUE WATER ON FLOOR BEAM STRUCTURE BELOW L1 ENTRY FLOOR BOARD AND BELOW LAV A. STA 297 TO STA 377 BL-0 TO L BL-62. REV VTSAA N/R 0027691. CLEANED,NEUTRALIZED, PERFORMED DUI OF AND APPLIED CIC TO FLOOR B EAM STRUCTURE BELOW L1 ENTRY FLOOR BOARD AND BELOW LAV STA 2971T O STA 377 BL-0 TO LBL-62 IAW EC/RA 2011-01000 REV AA. THIS IS TR ANSCRIBED INFORMATION ACCOMPLISHED AND RECORDED ON STSAA PAPER N /R 0027691, WORK ACCOMPLISHED BY MECH V923289,INSP BY V920309
(B757-53-3-0488) HEAVY BLUE WATER ON FLOORBEAM STRUCTURE BELOW R 1 ENTRY FLOORBEAM AND ABOVE NLG WW UPPER WEB STA 350 TO STA 365 BL-0 TO RBL 25. REF VTSAA NR 0027692. CLEANED, NEUTRALIZED, PERFORMED DVI AND APPLIED CIC TO FLOOR BEA M STRUCTURE BELOW R1 ENTRY FLOORBOARD AND ABOVE NLG WW UPPER WEB STA 350 TO STA 365 BL0 TO RBL 25 IAW ECRA 2011-01000, REV AA. T HIS IS TRANSCRIBED INFORMATION ACCOMPLISHED AND RECORDED ON VTSA A NR 0027692. WORK ACCOMPLISHED BY V923289 AND INSPECTED BY V892 744.
(B757-06-3-0371) CORROSION ON RIGHT FWD OVERWING EXIT DOOR SUPPO RT CHANNEL. REF VTSAA NR 0027751. BLENDED CORROSION AT RH FWD OVERWING EXIT DOOR SUPPORT CHANNEL A ND FOUND DIMENSIONS D=.025 W=1 L=2 TO BE OUT OF LIMITS IAW B757- 2 SRM 52-20-02 AD1 FIG 101 REMOVED AND REPLACED SUPPORT CHANNEL IAW DWG 414N1003 AND B757-2 SRM 51-40-02 PAR 4,5 AND 7. THIS IS TRANSCRIBED INFORMATION ACCOMPLISHED AND RECORDED ON VTSAA NR 00 27751 WORK ACCOMPLISHED BY V906232 AND INSPECTED BY V892744. INSPECTION COMPLETED AND ACCEPTED BY VT-SAA INSP V892744
CORROSION BETWEEN STA 900 BULKHEAD CHORD AND FUSELAGE SKIN IN AREA AFT OF FWD CARGO COMPARTMENT, STA 900 BETWEEN STR 27R. SKIN FOUND OUT OF LIMITS PER SRM 5300-00-01-A1. L+8.0,W+4.0,D-.120. CUTOUT DAMAGE AND ACCOMPLISHED REPAIR PER ECRA 5330-06451.
AFT CARGO DOOR CUTOUT UPPER FWD DOOR STOP FITTING BROKEN AT STA 1400 RG23. REMOVED BROKEN STOP FITTING WITH MISSING BEARING PLATE AND INSTALLED NEW STOP FITTING P/N 69-45580U3 AND BEARING PLATE P/N 140N2850-1 AT AFT CARGO DOOR CUTOUT UPPER FWD STA 1400 IAW SRM 51-40-02 PS 7 PARA D AND B DWG NR 143N8543 AND AMM 52-34-00-968-014.
AIRCRAFT DIVERTED INTO DEN (FLT1640 LAX/EWR) DUE TO SMELL LIKE GAS IN AFT GALLEY AREA. WARRANT SMOKE/ODOR CONDITION INSPECTION 05-51-58-910-801C RAN APU, PACKS TOGETHER AND ISOLATED. RAN ALL OVENS, COFFEEMAKERS, WARMERS, LIGHTS, LAV MOTORS. ACCOMPLISHED HIGH POWER RUN FOR 30 MINUTES WITH BLEEDS AND PACKS ISOLATED AND TOGETHER. COULD NOT DUPLICATE SMELL. NO DEFECTS FOUND. REF 5-51-58-910-801C.INSPECTED CABIN, CARGO PITS AND EE COMPARTMENT. NO FAULTS FOUND.
DUE TO RIGHT ENGINE HYDRAULIC LOST, AIRCRAFT REQUIRES RIGHT MAIN HYDRAULIC SYSTEM FLUSH AND FILTER REPLACEMENTS. REPLACED THE FILTER ELEMENTS IN THE PRESSURE AND CASE DRAIN MODULE FILTERS FOR THE RIGHT HYDRAULIC SYSTEM IAW AMM 29-11-00, PAGEBLOCK 201, CONDITION 2. FLUSHED THE HYDRAULIC PRESSURE/CASE DRAIN LINE AND R & R THE PRESSURE AND CASE DRAIN FILTERS IAW AMM 29-11-17-404-027-17-404-027. PERFORMED LEAK CHECK ON RIGHT HYD PRESSURE AND CASE DRAIN FILTERS IAW AMM 29-11. NO LEAKS NOTED. MAIN CAUSE LEAK WAS THE RT ENGINE THRUST REVERSER OTBD ACTUATOR.
AFT RIGHT EXIT DOOR MISSING SLIDE ARM LIGHT. REPLACED MISSING LENSE ON AFT RT EXIT DOOR SLIDE ARM LIGHT,OPS CHECKED NORMAL.
EMERGENCY EXIT SIGN IN CENTER AISLE AFT COACH IS MISSING PLASTIC COVER AT BOTTOM OF SIGN. RE-INSTALLED AFT EMERGENCY EXIT LENS COVER. OK TO CONT
AFTER TAKEOFF, SHORTLY AFTER GEAR RETRACT, RECEIVED A FIRST EICAS MESSAGE ALT DISAGREE,THEN AIRSPEED DISAGREE, THEN RUDDER RATIO, MACH/SPEED TRIM, THEN BOTH LT & RT EEC STATUS MESSAGE, ELEVATOR ASYM. EMERGENCY DECLARED. LANDING WAS MADE. TAXIING IN, WITH EXCEPTION OF EEC MESSAGES, THE ABOVE EICAS MESSAGES WERE NO LONGER DISPLAYED. TROUBLESHOOTING FOUND RIGHT ADC AT FAULT. R & R IAW MM 34-12-01-024-001. ALSO PERFORMED TEST 30. NO FAULTS AT THIS TIME
21A LOWER EMER EXIT SIGN IS HANGING BY WIRES. RESECURED EXIT SIGN. OPS GOOD.
ON ARRIVAL DISCOVERED FUSELAGE SKIN TORN, ONE INCH LONG, BS 293 BETWEEN STRINGERS 21 - 22R. REPAIRED IAW AVO 125-17-04-04-01, STEP 4.
AFT CARGO DOOR LOWER END, AFT TEE STIFFENER IS CORRODED. FOR PREVIOUS WORK ACCOMPLISHED SEE WIPS ABOVE. R & R AFT CARGO DOOR LOWER END AFT TEE STIFFENER IAW DWG 146N6603 & SRM 51-40-02.
CENTER INTERCOSTAL WEB ANGLE ATTACHES ON AFT CARGO DOOR LOWER END IS CORRODED. FOR PREVIOUS WORK ACCOMPLISHED SEE WIPS ABOVE. INSTALLED NEW CTR INTERCOSTAL WEB AT AFT CARGO DOOR IAW DWG 146N6 603 & SRM 51-40-02.
CENTER INTERCOSTAL ANGLE ON AFT CARGO DOOR LOWER END IS CORRODED OUT OF LIMITS. FOR PREVIOUS WORK ACCOMPLISHED SEE WIPS ABOVE. INSTALLED NEW CTR INTERCOSTAL ANGLE ASSEMBLY IAW DWG 146N6603 & SRM 51-40-02.
FORWARD CARGO COMPARTMENT, LT FRAME IS DENTED AT STATION 700 ABOVE STRINGER 23L. CUT OUT DAMAGED AREA OF FRAME & INSTALLED REPAIR DOUBLER & INITIATED A ZONE 2 DIP TO REINSPECT AT 25K FLIGHT CYCLES AFTER INSTALLATION OR 50K AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST & EVERY 11K FLIGHT CYCLES THEREAFTER CONTROL 38425 REF SRM 53-00-07 REPAIR 5.
FORWARD CARGO COMPARTMENT, RT FRAME DENTED AT STATION 680, ABOVE STRINGER 24L. CUT OUT DAMAGED AREA OF FRAME & INSTALLED REPAIR DOUBLER & INITIATED A ZONE 2 DIP TO REINSPECT AT 25K FLIGHT CYCLES AFTER REPAIR INSTALLATION OR 50K AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST & EVERY 11K FLIGHT CYCLES THEREAFTER CONTROL 38424 REF SRM 53-00-07 REPAIR 5.
FORWARD CARGO COMPARTMENT, LT FRAME IS DENTED AT STATION 800 ABOVE STRINGER 24L. CUT OUT DAMAGED AREA OF FRAME & INSTALLED REPAIR DOUBLER & INITIATED A ZONE 1 DIP TO REINSPECT AT 37,500 AFTER REPAIR INSTALLATION OR 50K AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST & EVERY 12K THEREAFTER CONTROL 38423 REF SRM 53-00-07 REPAIR 5.
MAIN CABIN FLOOR STRUCTURE FLOORBEAM 345 HAS CORROSION IN SEVERAL AREAS, FROM BL 0 TO LBL 1. SEE WIP & TASK STEPS FOR REPAIR OF FLOORBEAM AT STATION 345, BETWEEN LBL 51.8 & RBL-54.1 IAW SRM 53-00-51 REPAIR 10 & ECRA 5 310-06644 REV A.
FORWARD CARGO COMPARTMENT, LT FRAME IS DENTED AT STATION 660, ABOVE STRINGER 23L, D9244 WAS USED FOR SCEPTER ENTRY ONLY. CUT OUT DAMAGED AREA & INSTALLED REPAIR DOUBLER & INITIATED A ZONE 2 DIP TO INSPECT FRAME REPAIR AT 25000 FLIGHT CYCLE AFTER INSTALLATION OR 50000 AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST. REPEAT INSPECTION AT 11000, CONTROL NUMBER 3831 3 IAW SRM 53-00-07 REPAIR 5.
FORWARD CARGO COMPARTMENT, RT FRAME IS DENTED AT STATION 700, ABOVE STRINGER 24R, D9244 USED FOR SCEPTER PURPOSES ONLY. CUT OUT DAMAGED AREA OF FRAME & INSTALLED REPAIR DOUBLER & INITIATED A ZONE 2 DIP TO INSPECT REPAIR AT 25000 FLIGHT CYCLES AFTER REPAIR INSTALLATION OR 50000 AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST & INSPECT EVERY 11000 FLIGHT CYCLES THEREAFTER DIP CONTROL 38316 IAW SRM 53-00-07 REPAIR 5.
ABB FRAME AT STATION 1400, STRINGER 25 LT SHOWS DENT. INSTALLED FRAME REPAIR, TWO EACH STRINGER CLIPS, COLD WORKED TWO EACH HOLES & APPLIED CIC IAW SRM 53-00-07.
CABIN INTERIOR, LT SIDEWALL FRAME AT STATION 1580 SHOWS SIGN OF CRACK AT FASTENER, BETWEEN STRINGER 8L & 9L. CUT OUT DAMAGE & INSTALLED REPAIR DOUBLERS IAW SRM 53-00-07 REPAIR 1. INITIATED DIP FOR DETAIL VISUAL INSPECTIONS 12000 FC FROM REPAIR INSTALLATION, OR 50000 AIRFRAME FC, WHICHEVER COMES FIRST IAW SRM 53-00-07 REPAIR 1 TABLE 203 ZONE 3 PAGE 207. ACCOMPLISH INSPECTION 12,000 FC FROM REPAIR OR 50,000 TOTAL AIRFRAME FC WHICHEVER OCCURS FIRST & REPEAT INSPECTIONS EVERY 12,000 FC THEREAFTER.
CABIN INTERIOR, RT SIDEWALL FRAME AT STATION 800, SHOWS SIGN OF A CRACK AT FASTENER, BETWEEN STRINGER 8R & 9R, FOR SFR ENTRY PURPOSES ONLY. REPAIRED CABIN RT FRAME IAW SRM 53-00-07 REPAIR 1.
FLOORBEAM AT STATION 720 HAS CORROSION, FROM APPROX RBL 24 - 48. REPAIRED LOWEST ON FLOORBEAM STATION 720, AT APPROX. RBL 24 - 43 IAW SRM 53-00-51 REPAIR 11.
CABIN, AFT ENTRY, PRESS DECK AT STATION 1680, TOP SURFACE HAS CORROSION FROM RBL 25 - LBL 25. FABRICATED & INSTALLED DOUBLER REPAIR AT PRESS DECK, STATION 1680, RBL 7 - RBL 9 IAW SRM 53-60-51 REPAIR 2.
THREE SMALL DENTS IN AFT CARGO DOOR SKIN, APPROX 17" FROM FWD EDGE & 7" FROM LOWER EDGE. ACCOMPLISHED A REPAIR ON AFT CARGO DOOR DENTS IAW SRM 52-30-01 REPAIR 4. REQUIRE REPEAT INSPECTION, LFEC, EVERY 3000 FLIGHT CYCLES IAW NDT PART 6 53-00-06 IAW SRM 52-30-01 REPAIR 4 TABLE IV CATEGORY B, AFT CARGO DOOR SOURCE DOCUMENT 52-30-01. INSPECTION THRESHOLD 37,500 TOTAL DOOR FLIGHT CYCLES FROM DATE OF DELIVERY & THEREAFTER 3,000 FLIGHT CYCLE REPEAT INSPECTIONS INTERVAL.
EMERGENCY LIGHTS AT FIRST CLASS SEATS ARE INOPERATIVE. REPLACED EMER LIGHT BATTERY PACK M731. PERFORMED AN OPERATIONAL TEST, FOUND NORMAL IAW AMM 33-51-07.
MCP ALT SELECTOR WILL NOT SELECT OR HOLD ALT UN SELECTABLE. R & R MCP IAW MM 22-11-02. PERFORM FIM TASK 22-0 3-00 815-829 TEST 4, TEST PASSED. PERFORMED TEST 30 IAW MM 22-00-02-201, NO FAULTS FOUND. ACFT REMAINS FULL CAT CAPABILITY. OK FOR SERVICE. ROTABLE PARTS CHANGE WAS INDICATED TT 1659141 SN OFF 02711 PANEL, MODE CON OFF 99-2211-9-0003 2711 ON 99-2211-9-0003 2918.
DURING CLIMB BETWEEN FL180 & FL230 RT ENG BEGAN SURGING 1.66 - 1.69 EPR. ALL ENG PARAMETERS FOLLOWED ACFT DUCT PRESS SPLIT 35R 50L. WHEN DUCT PRESS EVENED SURGE STOPPED FLUCTUATION 1.66 & 1.69 EPR. PERFORMED POWER PLANT INSP IAW MM 71-00-00-206-007-R00. NO DEFECTS NOTED AT THIS TIME.
EXPERIENCE LOSS OF CENTER HYD FLUID WHILE VECTORING FOR APPROACH IAW LOG PAGE 7444864. FOUND ACMP FOR THE CENTER SYSTEM C2 LEAKING. R & R CENTER ACMP PUMP IN C2 POSITION IAW MM 29-11-02-404-016, NO LEAKS NOTED
NR 2 ENG PYLON MID SPAR FITTING LWR INBD AFT BOLT HAS SHIM MIGRATION. PERFORMED INTERIM REPAIR REF ECRA 5450-01673.
FASTENER INSTALLED WITH MINIMUM EDGE DISTANCE IN REF TO EXISTING FASTENER HOLE FROM PREVIOUS INTERIM REPAIR STA 205 JUST ABOVE S18L. CUT OUT DAMAGE AND INSTALLED A REPAIR DOUBLER ON THE INTERCOSTAL AND INSTALLED REPAIR DOUBLERS ON THE FUSELAGE SKIN.
EMERGENCY AISLE PATH LIGHTING FROM ROW 15 THRU 25 INOP. FOUND PINCHED WIRES AT ROW 23ABC SEAT TRACK GOING TO AISLE IND MODULES (L9043) REF WDM 33-51-22. WIRES SHORTED TO GND. REPAIRED WIRES PER SWP 20-10-13. OPS CHECK GOOD. IDT-QC 303.
LEFT SIDE OF FUSELAGE HAS A DENT APPROXIMATELY 19 INCHES LONG FROM STA 400 TO STA 420 BETWEEN STR 16L AND STR 17L. CUT OUT DAMAGE AND INSTALLED REPAIR DOUBLE AND TRIPLER PER ECRA 5330-03958 PART 1: INTERIM REPAIR STEPS 1-18 INITIATING A DIP TO ACCOMPLISH A PERMANENT REPAIR WITHIN 37,500 FLIGHT CYCLES. PLANNING CONTACT ENGINEERING AFTER 30,000 BUT BEFORE 31,000 FLIGHT CYCLES. (53-DIP CONTROL NR 01175) ACCOMPLISH A PERMANENT REPAIR WITHIN 37,500 TOTAL AIRCRAFT FLIGHT CYCLES.
DRILL DAMAGE LOCATED ON FUSELAGE SKIN, CROWN AREA, BETWEEN STATION 460 TO 480, STRINGERS S-2R AND S3-R. REPAIRED FUSELAGE SKIN BETWEEN STATION 460 TO 480, S-2R AND S3-R, PER B757 SRM 53-00-01, REPAIR 3.
THE AIRCRAFT SUSTAINED LIGHTNING STRIKE DAMAGE TO THE FUSELAGE SKIN AT STA 199 LT ABOVE THE LAP SPLICE S20L. AN INTERIM REPAIR WAS INSTALLED IAW PART 1A OF ECRA 5330-03537, REV A. A DIP WAS ISSUED TO REINSPECT THE AREA IAW PART 2 PRIOR TO THE ACCOMPLISHMENT OF 37,000 FLIGHT CYCLES AND THEREAFTER AT INTERVALS NOT TO EXCEED 12,000 FLIGHT CYCLES.
INSPECTION FOUND LIGHTNING DAMAGE AT FASTENER BS 202 BETWEEN S18L AND S19L. AN INTERIM REPAIR WAS PERFORMED IAW ECRA 5330-03537, REV A, PART 1A. A DIP WAS ISSUED TO REINSPECT THE AREA PRIOR TO ACCOMPLISHMENT OF 37,500 FLIGHT CYCLES AND THEREAFTER AT INTERVALS NOT TO EXCEED 12,000 FLIGHT CYCLES.
INSPECTION FOUND A 6" CRACK IN RT WING FIXED LEADING EDGE SKIN PANEL UPPER SURFACE AT WS 418. PERFORMED OPERATION 04 OF EA 5731-01010 AND REPAIRED THE CRACKED AREA IAW SRM 51-70-17 AND ATTACHED LAYUP PROCEDURE WORK CARD, COMPOSITE REPAIR WITHOUT CORE REPLACEMENT.
INSPECTION FOUND AN 8" CRACK IN LT WING FIXED LEADING EDGE SKIN PANEL UPPER SURFACE AT WS 425.5. PERFORMED OPERATION 04 OF EA 5731-01010 AND REPAIRED CRACKED AREA IAW SRM 51-70-17 AND ATTACHED LAYUP PROCEDURE WORK CARD (COMPOSITE REPAIR WITHOUT CORE REPLACEMENT).
STRINGER DAMAGED AT S-16L BETWEEN STA 620-640. REPAIRED STRINGER PER SRM 53-00-03.
DEFORMED SKIN AT STA 620/640. INSTALLED DOUBLER PER ECRA 5330-03433A.
TWO DENTS IN FUSELAGE IN FRONT OF L-2 DOOR. INSTALLED DOUBLER PER ECRA 5330-03433.
INSPECTION FOUND A 9 INCH CRACK IN LT WING LEADING EDGE SKIN AT OSS 450.0. THE SKIN WAS REPAIRED IAW EA 5731-01010, REV D.
INSPECTION FOUND A 9 INCH CRACK IN RT WING LEADING EDGE SKIN AT OSS 441.0. THE SKIN WAS REPAIRED IAW EA 5731-01010, REV D.
THE LT EMERGENCY ESCAPE SLIDE FAILED TEST 1. TROUBLESHOOTING PER FIM 25-65-00 FOUND CANNON PLUG D40828 AT LT EMERGENCY HATCH DISARM PANEL HAD LITE SURFACE CORROSION ON SEVERAL PINS. THE CONNECTOR WAS CLEANED AND RECONNECTED AND SYSTEM TESTED NORMAL.
A LEAF SPRING FOR L-2 DOOR GIRT BAR WAS FOUND BROKEN DURING PERFORMANCE OF FCD 2560-02033, B757-200/-300 GIRT BAR - INSPECT FOR PRESENCE AND CONDITION WHILE AT LAX. THE BROKEN SPRING PERMITS THE POSSIBILITY THAT THE SLIDE MIGHT NOT PERFORM ITS INTENDED FUNCTION WHEN OPERATED. THE LEAF SPRING WAS REPLACED.