N13138
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 | 2023-02-09 – 2023-02-09 | Operator named in NTSB report |
| UNITED AIRLINES, INC. (CALA) | Operator | 2023-02-09 – 2023-02-09 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
R4 DOOR INNER SKIN FWD SIDE HAS A CRACK AT UPPER HINGE ARM CUTOUT REPAIRED R4 DOOR SKIN REF ECRA 5310-03523 REPAIRED R4 DOOR SKIN REF ECRA 5210-03523
EMERGENCY LIGHTS SWITCH, LIGHT COVER MISSING ON OVERHEAD. REPLACED DEFECTIVE LENS CAP FOR ARMED ANNUNCIATOR, CHKD OKAY.
ENGINEERING WAS NOTIFIED BY THE FAA THAT THE RVSM ALTITUDE KEEPI NG IS NOT WITHIN LIMITS. ENGINEERING REQUESTS TO PERFORM THE FO LLOWING CHECKS: AMM TASK 51-10-00-206-025 STATIC PORT SKIN WAVINESS, AMM TASK 34-12-00-735-013 SYSTEM TEST - AIR DATA COMPUTING SYSTEM; ALSO VISUALLY INSPECT THE AOA VANES FOR ANY DAMAGE, IF A LL TESTS PASS AND NO DAMAGE TO STATIC PORT SKIN OR AOA VANES IS FOUND PLEASE REPLACE ADC#1 AND #2 PER AMM 34-12-01. REPORT ANY F INDINGS IN THIS LOG. CARRIED BY ELB SELECTED SDR UPON FURTHER EVAL NO DMG WAS FOUND TO STATIC PORT SKINS. ACCOMPLISHED AMM TASK 51-10-00-206-025 AND DETERMINED STATC PORT ADD EMP:415578 SKIN WAVINESS IS WITHIN LIMITS.
R2 DOOR WILL NOT ARM. REMOVED FOD FROM UNDER GIRT, SLIDE ARMS AND DISARMS NORMAL. IAW AMM 52-11-01.
EMERGENCY LIGHTS - OPERATIONAL TEST WITH THE TEST SWITCH PROCEDURE - OVERHEAD BIN EMERGENCY EXIT LAMP INOP ROW 29 DEF RELAMPED EXIT LAMP @29 IN REF TO AMM 33-51-00, OPS CHECK SATISFACTORY, OK TO CONTINUE PARTS USED: 00-0596-3-2874, QTY :1
4R DOOR SLIDE PRESSURE GAGE IN THE RED FOUND SLIDE PRES OK FO SVC PER 25-66-01-206-041
EMER LIGHTS PANEL UNARMED LIGHT IS LOOSE AND FALLS OUT. REMOVED EMERGENCY LIGHT/PASSENGER OXYGEN CONTROL PANEL. INSTALLED NEW LIGHTED INDICATOR BASE ASSEMBLY. REINSTALLED CONTROL PANEL. UNARMED LIGHT OPERATES NORMAL; EMERGENCY LIGHTS OPERATE NORMAL. REF AMM 33-51-08/401 AND AMM 33-51-00/501.
1L DOOR GASH ABOVE SLIDE COVER FOUND DAMAGE TO DOOR 1L SLIDE COVER IN UPPER LEFT CORNER GOING THROUGH THE INNER LAYER. REMOVED AND REPLACED L1 DOOR SLIDE COVER ASSY P/N 416N2100-723SP. REF IPC 25-66-01-01D. OK TO CONTINUE.
PDA 2 RT GREEN NAV LIGHT MISSING COVER AND GREEN LENS (DUPLICATE OF LOG 9822008) ADDING PHOTOS REPLACED GREEN LENS ASSY ON RH POSITION LIGHT. REF AMM 33-43-01-800-801-C1.
INSTALED SAFETY PIN IN ESCAPE SLIDE AT DR-4L FOR MX. REMOVED AND STOW SAFETY PIN AT DR-4L REF AMM 25-66-11.
DOOR 4L SLIDE LIGHT WILL NOT EXTINGUISH WHEN DOOR IS DISARMED REQUESTING MEL . COMPLIED WITH MEL , CONFIRMED GRITBAR OPERATIONAL. REMOVED SLIDE LIGHT INDICATOR BULB OFF. ESCAPE SLIDE GIRT BAR ENGAGEMENT LIGHT DOOR 4L - MEL 2566U PLACED ON MEL. REMOVED AND REPLACED DR-4L FWD AND AFT PROX SENSOR, OPS CHECK GOOD REF AMM 25-66-11. PARTS USED: 19-2400-3-0020,QTY :1
JET BRIDGE MALFUNCTIONED AND CONTACTED FUSELAGE, FOUND DENT AT STRINGER 16L APPROX 4 FEET FROM LEFT WING INSPECTION LIGHT PICS UPDATE WITH MEASUREMENTS DAMAGE IS FORWARD OF THE L2 DOOR. DENT FOUND TO BE ON STRINGER 16L @ STATION 611 (SEE SRM 53-00-01-1A-1 SHEET 5 DETAIL 3) DAMAGE WAS 2.250 WIDE X .071 DEPTH. DAMAGE BEING ON STRINGER PUTS IT OUT OF LIMITS (SEE SRM 53-00-01-1A-1 SHEET 5 DETAIL 3.) ACP. HFEC OF AFFECTED AREA, EXTERNAL SURFACE, NO CRACKS DETECTED, REF. NDT PT. 6, 51-00-19. ITEM LOCKED OPEN FOR MX FERRY FROM ORD TO MCO MX FERRY COMPLETE
ACCOMPLISH ACFT 0138 AVO12133 FUSELAGE SKIN DAMAGE AT STA 1862. ACP HFEC INSPECT THE EDGE OF THE SKIN TRIM PER 757 NDT MANUAL, ACP HFEC INSPECT ALL EXISTING FASTENER HOLES COMMON TO THE SKIN ACP AVO12133, ITEM 4. (A.) AND (B). VISUALLY INSPECT THE AREA TRIMMED OUT DAMAGE REFERENCING AVO12133 STEP 1. PART 6, 51-00-01 OR 51-00-19 TO ENSURE NO CRACKS EXIST. PER AVO REPAIR PER BOEING 757 NDT MANUAL, PART 6, 51-00-16 TO ENSURE NO UNDER THE REPAIR FOR FURTHER DAMAGE TO SUBSTRUCTURE. IF 12133 ITEM 2. CRACKS EXIST, PER AVO 12133, ITEM 3. DISCREPANCIES ARE FOUND, CONTACT ENGINEERING WITH THE DETAILS. ACPD NDT OF CUT OUT AND HOLE ROTO-PROBE PER AVO 012133 STEP 2 & 3 AT STA 1862 ONLY. REF B757 NDT MAN PART 6, 51-00-01 AND 51-00-16. ALSO ACPD STEP 4 INSP OF CORD VISUALLY AND NDT PART 6, 51-00-01. NO CKS OR DAMAGE. STARTED TO MFG FILLER .063 THICK 7075 T6 P.O. # 3051564330 AS REMANUFACTURED FILLER OUT OF .071 THICK 7075 T6 P.O. # 3944524 DRILLED FIELD FASTENERS INTO DOUBLER AND PICKED UP ALL HOLES TO PER ORIGINAL SKIN THICNESS.PICKED UP EXISTING FASTENER HOLES. FINAL SIZE AND COUNTERSINKED REFERENCING AVO12133 STEP 5. STARTED MFG OF DOUBLER FROM .071 THICK 7075 T6 P.O. #3944514. PICKED UP EXISTING HOLES STARTED TO LAYOUT PATTERN. REF AVO12133 COMPLETED MFG OF DOUBLER AND FILLER . P. O. FOR MATERIAL # ACP''D INSPECTION ITEM, VERIFIED REPAIR MATERIAL P.O # FOR TREATED AND PRIMED REPAIR AREA AND PARTS PER AVO12133 ACP''D INSPECTION ITEM, CLEARED AREA FOR REPAIR INSTALLATION.
CREW REPORTED TAIL STRIKE ON DEPARTURE. SFO-SFO FUNCTIONAL FLIGHT. CREW DEBRIEF: PILOT REPORTED TAIL STRIKE ON DEPARTURE FROM SFO ADDITIONAL PHOTOS TO SFO. THEY HEARD AND FELT STRIKE AS THEY ROTATED AND WERE CALLING FOR GEAR UP. DATA PROVIDED WAS V2 WAS 127, ROTATE 115-122 AND 146 TAKE OFF WEIGHT. ACCOMPLISHED INSP. STEP 4 (A) AND STEP 4(B) PER AMM ACCOMPLISHED INSPECTION OF THE UPPER FUSELAGE STRUCTURE AFT OF ACCOMPLISHED INSPECTION UP TO STEP 2 D (1)(E). SYSTEM TEST FOR 05-51-32-212-011 CREATED LOG PAGES WING SPARS PER AMM 05-51-32-212-012 ITEM 4 (C). NO DEFECTS THE STABILIZER POSITION INDICATION SYSTEM NEEDS TO BE FOUND. ACCOMPLISHED REF. AMM 5-51-32-212-011 ACCOMPLISHED STABILIZER TRIM POSITION INDICATING SYSTEM TEST REF AMM 27-48-00/501 AMM 05-51-32-212-011 TAIL STRIKE INSPECTON STEP 2.D.(1)(F). NO DISCREPANCIES NOTED.
CREW REPORTED TAIL STRIKE ON DEPARTURE. SFO-SFO FUNCTIONAL FLIGHT. CREW DEBRIEF: PILOT REPORTED TAIL STRIKE ON DEPARTURE FROM SFO TO SFO. THEY HEARD AND FELT STRIKE AS THEY ROTATED AND WERE CALLING FOR GEAR UP. DATA PROVIDED WAS V2 WAS 127, ROTATE 115-122 AND 146 TAKE OFF WEIGHT. ADDITIONAL PHOTOS ACCOMPLISHED INSP. STEP 4 (A) AND STEP 4(B) PER AMM 05-51-32-212-011 CREATED LOG PAGES ACCOMPLISHED INSPECTION OF THE UPPER FUSELAGE STRUCTURE AFT OF WING SPARS PER AMM 05-51-32-212-012 ITEM 4 (C). NO DEFECTS FOUND. ACCOMPLISHED INSPECTION UP TO STEP 2 D (1)(E). SYSTEM TEST FOR THE STABILIZER POSITION INDICATION SYSTEM NEEDS TO BE ACCOMPLISHED REF. AMM 5-51-32-212-011 ACCOMPLISHED STABILIZER TRIM POSITION INDICATING SYSTEM TEST REF AMM 27-48-00/501 AS REQUIRED BY AMM 05-51-32-212-011 TAIL STRIKE INSPECTON STEP 2.D.(1)(F). NO DISCREPANCIES NOTED. ADD EMP:U031682. TAIL STRIKE SHOE LIMITER HAS DAMAGE DUE TO TAIL STRIKE. REF IPC 53-86-50-01 ITEM 30 PICTURE UPDATE. ORDERED SHOE-TAIL STRIKE LIMIT. P/N 148N3217-2 M&E 19-5386-3-0019 IN TOCS. AVAIL EWR. REMOVED TAIL STRIKE FAIRING AND SHOE.
DUE TO ENGINE # 2 SURGE EVENT ACCOMPLISH FIM 71-06 TASK 812 ACCOMPLISHED TASK 1-11 BVCU F1 04 AND TPU F0 40 WERE PRESENT. THIS IS OK PER FLAG NOTE 2 NEED TO CONTINUE FROM BLOCK 12 C/W FIM TASK 71-06 BLOCK 12 , TESTED ALTITUDE SWITCH IAW AMM 75-32-07-735-001-R00 , OPS CHECK FAILED. REPLACED ALTITUDE SWITCH S/N OFF 5637, STALLED S/N 5907 L OPS CHECK GOOD. REQUIRES TEST 3 , IP/HP COMPRESSOR AIRFLOW CONTROL TEST. PERFORED TEST #3 IP/HP COMRESSOR AIRFLOW CONTROL TEST AND TEST#13 TAKE OFF POWER ASSURANCE TEST. ALL TESTS PASSED NO DEFECTS NOTED. TOMC NOTIFIED OF TEST RESULTS. PERFORM GVI OF AIRCRAFT. NO DISCREPANCIES FOUND OR DAMAGE. SUSPECTED A SHIFT IN AFT CARGO LUGGAGE AS SOURCE OF BANG AND VIBRATION. C/W WITH TOMC REQUEST AND PERFORMED INSPECTION AFTER SURGE PER AMM 71-00-00-206-007-R00, TASKCARD: 19-0572-8-0004 FOR COMPLIANCE. COMPLIED WITH BOROSCOPE INSPECTION OF #2 ENGINE HP, IP, LP TURBINES, HPC STGS 1 TO 6, IPC STGS 1 TO 6. NO DEFECTS NOTED AT THIS TIME.
LDG GEAR MONITOR EICAS S "SYSTEM 1 AND SYSTEM 2 LANDING GEAR POSITION INDICATIONS DO NOT AGREE. ALL GEAR DOW N GEAR DISAGREE GEAR DOORS GEAR LEVER L(R) GEAR DOWN L(R) DRAG B RACE L(R) SIDE BRACE NOSE GEAR DOWN NOSE GEA NOTED AFTER TO ADJUSTED NOSE GEAR DOWNLOCK SENSOR S10065 AND S10078, PERFORMED GEAR SWINGS AND INDICTION SYSTEM OPS CHECK GOOD. NO DEFECT NOTED.
(B757-06-3-0328) RIGHT WING APPROX. FSS 228 UNDER #6 SLAT, VERTI CAL STIFFNER AT DUCT ATTACH BRACKET CHAFING DUE TO BRACKET BEING LOOSE AS MARKED. TRANSCRIBED FROM HAECO GSO NR 9280145. AND BOEING DWG 112N2038 REV-. INSTALLED NEW STIFFENER IAW REO-G2 4456, B757-200 SRM 51-40-02 AND BOEING DWG 112N2002 REV D EVALUATED DAMAGE AND FOUND TO BE OUT OF LIMITS IAW B757-200 SRM 57-20-10-1A-2 ORIGINAL THICKNESS .130, DAMAGE DEPTH .100 MATERIA L REMAINING .030. REMOVED VERTICAL STIFFENER IAW B757-200 SRM 51 -40-02. FABRICATED NEW STIFFENER IAW BOEING PL 112N2038 REV D
2(EA) CRACK INDICATIONS FOUND: L/H UPPER WING SKIN & DRAG FITTIN G FASTENER HOLE #2, IN UPPER LAYER(SKIN) AT 3 & 9 ''OCLOCK POSITI ONS. FLIGHT CYCLES THEREAFTER." REPAIRED #2 HOLE AT L/H WING SKIN & I/B DRAG FITTING PER REO-G24 "ACCOMPLISH INITIAL INSPECTION REQUIREMENTS PER PART 2B OF ECRA- 432 AND REPLACED I/B DRAG FITTING P/N 653N0002-13, PO: 1057274.1 01053 LATEST REVISION ON OR BEFORE THE AIRCRAFT THRESHOLD 21,400 PER BAC DWG 112N7001, REV D, B757-200 SRM 57-20-01, REPAIR 8. TOTAL FLIGHT CYCLES. ACCOMPLISH REPEAT INSPECTIONS PER PART 2A O F ECRA-01053 LATEST REVISION AT INTERVALS NOT TO EXCEED 1,050
REFERENCE PREVIOUS LOGPAGE #9295835. THE REPAIR INCORPORATED VIA ECRA 5331-03026 IS APPROVED AS TIME-LIMITED UNTIL 39,750 TOTAL A IRCRAFT CYCLES PENDING THE RESULTS OF A DAMAGE TOLERANCE ANALYSI S (DTA). REMOVE THE AIRCRAFT FROM SERVICE ON OR BEFORE 39,750 TO TAL AIRCRAFT FLIGHT CYCLES, UNLESS ANOTHER 8100-9 FORM IS RECEIV ED FINDING APPROVAL FOR DAMAGE TOLERANCE REQUIREMENTS. TRANSCRI BED FROM HAECO GSO NR 9285835. 39,750 TOTAL AIRCRAFT CYCLES PENDING THE RESULTS OF A DAMAGE TO EFORE 39,750 TO TAL AIRCRAFT FLIGHT CYCLES, UNLESS ANOTHER 8100- MENTS". TRANSCRIBED FROM HAECO GSO NR 9280032. LERANCE ANALYSIS (DTA). REMOVE THE AIRCRAFT FROM SERVICE ON OR B 9 FORM IS RECEIVED FINDING APPROVAL FOR DAMAGE TOLERANCE REQUIRE REFERENCE LOG PAGE 9295835 L/H ALTERNATE STATIC PORT, "REPAIR IN CORPORATED VIA ECRA 5331-03026 IS APPROVED AS TIME-LIMITED UNTIL RII INSPECTION ACCOMPLISHED BY HAECO INSPECTOR PENDER V935793. DIP 53-DIP TOMC REJECTS DIP REQUEST FOR CORRECTION OR VOID DUE TO INCORRECT OT LACKING REPAIR INFORMATION LOGPAGE READY TO BE CLEARED, ENTERED IN ERROR
THE REPAIR INCORPORATED VIA ECRA 5331-03025 IS APPROVED AS TIME- LIMITED UNTIL 37,500 TOTAL AIRCRAFT CYCLES PENDING THE RESULTS OF A DAMAGE TOLERANCE ANALYSIS(DTA). REMOVE THE AIRCRAFT FROM SE RVICE ON OR BEFORE 37,500 TOTAL AIRCRAFT FLIGHT CYCLES, UNLESS A NOTHER 8100-9 FORM IS RECEIVED FINDING APPROVED DAMAGE TOLERANCE REQUIREMNETS. TRANSCRIBED FROM HAECO GSO NR 9280033. REFERENCE LOGBOOK NUMBER 9296053 UPDATE OF INFORMATION. L 37,500 TOTAL AIRCRAFT CYCLES PENDING THE RESULTS OF A DAMAGE T EFORE 37,500 TOTAL AIRCRAFT FLIGHT CYCLES, UNLESS A NOTHER 8100- S. TRANSCRIBED FROM HAECO GSO NR 9280033. OLERANCE ANALYSIS(DTA). REMOVE THE AIRCRAFT FROM SERVICE ON OR B 9 FORM IS RECEIVED FINDING APPROVED DAMAGE TOLERANCE REQUIREMNET REFERENCE LOG PAGE 9296053 LH PRIMARY STATIC PORT, "THE REPAIR I NCORPORATED VIA ECRA 5331-03025 IS APPROVED AS TIME-LIMITED UNTI DIP 53-DIP THE INITIAL LOG ENTRY REQUIRES A DESCRIPTION OF THE DISCREPANCY BEING ADDRESSED. CLOSE OUT THIS LOG PAGE AND CREATE A NEW LOG PAGE WITH INFORMATION REGARDING WHAT THE DEFECT WAS. RII INSPECTION ACCOMPLISHED BY HAECO INSPECTOR PENDER V935793 CLEARED OUT LOGPAGE PER TOMC.
(SUPPORT TASK) MAIN CABIN FLOOR BEAM STA 720 RBL 24 CORRODED ON UPPER SURFACE. TRANSCRIBED ON HAECO GSO NR 9280357 REPAIRED FLOORBEAM STA 720 RBL24 IAW B757-200 SRM 53-00-51-2R-10 AND SRM 51-40-02. HAECO GSO MECH V900838 INSP QC031
(SUPPORT TASK) MAIN CABIN FLOOR BEAM STA 324 RBL 45 UPPER SURFAC E CORRODED. TRANSCRIBED FROM HAECO GSO NR 9280358. HAECO GSO MECH V900838 INSP QC204 REPAIRED STA 324 UPPER 7 CHORD IAW B757-200 SRM 53-10-08-2R-1 RE PAIR 1 FIG 201 THIS IS A CATEGORY B REPAIR. INSPECTION THREHOLD 37,500 FLIGHT CYCLES AFTER AIRPLANE DELIVERY OR 12,000 FLIGHT C YCLES AFTER REPAIR, WHICH EVER COMES LATER.
(SUPPORT TASK) MAIN CABIN STA 1640 BL0 PREVIOUS TCAP REPAIR CORRODED ON UPPER SURFACE. TRANSCRIBED FROM HAECO GSO NR 9280466. ENTERED IN ERROR
(SUPPORT TASK) MAIN CABIN DECK PLATE STA 1720 BL0 PREVIOUS REPAIR HAS EVIDENCE OF CORROSION. TRANSCRIBED FROM HAECO GSO NR 9280 454. REMOVED AND FAB. NEW DOUBLER AT STA 1720 BL0 IAW B757-200 SRM 53 -60-51-2R-2.
(SUPPORT TASK) MAIN CABIN DECK PLATE STA 1720 LBL20 PREVIOUS REP AIR HAS EVIDENCE OF CORROSION. TRANSCRIBED FROM HAECO GSO NR 92 80455. REMOVED AND FAB. NEW DOUBLER AT STA 1720 LBL20 IAW B757-200 SRM 53-60-51-2R-2.
EICAS AUTOTHROT DISC EICAS ON T/O L ENG EEC L ENG LIMITER PERFORMED FIM 22-02 TASK 801 AND FOUND A/T DISC EEC L/TMC CODE 31890. PERFORMED EEC BITE FIM 73-21 T 802 AND NO FAULT NOTED. PERFORMED BVCU BITE FIM TASK 75-32 T 830 AND NO FAULT FOUND. CK BETWEEN PINS 4 AND 19 OF CON D1386P TO PINS 4 AND 19 OF CON D1484 THRU TB 1 JJ7. ALL CK GOOD REF WDM 71-51-22. PERFORMED FIM TASK 73-21 FT 820. 28 VDC AT CON D4162 PIN 2 AND FURTHER T/S REQUIRED. AS PER TECH SUPPORT, DG REQUIRES TECH SUPPORT MIKE LEONARD REQUESTS REPLACEMENT OF E1 DRIVE REMOVED #1 ENGINE DEDICATED GENERATOR. REF MM 73-21-08 R&R DEDICATED GENERATOR STATOR IAW AMM 73-21-08 , OPS AND LEAK R&R GENERATOR ROTOR AND DRIVE IAW AMM 73-21-08-01 , OPS AND LEAK DIOD CHECKS IN DGCU A AND B CK GOOD. PERFORMED CONTINUITY AND REPLACEMENT AND HIGH POWER ENGINE RUN. GENERATOR AND HIGH POWER ENGINE RUN. ADD EMP:U248952 CHECK GOOD PARTS USED: 19-7321-9-9002,QTY :1 CHECK GOOD PARTS USED: 19-7321-9-0004,QTY :1 MEG CK BETWEEN M10157 AND M10165 DGCU''S TO M10169 DG WITH ADD EMP:U139080 ADD EMP:U139080 SHAKEDOWN. PERFORMED RESISTANCE CK OF COILS IN DG. PERFORMED RES ROTABLE PARTS CHANGE WAS INDICATED - TT # 1869505 SN OFF 0121 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1966393 SN OFF 4588 IPC REFERENCE # 73-21-08 GENERATOR, ROTO OFF 19-7321-9-0004 4588 ON 19-7321-9-0004 4386 STATOR, DEDICAT OFF 19-7321-9-9002 0121 ON 19-7321-9-9002 0014 PERFORMED HIGH POWER RUN IAW AMM 71-00-00 TEST 13 , ALL PARAMETERS NORMAL. NO FAULTS N
LSAT EEC & LIMITER . REF CHRONIC HISTORY OF "L ENG EEC" & "L ENG LIMITER" EICAS MSGS DISPLAYED. THE EEC & THE ENG START/RAT CONT. PANEL (WITH LIMITER SW''S) RECENTLY REPLACED. YET PROBLEM REPEATED. PLEASE DO THE FOLLOWING: 1. PERFORM AUTOFLIGHT BITE (FIM 22-02 TASK 801). READ & RECORD PREVIOUS FLT FAULTS & THEIR DIAGNOSTIC CODES. 2. PERFORM EEC & BVCU BITE (FIM 73-21 T 802 & 75-32 T 830). 3. CK THE SECURITY OF REMOVE DDG CONNECTOR D1384P. THEN REMOVE IT AND (WITH BACKSHELL REMOVED) CK FOR CONDITION OF WIRES. ENSURE THERES NO BROKEN WIRES (OFTEN THEY BREAK AT THE PIN CRIMPING). 5. AFTER COMPLETING THE PREVIOUS STEPS, IF NO FAULT IS DETECTED, CORRECT ANY DISCREPANCY NOTED & PLEASE UPDATE THIS L/P WITH THANKS! MINUTES, PER AMM 71-00-00-700-804-R03. EICAS MSG CLEARED. REQUIRES FURTHUR TROUBLESHOOTING. HP2 BLEED VALVE SOLENOID OHMED OUT OK. RAN ENG AND FAULT 18 ON F0 (FLIGHT "0"). ALSO NOTED WAS L ENG SURGE BITE MAINT MSG 3911010. NEEDS BVCU REPLACE THE DGCU (POWER CONDITION& CONTROL) UNIT A (TOP). ALL FINDINGS & ACTIONS TAKEN. PERFORMED BVCU BITE FOUND FAULT CODE 18 HP2A SOLENOID O/C. 19-7321-9-0016,QTY :1 CLEARED, HOWEVER NOW FAULT 65 ( 5V POWER SUPPLY FAILURE) SHOWS DURING IDLE RUN AFTER CLEARED. ITEM IS CURRENTLY ON MEL LOG ROTABLE PARTS CHANGE WAS INDICATED - TT # 1803400 SN OFF 0816 CARRIED BY ELB 2. AT THE DDG ITSELF, CHECK THE WINDINGS FOR CONTINUITY BETWEEN NOTE: FOR THE CHECKS REQUESTED SEE WDM 71-51-22-1 (SH''S 2, AS PER FOLLOW
R/H APU DOOR HAS HEAT DAMAGE FROM TAIL PIPE AND DRAIN MAST FIRE. DAMAGE (1) IS 2" ABOVE DRAIN MAST MEASURING 6" X 6" AND IS .125" DEEP. DAMAGE AREA (2) IS 3" AFT OF DRAIN MAST MEASURING 5" X 11" AND IS .125" DEEP. DAMAGE (3) IS 2" BELOW DRAIN MAST AND MEASURING 5" X 5" AND IS .125" DEEP. DAMAGE AREA (4) IS 2" FWD OF DRAIN MAST AND IS 3" X 5" AND IS .100" DEEP. LOG LOCKED FOR MAINTENANCE FERRY PURPLE K WAS USED ON THE EXTERIOR R/H APU DOOR AT THE DRAIN MAST, THEN WASHED WITH WATER FROM FIRE DEP. PURPLE K WAS USED ONLY ON OUTSIDE OF DOOR. CLEANED AND INSPECTED R/H APU DOOR AND DRAIN MAST FOR FIRE REMOVED RH APU ACCESS DOOR IN REF TO AMM TASK 52-48-21-000-801. ROTABLE PARTS CHANGE INFO ONLY. DAMAGE IAW AMM 49-11-00-206-021. FIRE DAMAGE NOTED AROUND DRAIN ADD EMP:U330982, U231804 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1014208 SN OFF 0138 MAST. APU REMOVAL IS REQUIRED FOR FURTHER INSPECTION OF APU COMPARTMENT FOR OTHER FIRE DAMAGE. DOOR, ASSY, APU OFF 19-5248-9-0005 0138 ON 19-5248-9-0005 9550 VISUALLY EXAMINED THE APU COMPARTMENT AND ITS STRUCTURAL INSTALLED(NEW)SERVICEABLE RH APU ACCESS DOOR IN REF TO AMM COMPONENTS FOR SIGNS OF FIRE DAMAGE, NO DISCREPANCIES FOUND PER 52-48-05-404-007 & APU FIRE DETECTOR ELEMENT IN REF TO AMM AMM SUBTASK 49-11-00-216-023 26-15-02-424-010. ADD EMP:U330982, U231804 UNLOCKED THE LOGPAGE FOR UPDATE. LOCKED LOGPAGE AGAIN UNTIL DOOR IS REPLACED. REMOVED R/H APU DOOR ASSY AS SERVICABLE UNIT P/N 148N6660-30 . S/N 9550. REF 52-48-01. DOOR HAS
PDA UPPER LEFT GENERATOR COMPESSOR GAS FAIRING BROKE OFF NR 2 ENGINE. DISCOVERED AFTER FLIGHT 675.
1R SLIDE LIGHT IS NOT ILLUMINATED. UPPER SIDE OF DOOR. RELAMPED INDICATOR, OP CK OK
EMERGENCY LIGHTS AT SEAT 3 AND 4 FOUND TO BE INOPERATIVE. REPLACED THE POWER SUPPLY M731 AND BATTERY PACK. LIGHTS CHECKED GOOD.
L3 DOOR EXTERIOR EMERGENCY LIGHT FOUND INOPERATIVE. REMOVED AND REPLACED THE BULB IAW AMM 33-51-06, OPS CHECKED GOOD.
FUMES IN COCKPIT AND CABIN. LOST AIRSPEED INDICATIONS AND MACH TRIM. CHECKED ENGINE BLEEDS AND LT AND RT MM 05-51-58-910-801C1. NO SMOKE OR ODORS.
ON CLIMBOUT FUEL IMBALANCE OF 2000 POUNDS HAD TO CROSSFEED WITH RIGHT CENTER PUMP OFF. REMOVED AND REPLACED RT CTR FUEL BOOST PUMP IAW MM REF 28-22-03. OPS AND LEAK CKS GOOD AT THIS TIME. OK TO CONTINUE.
SKIN DENTED AT BS 573, STRINGERS 25-26R. ACCOMPLISHED EXT SKIN DOUBLER REPAIR AT FWD CARGO DOOR IAW SRM 52-30-01 REPAIR 4.
UPPER LOBE BETWEEN BS 880 AND 900, STRINGER 15R CHAFED. INSTALLED AN INTERIM REPAIR ON THE STRINGER IAW ECRA 5310-07129.
R4 SLIDE UNRAVELED. REMOVED AND INSTALLED NEW R4 DOOR ESCAPE SLIDE AS PER REF AMM 25-66-01-004-154 AND AMM 25-66-01-404-044.
AFT WET AREA STA 1640 RBL 1 FLOORBEAM HAS CORROSION. INSTALLED NEW CHORD SECTION AND EXISTING REPAIR PARTS AT FLOORBEAM STA 1640 BETWEEN RBL 20 AND LBL 17 PER REF SRM 53-00-51 FIG 201.
R2 DOOR CREASE BEAM SUPPORT FROM STA 720 TO STA 740 RBL 60 SEVERAL SPOTS HAVE EVIDENCE OF CORROSION. REMOVED CORROSION, ORIG MAT .080" MAT LOSS .016" MAT REMAINING .064" FOUND OUT OF LIMITS. REMOVED AND REPLACED CREASE BEAM AT R2 DOOR STA 665 TO 755 IAW SRM 51-10-02, 51-40-02, 53-30-13 AND DRAWING NR 143N8322.
LT UPPER LOBE STA 760 TO STA 700 LBL 63 MAIN DECK FLOOR STRUCTURE CREASE BEAM HAS EVIDENCE OF CORROSION. REMOVED AND REPLACED CREASE BEAM LT SIDE BETWEEN STA 755 THRU STA 665 AS PER SRM 51-40-02 AND DRAWING NR 143N5520.
EMERGENCY LIGHTS FLICKERING IN BACK OF AIRCRAFT RMVD AND RPLD POWER SUPPLY AND BATTERY PACK, OPS CHKD OK.
SMOKE ALARM SOUNDED, NO SMOKE, FIRE EXTINGUISHER DID NOT DISCHARGE. CHECKED AFT LAVATORIES, AFT GALLEY, ALL LIGHTS IN CABIN. ALL CHECKED GOOD .
FA EMERGENCY HAND HELD MEGAPHONE INOP. REPLACED FA EMERGENCY HAND HELD MEGAPHONE. STOWED IN FIRST CLASS.
AFT GALLEY OVEN NR 1 HAD FOREIGN SUBSTANCE LEFT INSIDE OVEN BY PREVIOUS FLIGHT. WHEN OVEN WAS USED, HEAVY SMOKE RESULTED. CB`S WERE PULLED & EXTINGUISHER DISCHARGED INTO OVEN. SMOKE SUBSIDED. OVEN 411 REMOVED CONTAMINATED, WITH FOOD, METAL TRAY INSERT. OVEN OPERATIONS CHECKED GOOD AFTER 10 MINS OPERATION. NO SMOKE & OK TO CONTINUE.
ON TAKEOFF ROLL AT 50-60KTS LT ENGINE BLEED LIGHT CAME ON. PERFORMED LOW SPEED REJECT. LT ENG BLEED LIGHT WENT OUT DURING THE REJECT. REPEAT WRITEUP REF 38965158 PERFORMED FIM TASK 36-10-00-815-811 NO DEFECTS FOUND. REF NUMEROUS NON ROUTINES IN CHAPT 36 FOLLOWING PARTS REPLACED HPSOV, 390, 450, 490 SENSORS MX REQUESTED EVALUATION FLT.
DURING TAKEOFF AT APPROX 75-90 KNTS, REJECTED T/O FOR "LEFT BLEED OFF" LIGHT ILLUM. ON EICAS. PERFORMED FIM TASK 36-10 TASK 816 AND FOUND NO DEFECTS. PERFORMED MM 36 -00-23-705-152-001 (PRSOV TEST) AND FOUND NO DEFECTS. RAN NR 1 ENG AND ALL OPS OK.
LEFT EMERGENCY ESCAPE SLIDE DID NOT DEPLOY WHEN PERFORMING OPERATIONAL TEST. REMOVED AND REPLACED L/T OFF-WING ESCAPE SYSTEM ACTUATOR IN REF AMM 25-65-05-404-017. PERFORMED LEFT EMERGENCY ESCAPE OPERATIONAL CHECK PER AMM 25-65-00-715-052. OPS CHECK OK. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1465275, S/N OFF 01134 ACTUATOR, WING OFF 19-2565-9-0003 1134, ON 19-2565-9-0003 0158.
SUPPORT TASK: FWD CARGO COMPT, STA 620 AT RBL-28, FRAME HAS A MIS-DRILLED HOLE NEXT TO EXISTING FASTENER HOLE. INSTALLED REPAIR ACCOMPLISHED REF PER EC/RA 5310-05374 AT STA 620 RBL 28 AND INITIAL A DIP TO ACCOMPLISH A PERMANENT REPAIR WITHIN 24 MONTHS OF APRIL-12-2011. PLANNING TO CONTRACT ENGINEERING AFTER 22 MONTHS BUT BEFORE 23 MONTHS FOR A PERMANENT REPAIR.
ACCOMPLISH A PERMANENT REPAIR WITHIN 12 MONTHS OF MARCH 30-2011 PLANNING CONTACT ENGINEERING AFTER 10 MONTHS BUT BEFORE 11 MONTHS FOR A PERMANENT REPAIR. REFERENCE ECRA 5310-05367 LT CREASE BEAM I/B CHORD CORROSION AT STATION 1300-1310. INITIATING A DIP TO ACCOMPLISH A PERMANENT REPAIR WITHIN 12 MONTHS OF MARCH 30-2011 PLANNING CONTACT ENGINEERING AFTER 10 MONTHS BUT BEFORE 11 MONTHS FOR A PERMANENT REPAIR. REFERENCE ECRA 5310-05367 LT CREASE BEAM I/B CHORD CORROSION AT STATION 1300-1310. FOUND CORROSION DAMAGE AT LT CREASE BEAM STA 1300-1310. PER ECRA 5310-05367 COMPLETED INTERIM REPAIR. C/W PERMANENT REPAIR W/I 12 MONTHS FROM 30MAR11. PLANNING TO CONTACT ESC AFTER 10 MONTHS BUT BEFORE 11 MONTHS FOR REPAIR.
AFT CARGO COMPT FLOOR STRUCTURE BETWEEN STA 1500 TO STA 1520, STRINGER AT LBL 12 HAS CORROSION ON BOTTOM SIDE. REPAIRED ACCOMPLISHED PER ECRA 5320-02021.
AFT CARGO COMPT, FLOOR STRUCTURE BETWEEN STA 1500 TO STA 1520 STRINGER AT RBL 12 HAS CORROSION ON TOP/ BOTTOM SIDE. REPAIR ACCOMPLISHED PER ECRA 5320-02021.
AFT CARGO COMPT, FLOOR STRUCTURE BETWEEN STA 1500 TO STA 1520 STRINGER AT RBL 3 HAS CORROSION ON TOP SIDE. REPAIR ACCOMPLISHED PER ECRA 5320-02021.
AFT CARGO COMPT, FLOOR STRUCTURE BETWEEN STA 1500 TO STA 1520 STRINGER AT LBL 7 HAS CORROSION ON BOTTOM SIDE. REPAIRED ACCOMPLISHED PER ECRA 5320-02021.
AFT CARGO COMPT, FLOOR STRUCTURE BETWEEN STA 1500 TO STA 1520 STRINGER AT LBL 3 HAS CORROSION ON BOTTOM SIDE. REPAIR ACCOMPLISHED PER ECRA 5320-02021.
FRAME AT STA 1580 CRACKED AT PSU RAIL BETWEEN STRINGER 8 AND 9 LT. INSTALLED ALL REPAIR PARTS, REPAIRED FRAME REF EC/RA 5310-05365 .
FRAME AT STA 1580 CRACKED AT PSU RAIL BETWEEN STRINGER 8 AND 9 RT. INSTALLED ALL REPAIR PARTS, REPAIRED FRAME REF EC/RA 5310-05365 .
AFT ENTRY FLOORBEAM STA 1640 CORRODED FROM BL 7L TO BL 10R. CUT OUT DAMAGE AND INSTALLED FLOORBEAM UPPER CHORD REPAIR 3 IAW SRM 53-00-51 FIG 201.
DENT FUSELAGE SKIN STA 1706 BETWEEN STR 5 RT AND STR 6 RT APPROX INSTALLED REPAIR DOUBLER REF SRM 53-00-01 REPAIR 3 FIG 201 PG 207 TABLE 5 CATEGORY B REPAIR REQUIREMENTS 37500 FLT CYCLES PER NOTE J LFEC PER NOTE E. ADDITIONAL INFORMATION REPAIR DOUBLER THICKNESS IS .071 2024T3 FOUND DENT IN FUSELAGE SKIN STA 1706, STR 5 RT TO STR 6 RT PER SRM 53-00-01, REPAIR 3, PG 207 INSTALLED REPAIR. PERFORM LFEC INSP AT 37,500 AFTER REPAIR WAS INSTALLED, THEREAFTER EVERY 3,000 FLT CYC'S.
STRONG ELECTRICAL SMELL FROM MID GALLEY WHEN OVEN TURNED ON SMELL DISAPPEARED WHEN OVEN TURNED OFF. REMOVED AND REPLACED OVEN AND CONTROLLER, OPS CHECK OK. FILED SMOKE IN CABIN REPORT FOR MAINTENANCE WITH SUPERVISOR, OK TO CONTINUE. ROTATABLE PARTS CHANGE - OVEN, LARGE, OFF 99-2533-9-0002 S/N 0266 ON 99-2533-9-0002 S/N 0081.
FOUND HEAVY CORROSION ON CABIN INTERCOSTAL AT BS 345 LBL 20. INSTALLED NEW FLOOR SUPPORT REFERENCE DRAWING 141N5170 ITEM 56 AND SRM 51-40-02 AND GMM 10-900-01.
LAV SMOKE INDICATION ON EICAS. THE LEFT AFT LAV SMOKE DETECTOR WAS ACTIVATED. NO FLAME WAS NOTICED, BUT THE A/C DID HAVE A SMOKE (ELECTRICAL) SMELL. DIVERTED TO LAS. PER F/A WORKING AFT GALLEY, WHEN DOOR TO NR 1 OVEN OPENED SMOKE CAME OUT AND AFT LAV SMOKE DETECTION WENT OFF IMMEDIATELY. REMOVED NR 1 OVEN, INSPECTED WIRING, NO FAULTS FOUND. PULLED AND COLLARD NR 1 OVEN C/B AND PLACARD INOP. INSPECTED LAV PRECAUTIONARY NO FAULTS NOTED. OVEN HAS BEEN REMOVED AND REPLACED.
SMOKE WAS NOTED FROM OVERHEAD PSU PANEL AT ROW 4 WHILE EN ROUTE FROM CGN TO EWR. HALON AND WATER FIRE EXTINGUISHERS WERE USED ON THE OVERHEAD AND THE AIRCRAFT WAS DIVERTED TO SNN WHERE IT LANDED WITHOUT INCIDENT. TROUBLESHOOTING FOUND PSU AT ROW 4 WITH A BURNT CIRCUIT BOARD. MEL WAS APPLIED TO PSU 3EF AND 4EF.
INSPECTION FOUND EMERGENCY EXIT LIGHTS ON SEATS 26-34 INOPERATIVE. THE M736 BATTERY PACK WAS FOUND AT FAULT. THE POWER SUPPLY WAS REPLACED IAW MM 33-51-07.
INSPECTION FOUND A 0.2 INCH CRACK LT WING RIB AT WS 594, S11.5. THE CRACKED AREA WAS REMOVED AND A REPAIR WAS INSTALLED IAW ECRA 5700-01767.
INSPECTION FOUND A 1.5 INCH CRACK IN L-2 DOOR INSIDE INTERCOSTAL WEB AT LIGHTENING HOLE JUST FORWARD OF DOOR BOX. THE CRACK WAS TRIMMED OUT AND A DOUBLER WAS INSTALLED IAW ECRA 5210-01874.
INSPECTION FOUND CORROSION ON OUTER SKIN OF RT GTE AIRPHONE ANTENNA CUTOUT, STA 1500-1520, S28R TO S29R. THE CORRODED AREA WAS CUT OUT AND AN INTERIM REPAIR WAS INSTALLED IAW ECRA 5330-03507. A DIP WAS ISSUED TO ACCOMPLISH A PERMANENT REPAIR WITHIN 12 MONTHS.
INSPECTION FOUND CORROSION ON OUTER SKIN SURFACE OF LT GTE AIRPHONE ANTENNA CUTOUT, STA 1500-1520, S28L TO S29L. THE CORRODED AREA WAS CUT OUT AND AN INTERIM REPAIR WAS INSTALLED IAW ECRA 5330-03511. A DIP WAS ISSUED TO ACCOMPLISH A PERMANENT REPAIR WITHIN 12 MONTHS.
THE SLIDE CARRIAGE FAILED WORK CARD 19-2560-1-7650 STEPS DURING RT OFF WING DEPLOY FUNCTIONAL CHECK. THE RT WING ESCAPE SLIDE ACTUATOR WAS REMOVED AND REPLACED IAW MM 25-65-05. THE DOOR LATCHES WERE ADJUSTED IAW MM 25-65-07.
THE LT OFF WING SLIDE DEPLOY CHECK FAILED STEPS OF WORK CARD 19-2560-1-7650. THE LT WING ESCAPE SLIDE DEPLOYMENT ACTUATOR WAS REPLACED IAW MM 25-65-05.