N15751
Registered owner: UNITED AIRLINES INC, IL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
EMERGENCY LIGHTS - OPERATIONAL CHECK EMERGENCY LIGHTS OPERATIONAL CHECK - ROW 29 ABC EPL SHROUD IS DAMAGED AND NOT SECURED TO SEAT REMOVED AND REPLACED THE BROKEN SHROUD. REF CMM 25-21-56.
SMOKE ALARM. NO SMOKE NOTICED ALL LAV SMOKE DETECTORS OPS NORMAL, IAW AMM 26-14-00-730-801.
FLAPS STUCK BETWEEN 5 AND 10 DEGREES AND WOULD NOT MOVE WITH FLAP HANDLE MOVEMENT. PSEU LIGHT ON. BITE CHECKED PSEU AND FOUND LDG FLAP A FAULT MESSAGE 32-62009 AND LDG FLAP B FAULT WITH MESSAGE 32-62010. AND NO DISPATCH. PERFORMED FSEU BITE. FOUND PROBLEM WITH LT FLAP TRANS. ALSO WHILE OPERATING FLAPS NOTICE FLAP POSITION IND LT NEEDLE STICKING AND MAKING NOISE. R & R FLAP POSITION IND REF 27-58-02. OPS CHECK NORMAL. NO FAULTS DURING FSEU BIT.
FLAP LOCK OUT ON 1ST TICK. ATTEMPTED RESEAT OF LEVER, NO HELP. ALTN EXTENSION REQUIRED. PERFORMED OPS CHECK OF NORMAL AND ALTN FLAP CONTROL SYSTEMS IAW AMM 27-51-00-710-801. OPS CHECK GOOD. PERFORMED BITE TEST OF FSEU IAW FIM 27-51 TASK 801. INTERMITTENT INACTIVE FAULT FOUND DURING BITE CHECK. NO HISTORY ON 30 DAY. GOOD TO CLEAR.
L3 WINDOW FRAME E-F POST REPAIRED PER ECRA 5310-08654. PERFORM AN INSPECTION OF LT WINDOW FRAME E-F POST REPAIR ON AIRCRAFT IAW PART 2 OF THE LATEST REVISION OF ECRA 5310-08654. MAJOR REPAIR. ACCOMPLISHED ESFR AND PERMANENT REPAIR COMPLIED WITH.
REPAIR THE RH #3 WINDOW FRAME E-F POST REF TO ECRA 5611-01314 R EV C PART 3. REPAIRED PER ECRA 5310-08655 REPAIR THE R3 WINDOW FRAME E-F POST REF TO ECRA 5611-01314 R EV C PART 3.
EMERGENCY PASSENGER CABIN LIGHTS M1674 FAILS BATTERY CAPACITY CHECK. REMOVED AND REPLACED EMERGENCY LIGHTS BATTERY PACK M01674 AND PERFORMED INSTALLATION TEST IAW B737 A.M.M. 33-51-06-960-805. TEST OK.
PDA 2 RF LOG 4481684.. LEFT RETRACTABLE LANDING LIGHT LENS AND BULB MISSING ON ARRIVAL... SEE PHOTO... ADDED PHOTO PARTS USED: 29-3342-9-0001,QTY :1 REPLACED LH LANDING LIGHT ASSY PER AMM33-42-02-960-802. OPS CHECKS GOOD. SDR REPORT SUBMITTED.PARTS USED: 29-3342-9-0001,QTY :2 ROTABLE PARTS CHG:TT # 1424625 SN OFF 9816 PN OFF 29-3342-9-0001 LIGHT, LANDING, OFF 29-3342-9-0001 9816 ON 29-3342-9-0001 0386
REMOVED AND INSTALLED NEW R/W FRONT SPAR LOWER STRAP INBD OF PYLON AT IFSS 155 AS PER SRM 51-40-02-0G-0,DWG 112A4401.REF AAR N/R9935224.WORK ACCOMPLISHED BY V945157.
FOUND 3 EACH LOWER STRAPS WITH GOUGES AT STA 540 LBL STRINGER 23 REF AAR N/R 9935388
REMOVED AND REPLACED PAN ASSY AT DOOR CUT OUT R1 PER REF SRM 51-40-02-0G-0 AND DWG 141A8370.REF AAR N/R 9935718. WORK ACCOMPLISHED BY V894270.
CRACK FOUND AT RIGHT HORIZONTAL STB LOWER SKIN STA 147.90, 24" FROM SPAR, I/B ROW. CRACK LENGTH 0.5" REF AAR N/R 9935073
AFT WET ARE STA 992 RBL48 INNER CHORD SEVERAL SPOTS OF CORROSION REF AAR NR9935198 REMOVED AND REPLACED AFT WET ARE STA992RBL48INNER CHORD DUE TO SEVERAL SPOTS OF CORROSION FOUND TO BE OUT OF LIMITS AS PER SRM 53-70-15-17-1 AND SRM 51-40-02-0G-0,DWG:147A8501.
LEFT PACK DRIVING FULL HOT REGARDLESS OF MANUAL CONTROL VALVE. E LEC SMELL NOTED REMOVED AND REPLACED L/H ACM PER REF AMM 21-51-04. OPS CHECK GOOD. NO LEAK NOTED. NO SMELL NOTED.
WINDOW LIGHT ABOVE EMERGENCY EXIT INOP AT ROW 21A. REPLACED LAMP PER AMM 33-21-00-960-807. OP 'S CHK OK.
LEADING EDGE FLAPS TRANSIT LIGHT ILLUMINATED ON DESCENT THEN ACTIONED QRH. DEBREIFED INBOUND CREW & RAN FLAPS UP & DOWN NO HELP LEADING TRANSIT LIGHT STILL ON UNLOCKING ACCOMPISHED LEADING EDGE FLAP AND SLAT PROXIMITY SENSOR TEST AMM 27-88-11-700-801 FOUND NO FAULTS WITH SENSORS. ACCOMPLISHED FIM 27-88 TASK 820 FOUND INBOARD TARGET AT #2L/E SLAT NOT SECURED. MEASURED GAPS WITHIN RANGE. SYSTEM OPS CHECK OK REF AMM 27-88-11-700-801. ACCOMPISHED LEADING EDGE FLAP AND SLAT PROXIMITY SENSOR TEST AMM 27-88-11-700-801 FOUND NO FAULTS WITH SENSORS. ACCOMPLISHED FIM 27-88 TASK 820 FOUND INBOARD TARGET AT #2L/E SLAT NOT SECURED. MEASURED GAPS WITHIN RANGE. SYSTEM OPS CHECK OK REF AMM 27-88-11-700-801.
ENGINE VIBRATION, VIBRATION HIGH ENGINE 2 MODERATE TO XCESSIVEVIBRATION ENG 2 AT CRZ STABILZD WITH NO AB IND RECURRED IN DESCENT ENG2 SN. 888650 (TSI=3004/ CSI= 1441) REMOVED MCD'S . FOUND METAL SHAVINGS IN REAR MCD. SEE PICS. (COPIED TEXTAND PIX FROM L/P 6781284). MORE PHOTOS OF DISSAMBLED MCD. ENGINE, BASIC, OFF57-7200-9-0001 8650 ON 57-7200-9-0001 5237 ENGINE, BASIC, OFF 57-7200-9-0001 8650 ON 0000REMOVED AND REPLACED #2 ENG PER W.C.29-7210-9-9001 PARTS USED: 1742432,QTY :1 ROTABLEPARTS CHANGE WAS INDICATED - TT # 1742432 SN OFF 8650.
ROW 29ABC EMERGENCY STOWBIN LIGHT INOP RELAMPED. OPS CK GOOD
SUSPECT CRACK IN R3 WINDOW FRAME ON FWD. SIDE 2ND FASTENER FROM BOTTOM PERFORMED HFEC SURFACE INSPECTION OF L3 WINDOW FRAME AT SECOND FASTENER HOLE FROM THE BOTTOM OF FWD FRAME EDGE AND VERIFIED CRACK EMINATING AFT .200 FROM FASTENER EDGE. REF 737 NTM PART 6-51-00-00 PROCEDURE 23. VERIFIED ACCOMPLISHMENT OF PART 1, PARG. B. STEPS 2 (FIGURE4) & STEP 4 (FIGURE 6) OF ECRA 5611-01314 REV. B. WINDOW POST NEEDS INSPECTED PER FIGURE 6. ACCOMPLISHED PART 1, PARG. B. STEPS 2 (FIGURE4) & STEP 4 (FIGURE 6) OF ECRA 5611-01314 REV. B. WINDOW POST NEEDS INSPECTED PER FIGURE 6. VERIFIED COMPLETION OF ECRA 5611-01314 REV B. PART 1.B.6. OK TO INSTALL DOUBLER REF. ECRA 5611-01314 REV.B. PART.1.C AND VERIFIED DOUBLER INSTALLED PER ECRA 5611-01314 REV.B PART 1.C.2. FIG.12. REINSTALLED E-F POST FASTENERS PER ECRA 5611-01314 REV B. PART DRILLED INTERNAL DOUBLER PER ECRA 5611-01314 REV.B. PART.1.C AND INSTALLED INTERNAL REPAIR DOUBLER PER ECRA 5611-01314 REV.B PART 1.B.6. FIG.12. OK TO INSTALL.. 1.C.2. VERIFIED ACCOMPLISHMENT OF ECRA 5611-01314 STEPS 1 - 20 FIG 10 SHEETS 6, 7, 8 AND 9. OK TO CONTINUE INSTALLING SEALANT AND REPAIR DOUBLERS. COMPLETED STEPS 1 THRU 20 OF ECRA 5611-01314 FIG 10 SHEET 6, 7, 8 AND 9. OK ADD SEALANT AND INSTALL REPAIR. VERIFIED INSTALLATION PER ECRA 5611-01314 REV. B FIG. 10 STEPS 21 THROUGH 25. INSTALLED REPAIR DOUBLER PER ECRA 5611-01314 REV B FIG 10 PARTS 21 THRU 25. INSTALLED REPAIR ON R/H #3 WINDOW FRAME PER EC/RA 5611-01314.REV. B. SEE DIP LOG. 4101632, 41
SUSPECT CRACK IN L3 WINDOW FRAME ON FWD. EDGE 2ND FASTENER FROM THE BOTTOM PERFORMED HFEC SURFACE INSPECTION OF L3 WINDOW FRAME AT SECOND FASTENER HOLE FROM THE BOTTOM OF FWD FRAME EDGE AND VERIFIED CRACK ACROSS FASTENER HOLE TO EDGES.REF 737 NTM PART 6-51-00-00 PROCEDURE 23. ACCOMPLISHED HFEC PER 6-51-00-00-23. CRACK TERMINATES APPROXIMATELY .310" FROM NEAREST FASTENER HOLE. SEE ATTACHED PIC. PER ENGINEERING REQUEST PERFORM SURFACE HFEC INPECTION OF FWD ADDING PIC. FRAME ATTACH HOLES TO VERIFY CRACK TO HOLE EDGE DISTANCE. ! D AND E OF AVO010546 VERIFIED COMPLETION OF FIG 5, STEPS 1 THRU 3 OF ECRA 5611-01314 REV B. ALSO COMPLETED STEP 1C OF AVO10546 REF NDT PART 6, 51-00-00 PROCEDURE 23. NO CRACKS NOTED, OK TO CONTINUE SEPARATED LEFT SIDE # 3 WINDOW FRAME AND CUT WINDOW FRAME IN TRIMED OUT THE WINDOW FRAME #3 AND REMOVED DISCREPANT HOLE AS ACCORDANCE WITH FIG 5 OF ECRA 5611-01314. COMPLETED STEPS 1 THRU SHOWN IN FIG ! COMPLETED STEPS ! A & B OF AVO10546. NEED TO HFEC 3 OF FIG 5 SHEET 3. EDGES OF TRIM OUT AREA PER STEP C. MAINTAINED 2D EDGE MARGIN FROM FASTENERS AND MAINTAINED 125 RA SURFACE ROUGHNESS PER STEPS VERIFIED COMPLETION OF ALL STEPS OF ECRA 5611-01314 FIGURES 7, 9 VERIFIED INSTALLATION OF REPAIR FILLER ON L3 WINDOW POST PER AVO AND 11. OK TO INSTALL DOUBLER AND TRIPLER. 10549 PAR 2 A AND B. VERIFIED INSTALLATION OF REPAIR DOUBLER AND TRIPLER PER ECRA 5611-01314 PART 21 THRU 22. OK TO SEAL PRIME AND PAINT. INSTALLED FASTENERS ON ON #3 WINDOW FRAME PER ECRA 5611-0
SUSPECT CRACK IN L3 WINDOW FRAME ON FWD. EDGE 2ND FASTENER FROM THE BOTTOM PERFORMED HFEC SURFACE INSPECTION OF L3 WINDOW FRAME AT SECOND FASTENER HOLE FROM THE BOTTOM OF FWD FRAME EDGE AND VERIFIED CRACK ACROSS FASTENER HOLE TO EDGES.REF 737 NTM PART 6-51-00-00 PROCEDURE 23. ACCOMPLISHED HFEC PER 6-51-00-00-23. CRACK TERMINATES APPROXIMATELY .310" FROM NEAREST FASTENER HOLE. SEE ATTACHED PIC. PER ENGINEERING REQUEST PERFORM SURFACE HFEC INPECTION OF FWD ADDING PIC. FRAME ATTACH HOLES TO VERIFY CRACK TO HOLE EDGE DISTANCE.
SUSPECT CRACK IN R3 WINDOW FRAME ON FWD. SIDE 2ND FASTENER FROM BOTTOM PERFORMED HFEC SURFACE INSPECTION OF L3 WINDOW FRAME AT SECOND FASTENER HOLE FROM THE BOTTOM OF FWD FRAME EDGE AND VERIFIED CRACK EMINATING AFT .200 FROM FASTENER EDGE. REF 737 NTM PART 6-51-00-00 PROCEDURE 23. VERIFIED ACCOMPLISHMENT OF PART 1, PARG. B. STEPS 2 (FIGURE4) & STEP 4 (FIGURE 6) OF ECRA 5611-01314 REV. B. WINDOW POST NEEDS INSPECTED PER FIGURE 6. ACCOMPLISHED PART 1, PARG. B. STEPS 2 (FIGURE4) & STEP 4 (FIGURE 6) OF ECRA 5611-01314 REV. B. WINDOW POST NEEDS INSPECTED PER FIGURE 6. VERIFIED COMPLETION OF ECRA 5611-01314 REV B. PART 1.B.6. OK TO INSTALL DOUBLER REF. ECRA 5611-01314 REV.B. PART.1.C AND VERIFIED DOUBLER INSTALLED PER ECRA 5611-01314 REV.B PART 1.C.2. FIG.12. REINSTALLED E-F POST FASTENERS PER ECRA 5611-01314 REV B. PART DRILLED INTERNAL DOUBLER PER ECRA 5611-01314 REV.B. PART.1.C AND INSTALLED INTERNAL REPAIR DOUBLER PER ECRA 5611-01314 REV.B PART 1.B.6. FIG.12. OK TO INSTALL.. 1.C.2.
FUSELAGE SKIN AT FRAME 737C BETWEEN STR 2L AND 2R CRACK DAMAGE.FOR REPAIR OF SKIN FRAME AT 737C BETWEEN FRAME 2L AND 2R (WORK ACCOMPLISHED BY V920656 AND AAR QC V923046) ADD EMP:V920656 COMPLIED WITH EC/RA 5331-02969 & EC/RA 5331-02968 FOR REPAIR OF SKIN FRAM AT 727C BETWEEN FRAME 2L AND 2R,
ON OR BEFORE JUNE 26, 2023, OR THE ACCUMULATION OF 28,974 TOTAL AIRCRAFT FLIGHT CYCLES, WHICHEVER COMES FIRST, PERFORM AN INSPECTION OF THE EXTERNAL DOUBLER/TRIPLER REPAIR TO THE FUSELAGE SKIN AT STA 747 - 787, STR 1 - 4L ON AIRCRAFT N15751 IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02968. INSPECTION OF THE EXTERNAL DOUBLER/TRIPLER REPAIR TO THE ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA FUSELAGE SKIN AT STA 747 - 787, STR 1 - 4L ON AIRCRAFT N15751 IN 5331-02968. ON OR BEFORE JUNE 26, 2023, OR THE ACCUMULATION OF 28,974 TOTAL AIRCRAFT FLIGHT CYCLES, WHICHEVER COMES FIRST, PERFORM AN DIP APPROVED FOR THE EXTERNAL DOUBLER/TRIPLER REPAIR TO THE TOMC-APPROVAL FROM SC1ELBYC COMMENT FUSELAGE SKIN AT STA 747 - 787, STR 1 - 4L. ON OR BEFORE JUNE 26, 2023, OR THE ACCUMULATION OF 28,974 TOTAL AIRCRAFT FLIGHT CYCLES, WHICHEVER COMES FIRST, PERFORM AN INSPECTION IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02968 QC QC REVIEW INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
ON OR BEFORE AUGUST 27, 2023, PERFORM AN INSPECTION OF THE EXTERNAL DOUBLER/TRIPLER REPAIRS TO THE FUSELAGE SKIN AT STA 727C, STR 3L ? 3R IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02969. 727C, STR 3L ? 3R ON AIRCRAFT N15751 IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02969. ON OR BEFORE AUGUST 27, 2023, PERFORM AN INSPECTION OF THE EXTERNAL DOUBLER/TRIPLER REPAIRS TO THE FUSELAGE SKIN AT STA FINAL INSP COMPLETED AND DOCUMENTED ON AAR NON-ROUTINE 99939519 ADD EMP:AAR INSP V920285 DIP APPROVED FOR EXTERNAL DOUBLER/TRIPLER REPAIRS TO THE TOMC-APPROVAL FROM SC1ELBYC COMMENT FUSELAGE SKIN AT STA 727C, STR 3L / 3R ON OR BEFORE AUGUST 27, 2023, PERFORM AN INSPECTION IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02969. INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
DURING A C CHECK AT AAR-RFD, HEAVY CORROSION WAS FOUND ON THE LO WER SURFACE OF THE WING CENTER SECTION FORWARD LOWER SKIN PANEL (P/N 111A4102-7) AT STA 540 UNDER THE LEFT-HAND DRAG LINK (P/N 1 43A0062-27) (REF AAR RFD NR 99939586) PERFORMED REPAIR OF CORROSION FOUND ON LEFT WING CENTER SECTION LOWER PANEL BS540 AND COMPLIED WITH EA 220206 AND EC/RA 5710-028 11 INITIATE DIPS IAW PART 1 STEPS 2,3 AND 4 OF EC/RA 5710-02811 (WORK ACCOMPLISHED BY AAR V934678 AND AAR QC 931821) FIRST, AND AT INTERVALS NOT TO EXCEED 36,000 FLIGHT CYCLES FORWARD LOWER SKIN PANEL ON AIRCRAFT N15751 IN ACCORDANCE WITH THEREAFTER, PERFORM AN INSPECTION OF THE WING CENTER SECTION PART 2, STEP 1 OF THE LATEST REVISION OF ECRA 5710-02811. ON OR BEFORE THE ACCUMULATION OF 64,141 TOTAL AIRCRAFT FLIGHT CYCLES OR 100,000 TOTAL AIRCRAFT FLIGHT HOURS,WHICHEVER COMES ON OR BEFORE THE ACCUMULATION OF 64,141 TOTAL AIRCRAFT FLIGHT CY TOMC-APPROVAL FROM SC1ELBYC COMMENT CLES OR 100,000 TOTAL AIRCRAFTFLIGHT HOURS, WHICHEVER COMES FIR ST, AND AT INTERVALS NOT TO EXCEED 36,000 FLIGHT CYCLESTHEREAFT ER, PERFORM AN INSPECTION OF THE WING CENTER SECTION FORWARD LOW ER SKIN PANEL ONAIRCRAFT N15751 IN ACCORDANCE WITH PART 2, STEP 1 OF THE LATEST REVISION OF ECRA 5710-02811. QC QC REVIEWED. INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
HEAVY CORROSION WAS FOUND ON THE LOWER SURFACE OF THE WING CENTER SECTION FORWARD LOWER SKIN PANEL AT STA 540 UNDER THE LEFT-HAND DRAG LINK. PERFORMED REPAIR OF CORROSION FOUND ON LEFT WING CENTER SECTION LOWER PANEL BS540 AND COMPLIED WITH EA 220206 AND EC/RA 5710-028 11 INITIATE DIPS FIRST, AND AT INTERVALS NOT TO EXCEED 36,000 FLIGHT CYCLES FORWARD LOWER SKIN PANEL ON AIRCRAFT N15751 IN ACCORDANCE WITH THEREAFTER, PERFORM AN INSPECTION OF THE WING CENTER SECTION PART 2, STEP 1 OF THE LATEST REVISION OF ECRA 5710-02811. ON OR BEFORE THE ACCUMULATION OF 64,141 TOTAL AIRCRAFT FLIGHT CYCLES OR 100,000 TOTAL AIRCRAFT FLIGHT HOURS, WHICHEVER COMES ON OR BEFORE THE ACCUMULATION OF 64,141 TOTAL AIRCRAFT FLIGHT CY TOMC-APPROVAL FROM SC1ELBYC COMMENT CLES OR 100,000 TOTAL AIRCRAFT / FLIGHT HOURS, WHICHEVER COMES FIR ST, AND AT INTERVALS NOT TO EXCEED 36,000 FLIGHT CYCLES / THEREAFT ER, PERFORM AN INSPECTION OF THE WING CENTER SECTION FORWARD LOW ER SKIN PANEL ON / AIRCRAFT N15751 IN ACCORDANCE WITH PART 2, STEP 1 OF THE LATEST REVISION OF ECRA 5710-02811. QC QC REVIEWED. INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
EMERGENCY LIGHTS CAPACTIY CHECK NO GOOD ON BATTERIES M1674 AND M 1669 (REF AAR NR 99939054).
BEGIN REPAIR AT L/H SIDE AT WASTE TANK VACUMM HOLE (REF AAR NR 9 9939552) 31-02932 INITIATE 2ND DIP FOR PLANNING TO CONTACT ENG FOR INSCPE CTION REQUIREMENTS ON REPAIR ON OR BEFORE JAN 10, 2024 (WORK ACC OMPLISHED BY V920656 AND V895387) COMPLIED WITH EC/RA 5331-02932 AND EA 220201 IR FOR STA 888-927 STR 20L-24L SKIN REPAIR PER EC/RA 5331-02932 INITIATE DIP FOR ON OR BEFORE FEB 10, 2024 PERFORM INSPECTION OF THE REPAIR AT STA 8 88-927 STR 20L-24L IAW PART 2 OF THE LATEST REVISION OF EC/RA 53 888-927,STR 20L-24L ON AIRCRAFT N15751 IN ACCORDANCE WITH PART 2 OF THE LATEST REVISION OF ECRA 5331-02932. ON OR BEFORE FEBRUARY 10,2024, PERFORM AN INSPECTION OF THE EXTERNAL DOUBLER/TRIPLER REPAIR TO THE FUSELAGE SKIN AT STA REVIEWED ECRA AND SUBMITTED ESFR ON OR BEFORE FEBRUARY 10, 2024, PERFORM AN INSPECTION OF THE TOMC-APPROVAL FROM SC1ELBYC COMMENT EXTERNAL DOUBLER/TRIPLER REPAIR TO / THE FUSELAGE SKIN AT STA 888 - 927, STR 20L - 24L ON AIRCRAFT N15751 IN ACCORDANCE WITH / PART 2 OF THE LATEST REVISION OF ECRA 5331-02932. QC QC REVIEWED. INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
TEMP PROBE LIGHT LIGHT ON PROBE P/N NIS EWR 29-3421-3-0006 GASKET P/N 29-3412-3-0007 AVIONICS UPDATE THERE IS NO POWER TO THE TAT PROBE AVIONICS T/S PER SSM 24-51-11 PG1 FOUND NO PWR TO TCAS AND TAT PROBE C/B'' TROUBLE SHOOTING CONTINUES SUSPECT LOST OF POWER TO XFER BUS S.FOUND C/B C3001 XFER BUS 1 TO BE BAD.NEEDS R&R NIS EWR. REMOVED P91 PANEL TO FACILITATE R&R OF C/B PER AMM 24-21-21-000- 801 INSPECTION ITEM MARKED BY MISTAKE R&R C/B C3001 XFER BUS 1 PER WDM 24-51-11. P91 PANEL REQUIRES INSTALL AND OPS CHECKS. INSTALLED P91 PANEL IAW AMM 24-21-21-400-801. ALL OPS CKS GOOD. PERF''D TEMP PROBE OPS CKS IAW AMM 30-31-00-730-801, ALL OPS NORMAL AT THIS TIME. OK TO CONTINUE. ADD EMP:U245814
STAB TRIM LITE ILLUMINATED IN FLIGHT WITH A SPEED TRIM FAILURE BOTH AIRCFAFT HAD TO BE FLOWN BY HAND NO AUTOPILOT PERFORMED STAB TRIM TEST, COLUMN SWITCHING MODULES AND NEUTRAL SHIFT SENSOR FAILED SEVERAL TIMES. FURTHER T/S REQUIRED. REF L/P 8537413, FOUND PHASE B MISSING FROM CB C3001. R&R''D CB C3001, PERF''D DFCS OPS TEST FOR STAB/SPEED TRIM SYS IAW AMM 22-11-00-740-801. ALL TESTS PASS, NO FURTHER DEFECTS NOTED. OK TO CONTINUE.
PDA 2 REF LOG PAGE 3676794; AIRCRAFT ARRIVED IN SAT WITH LOWER 13 INCHES OF APU FUEL LINE SHROUD DRAIN MAST MISSING. MAST P/N IS 346A2801-3. CORRECTIVE ACTION IS REPLACEMENT OF DRAIN MAST, REF L/P 3676794
FOUND 4EA.CRACKS ON RIGHT CENTER WING REAR SPAR VERTICAL RESSURE WEB1 CRACK STA.RBL 25-31.83. 1 CRACK STA RBL 31.83-40.2 CRACK S STA RBL 40-45.64. ALL CRACKS VERIFIED WITH HFEC AND CRCKS MARKED. REMOVED DAMAGED SECTION OF PESSURE DECK WEB AND INSTALLED REPAIR DOUBLER PER EC/RA#5710-02723,PART 1.
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 727D BETWEEN S-8L AN D S-9L HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SU PPORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) REPAIRED MAIN CABIN UPPER LOBE FUSELAGE FRAME STATION 727D BETWE EN S-8L AND S-9L. REF EA 5310-04716 REV I OP 1 FIG 3 AND EC/RA 5 311-02138 REV A ALL REQUIRED WORK AND DOCUMENTATION COMPLIED WITH
AFT CARGO FRAME STA 727C RBL 15 BETWEEN STR 25R AND 26R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED REF ECRA 5310-07631, SEE FLEETCYCLE L/P 9672870 FOR ALL WORK PERFORMED. ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHES 75000 TOTAL FLIGHT CYCLES. PLANNING TO CONTACT ENGINEERING AFTER 68000 TOTAL FLIGHT CYCLES BUT BEFORE 69000 FLIGHT CYCLES FOR INSPECTION REQUIREMENTS. FRAME REPAIRED REF ECRA 5310-07631, SEE FLEETCYCLE L/P 9672870 FOR ALL WORK PERFORMED. ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHES 75000 TOTAL FLIGHT CYCLES.
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA380 BETWEEN S-8R AND S-9R HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET.
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 747 BETWEEN S-8R AND S-9R HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) REPAIRED CABIN FRAME AT STA 747 STR8R PER ECRA 5310-07620.
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 440 BETWEEN S-8R AND S-9R HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) REPAIRED CABIN FRAME AT STA 440 STR8R PER ECRA 5310-07627.
AFT CARGO FRAME STA 747 RBL 15 BETWEEN STR 25R AND 26R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED REF ECRA 5310-07631
MAIN CABIN UPPER LOBE FUSELAGE FRAME BS 727D BETWEEN S-8L AND S-9L WAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET.
FRAME AT BS 500A BETWEEN S-8R AND S-9R CRACKED AT I /B FASTENER HOLE AC OUTLET EXTRUSION SUPPORT BRACKET. REPAIRED THE FRAME IAW ECRA 5 311-02138 AND EA 5310-04716 REV I OP1 FIG 3.
FRAME AT STA 480 BETWEEN S-8R AND S-9R CRACK AT I/B FASTENER HOLE AC OUTLET EXTRUSION SUPPORT BRACKET. REPAIRED FUSELAGE FRAME IAW ECR A 5311-02138 AND EA5310-04716 REV I OP1 FIG 3 .
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 380 BETWEEN S-8L AND S-9L HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPP ORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) REF FLEETCYCLE N/R 9666842 REPAIRED FRAME STA 380 S-7L AND S-8L PER EC/RA # 5311-02160. ADD EMP:U244023 SEE FLEETCYCLE N/R 9666842 FOR ALL WORK ACCOMPLISHED. DIP 53-DIP NEED TERM LIMITS ADDED. SEE FLEETCYCLE N/R 9666842 FOR ALL WORK ACCOMPLISHED. INITIATE A DTA DIP TO -ACCOMPLISH INSPECTION REQUIREMENTS ON OR ADD EMP:U244023 REPAIRED FRAME STA 380 S-7L AND S-8L PER EC/RA # 5311-02160. G TO CONTACT ENGINEERING AFTER 43,000 TOTAL FLIGHT CYCLES BUT BEFORE 44,000 TOTAL FLIGHT CYCLES FOR THE INSPECTION REQUIREMENT BEFORE THE AIRCRAFT REACHING 50,000 TOTAL FLIGHT CYCLES. PLANNIN . BEFORE THE AIRCRAFT REACHING 50,000 TOTAL FLIGHTY
AFT CARGO FRAME STA 727A RBL 15 BETWEEN STR 25 R AND 26 R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED AS REF ECRA 5310-07631 SEE FLEETCYCLE L/P 9672868 FOR WORK PERFORMED. VERFIED ACCOMPLISHMENT OF FRAME REPAIR REF. EC/RA 5310-07631
AFT CARGO FRAME STA 727D RBL 15 BETWEEN STR 25R AND 26R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED AS REF ECRA 5310-07631 SEE FLEETCYCLE L/P 9672871 FOR WORK PERFORMED. VERIFIED ACCOMPLISHMENT OF FRAME REPAIR REF ECRA 5310-07631
AFT CARGO FRAME STA 767 RBL 15 BETWEEN STR 25R AND 26R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED AS REF ECRA 5310-07631 SEE FLEETCYCLE L/P 9672873 FOR ALL WORK PERFORMED. VERIFIED ACOMPLISHMENT OF FRAME REPAIR REF. EC/RA 5310-07631
AFT CARGO FRAME STA 727E RBL 15 BETWEEN STR 25R AND 26R ELONGATED HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED AS REF ECRA 5310-07631 SEE FLEETCYCLE L/P 9672872 FOR ALL WORK PERFORMED. VERIFIED ACCOMPLISHMENT OF FRAME REPAIR REF. EC/RA 5310-07631
AFT CARGO FRAME STA 727B RBL 15 BETWEEN STR 25R AND 26R ELONGATE D HOLE WHERE SIDE PANEL ATTACHES. FRAME REPAIRED AS REF ECRA 5310-07631 REF FLEETCYCLE L/P 9672869 FOR ALL WORK PERFORMED. VERIFIED ACCOMPLISHMENT OF FRAME REPAIR REF ECRA 5310-07631
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA.400 BETWEEN S-8R AND S-9R HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUP PORT BRACKET (REPAIR PER W/C SEQ#1655 FIG 3 STEP 9). REMOVED DAMAGED SECTION OF FRAME AND INSTALLED REPAIR CHANNELS P ER EC/RA#5310-07619,REV.A,PART 1. INITIATED DIP TO "ACCOMPLISH I NSPECTION REQUREMENTS ON OR BEFORE THE AIRCRAFT REACHING 50,000 TOTAL FLIGHT CYCLES. PLANNING TO CONTACT ENGINEERING AFTER 43,00 0 TOTAL FIGHT CYCLES BUT BEFORE 44,000 TOTAL FLIGHT CYCLES FOR I NSPECTION REQUIREMENTS".SEE FLEET CYCLE L/P9666849 FOR ALL WORK ACCOMPLISHED. TOMC APPROVED, PLACE ON DIP TOMC-APPROVAL FROM SC1ELBYC COMMENT INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE. VERIFIED EC/RA 5310-07619 REV.A PART 1 COMPLETED AND DIP ISSUED REVIEWED QC REVIEW QC REVEIWED QC REVIEW
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA.480 BETWEEN S-8L/S- 9L HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET (REPAIR PER W/C SEQ#1655 FIG. 3 STEP 9) REPAIRED MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 480 BETWEEN S-8L & S-9L IN REF TO EA5310-04716 REV 1 AND EC/RA#5311-02138 REV A SEE FLEETCYCLE N/R#9666845 FOR ALL STEPS ACCOMPLISHED.
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 727D BETWEEN S-8R AN D S-9R HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SU PPORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) COMPLETED REPAIR OF FUSELAGE FRAME @ STA 727D S8R-S9R REF ECRA 5 311-02138 & EA 5310-04716I OP1 FIG 3 (REF FLEETCYCLE N/R#9666854 FOR ALL STEPS ACCOMPLISHED)
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 440 BETWEEN S-8L AND S-9L HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUPPORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9). COMPLETED REPAIR OF FUSELAGE FRAME @ STA 440 STR-8L AND STR-9L REF ECRA 5311-02138 & EA 5310-047161 OP1 FIG 3 (REF FLEETCYCLE N/ R# 9666844 FOR ALL STEPS ACCOMPLISHED)
MAIN CABIN UPPER LOBE FUSELAGE FRAME AT STA 787 BETWEEN S-8L AND S-9L HAS CRACK AT I/B FASTENER HOLE FOR AC OUTLET EXTRUSION SUP PORT BRACKET (REPAIR PER W/C SEQ #1655 FIG 3 STEP 9) REPAIRED MAIN CABIN UPPER LOBE FUSELAGE FRAME STATION 787 BETWEE N S8L & S9L. REF: EA 5310-047161 AND EC/RA#5311-02138 REV A. REF FLEETCYCLE 9666847 FOR ALL STEP ACCOMPLISHED.
NR 1 ENGINE HYD LOW PRESSURE LIGHT ON DURING CLIMBOUT. EMERGENCY DECLARED. REPLACED NR 1 ENGINE HYD PUMP IAW AMM 29-11-11-400-801-001. FLUSH HYD. SYS A REF AMM29-11-00-170-801. REPLACED SYS A PRESS AND RETURN FILTERS IAW AMM 29-11-61-400-801 AND 29-11-71-400-801. REPLACED NR 1 ENG CASE DRAIN FILTER REF AMM 29-11-51-400-801. NR 1 ENGINE EDP CASE DRAIN HOSE QUICK DISCONNECT IS BLOCKED WITH DEBRIS. REPLACED DRAIN HOSE QD IAW AMM 29-11-11-400-801-001.
AFT FLT ELT NEEDS REPLACEMENT, T HANDLE CORD IS MISSING. INSTALLED EMERGENCY LOCATOR TRANSMITTER (ELT) PER AMM 25-64-00- 400-801.
EMERGENCY LIGHTS ASSOCIATED WITH BATTERY PACK M1674 WILL NOT STAY ILLUMINATED. REMOVED AND REPLACED BATTERY PACK AT M1674 IAW AMM 33-51-06-960-805. OPS CHECK GOOD IAW AMM 33-51-06-960-805 MFR PN D717-01-100 STA 952 WL-290 BL-L014.
EMERGENCY LIGHTS ASSOCIATED WITH BATTERY PACK M1675 WILL NOT STAY ILLUMINATED. REMOVED AND REPLACED BATTERY PACK AND POWER SUPPLY AT M1675 IAW AMM 33-51-06-960-805, 33-51-06-960-806, AND WDM 33-51-12 . OPS CHECK GOOD IAW AMM 33-51-06-960-806.
EPL AT O/H BIN 3BA IS INOP. RELAMPED EMERGENCY AREA LIGHT AT SEAT ROW 3AB IAW AMM 31 -51-03-960-801. OPS CHECK TO BE ACCOMPLISHED ON N/R 6187470
CB AT B10/EMER CHARGER FOUND POPPED. MECH RESET AND IT POPPED AGAIN. FOUND EMERGENCY BATT PACK M1669 FAULTING. REPLACED POWER SUPPLY AND BATT PACK PER AMMM33-51-06, OPS CHECKS NORMAL.
HFEC DETECTED CRACK INDICATIONS AT STATION 727B AT LBL 45.50, SPLICE STRAP, THREE HOLES EACH, FWD INBD, AFT INBD, AFT OTBD. ACCOMPLISHED STRAP REPAIRS IAW RES-WI 2009633-2 & ECRA 5320-02627 INBD & OTBD.
HFEC INSPECTION DETECTED A CRACK INDICATION AT STATION 727B, RBL45.50, TWO HOLES EACH, AFT INBD & AFT OTBD. ACCOMPLISHED STRAP REPAIRS IAW RES-WI 2009633-4 & ECRA 5320-02627.
HFEC DETECTED CRACK INDICATIONS AT STATION 727B AT LBL 45.50, SPLICE STRAP, THREE HOLES EACH, FWD INBD, AFT INBD & AFT OTBD. ACCOMPLISHED STRAP REPAIRS IAW RES-WI 2009633-2 & ECRA 5320-02627, IND & OTBD.
HFEC DETECTED A CRACK INDICATION AT STATION 727B, LBL 24.75, INBD AFT HOLE, ONE EACH. ACCOMPLISHED STRAP REPAIRS IAW RES-WI 2009633-1 & ECRA 5320-02627.