N587AS
Registered owner: ALASKA AIRLINES INC, WA (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
FA REPORTS L1 DOOR DIFFICULT TO OPEN AND CLOSE HINGE MECHANISM AND HANDLE STICKY. GROUNDED - YES. PERFORMED FIM TASK 52-10 TASK 807. LUBRICATE L1 DOOR SERVICING-MECHANISM PER AMM TASK 12-25-11-640-802. FOUND DOOR GUIDE BALL MISS-ALIGNED ON TRACK. ADJUSTED UPPER GUIDE ARM PER AMM TASK 52-11-00-820-801. FWD ENTRY DOOR OPS CHECKED GOOD PER AMM TASK 52-11-00-700-804. A/C RESTORED TO NORMAL CONFIG.
FA REPORTS L-1 BOARDING DOOR DIFFICULT TO OPEN. GROUNDED - YES. LUBRICATED DOOR HINGE PLATES REF MM 12-25-11640-801. CYCLED DOOR SEVERAL TIMES OPS CK OK.
AFT CARGO L/H CARGO TRACK STA 727I TO STA 727E CRACKED. GROUNDED - YES. REPAIRED AFT CARGO TRACK L/H STA 727I TO 727E IAW B737-800 SRM 53-00-53-2A-3.
AFT CARGO R/H CARGO TRACK STA 727C TO STA 767 CRACKED. GROUNDED - YES. REMOVED AND REPLACED CARGO TRACK IAW B737-800 SRM 53-00-53-2R-3.
AFT CARGO RT TRANSITION CORRODED, RBL 24, BS 747 - 727A. GROUNDED - YES. REMOVED CORROSION FOUND TO BE OUT OF LIMITS, REMOVED AND REPLACED TRANSITION PANEL IAW SRM 53-00-53-2R-5.
AFT CARGO L/H TRANSITION CORRODED LBL 24 STA 787 TO 727A. GROUNDED - YES. REMOVED DAMAGE ON AFT CARGO L/H TRANSITION LBL24 STA 787 TO 727A FOUND TO BE OUT OF LIMITS REMOVED AND REPLACED L/H TRANSITION PANEL IAW B737-800 SRM 53-00-53-2R-5W: 2" O: 0.040 R: 0 L: 2" D: 0.040.
FA REPORTS L1 DOOR DIFFICULT TO OPEN AND HAS POSSIBLE TORN SEAL LOWER RIGHT SIDE OF DOOR. GROUNDED - YES. PERFORMED BVI OF DOOR SEAL NO TORN SEAL OR DEFECTS NOTED. CLEANED DOOR TRACK FOR DEBRIS. PERFORMED OPS CHECK L1 DOOR OPEN & CLOSE IAW AMM 52-11-00 OPS CHECK GOOD.
L1 DOOR WOULD NOT OPEN FROM INSIDE. GROUNDED - YES. PREFORMED OPS CHECK L1 DOOR OPEN + CLOSE FUNCTION AMM 52-11-00. CHECKS OK AT THIS TIME - PERFORMED GVI L1 DOOR AREA LINER INSTALLED. - NO DEFECTS.
SIDEWALL EXIT/SALIDA LT LENS MISSING AT ROW 16 ABC. GROUNDED - YES. REPLACED LT LENS ON EXIT/SALIDA LT AT ROW 16 ABC SIDEWALL. REF AMM 33-51-01. OPS CHK GOOD.
RAMP REPORTS R1 DOOR DIFFICULT TO CLOSE. GROUNDED - YES. INSPECTED AND FOUND UPPER TORQUE TUBE LINK ASSY TO GUIDE ARM INTERFACE HAS EXCESSIVE PLAY. VERIFIED R1 DOOR OPENS AND CLOSES. A/C RELEASED FOR THE SPECIAL FLIGHT TO SEA PER SPECIAL FLT PERMIT DATED 5/27/2025 TO ACCOMP REPAIR TO THE R1 DOOR. REMOVED AND REPLACED R1 DOOR UPPER HINGE LINK REF AMM 52-41-41-400-801. R1 DOOR ADJUSTMENT AND OPS TEST GOOD PER AMM 52-41-00-820-801.
R1 DOOR -FWD SERVICE- IS DIFFICULT TO CLOSE UPPER RIGHT SIDE OF DOOR NEEDS TO BE PUSHED TO ENGAGE CAM. GROUNDED - YES. PERFORMED LUBING ON DOOR ROLLER & CLOSED R1 DOOR SEVERAL TIMES PER AMM 52-41-00. OPS NORMAL.
L1 DOOR FAILED POST HEALTH CHECK SRXR430X. GROUNDED - YES. PERFORMED FWD ENTRY DOOR UPPER AND LOWER GATE BALL ADJUSTMENT AND RECHECKED FWD ENTRY DOOR POST HEALTH CHECK TORQUE MEASUREMENT IN REF TO B737 AMM 52-11-00-820-801-AND AMM 52-11-00-700-804 ADJUSTMENT AND HEALTH CHECK TORQUE MEASUREMENT GOOD SRXR430X.
AT DRAIN MAST ON THE RIGHT-HAND SIDE HAS CORROSION SRXR430X. GROUNDED - YES. ACCOMPLISHED CATEGORY "A" REPAIR ON FUSELAGE SKIN P/N 147A3400-4 BY AFT DRAIN MAST ON THE RIGHT-HAND SIDE AT STA 986.5 TO STA 1006 AND STR 24L TO 25L. IAW 800-53EA-28423 REV00 SRXR430X.
CORROSION ON FASTENERS FWD OF OUTFLOW VALVE BETWEEN STA 986 AND STA 967 SRXR430X. GROUNDED - YES. ACCOMPLISHED CATEGORY "A" REPAIR ON FUSELAGE SKIN P/N 147A3400-4 BETWEEN STA 967 AND STA 986 AT AND STR 25R TO 27R. IAW EA800-53EA-28423 REV00 SRXR430X.
RIGHT OVER WING EXIT (ROW 17) BURNED OUT. GROUNDED - YES. SECURED LIGHT BULB AND OPS. GOOD. OK FOR SERVICE.
RH AFT EMERGENCY EXIT DOOR EMERGENCY ILLUMINATION LIGHT (IN UNIT AFT) INOP. GROUNDED - YES. RELAMPED AS REQUIRED. OPS TEST GOOD.
PLASTIC "EXIT" SIGN FELL OFF ROW 17 ABC. GROUNDED - YES. REINSTALLED ROW 17 ABC EMERGENCY EXIT SIGN LENS. OPS CKS GOOD. REF AMM 33-51-01.
FA REPORTS L1 DOOR DIFFICULT TO OPEM/CLOSE MIG-2C #40-0054465 HAS BEEN INITIATED, MIG-2C 40-0054466 & 40-0054467 INITIATED. MIG-2C #40-0054468 HAS BEEN INITIATED. GROUNDED - YES. DURING INSPECTION OF THE L1 FORWARD ENTRY DOOR FOUND LOWER HINGE PIN AND BEARING LOOSE AND WORN PARTS REQUIRED A BELTRAN 02/08/2024. REMOVED L-1 DOOR FROM A/C REF AMM REF.AMM 52-11-00-000-802 & AMM 52-11-41-000-802 09711 02/08/2024 ACCOMPLISHED MEASURMENT OF LWR L1 DOOR TORQUE TUBE LWR HINGE PIN CHECKS GOOD REF BOEING DRAWING 65C37130 ITEM # 41914 30981 8FEB24 LOWER HINGE BUSHINGS MEASURE WITHIN DESIGN DIMINSIONS REF BOEING DRAWING 65-25838 VIEW C3,C3 65613 9FEB24 BEGAN INSTALLATION OF L1 DOOR REF AMM TASK 52-11-00-400-802 STEPS 3.A THRU G.(5)(A)(B)(C) AND (D) 30981 9FEB24 ASA37INSP 30153 2/09/24 COMPLETED MIG-2C #40-0054465, #40-0054466, #40-0054467 AND #40-0054468 64232 COMPLETED FWD ENTRY DOOR INSTALLATION PER AMM 52-11-00.
UPON LANDING, PRESSURIZATION SYSTEM DID NOT OPEN THE OUTFLOW VALVE TO DEPRESSURIZE THE AIRCRAFT. GROUNDED - YES. BOTH CONTROLLERS, PERFORMED DCPC BITE REF FIM 21-31 TASK 801. NO EXISTING FAULTS NOTED. NO FAULTS NOTED ON INBD FL OR PREVIOUS ONE. GROUND TEST BITE PASSES BOTH CONTROLLERS.
DURING DESCENT CHECKLIST RECALL - LEFT PACK LIGHT ILLUMINATED AND IS RESETTABLE. GROUNDED - YES. (RESOLVED ON W/O: 1974348 TASKCARD: N/R-00002 ) CONFIGURATION CHANGES REVERSED FOR MEL 21-5C. LH RAM AIR INLET ACTUATOR REMOVED AND REPLACED PER AMM 21-51-21-000-801 AND AMM 21-51-21-400-801. FIVE MIG-51A TAGS INSTALLED & REMOVED. ALL OPERATIONAL CHECKS PASS. THIS REMOVES MEL 21-5C & CN: 21049587. SEAMC DAVE NOTIFIED.
L PACK LIGHT ILLUMINATED SINGLE CHANNEL FAULT. GROUNDED - YES. REF FIM 21-53 TASK 821, PERFORMED PZTC 1 + 2 BITE, PZTC 1 HAD RAM AIR ACTUATOR FAULT LIGHT. REF FIM 21-62 TASK 837 PERFORMED OPS TEST OF PACK 1, OPS TEST GOOD, L/H PACK LIGHT NOT ILLUMINATED, PERFORMED PZTC 1 (AND 2) BITE AGAIN, NO FAULTS, PZTC 1 FAULT CLEARED AND DID NOT RETURN, DURING BITE "VERIFY" L/H RAM AIR ACTUATOR OPS NORMAL. PER FIM THIS WAS AN INTERMITTENT FAULT. REMOVES CN: 20002587 SEAMC JOE NOTIFIED. THIS CLEARS MEL 21-32B.
FOLLOW-UP TO #2 IDG CONTINUED FREQUENT SERVICING. GROUNDED - YES. FOUND LEAK AT IDG DRAIN PAD. REF AMM 24-11-00. ETOPS PART VERIFICATION SEAMC WILL NOTIFIED. REMOVED AND REPLACED #2 IDG REF AMM 24-11-11. SUCCESSFUL ETOPS GROUND VERIFICATION SEAMC WILL NOTIFIED. REF LOG PAGE 60641001 FOR OIL / FILTER CHANGE DEFERRAL. THIS CLOSES TSR715105.
RIGHT APU GEN SWITCH IS LOOSE. GROUNDED - YES. SECURED AS REQUIRED SWITCH NO LONGER LOOSE.
LEFT TEMP PROBE (A) FAILED - LIGHT ILLUMINATED ENROUTE @ FL 360 TEMP -27 DEG C. GROUNDED - YES. (RESOLVED ON W/O: 1968753 TASKCARD: N/R-00001 ) REPLACED LEFT TAT PROBE WITH SERVICABLE UNIT, HEATER SYSTEM TEST AND INSTALLATION TEST OK. REF AMM 34-21-06. ETOPS SYSTEM GROUND VERIFICATION TEST SUCCESSFUL. CLEARS MEL 30-7B, ALL PLACARDS REMOVED. SEAMC PETER NOTIFIED.
FOLLOW-UP TO #2 IDG FREQUENT SERVICING----(#PRI2)-----ETOPS SIGNIFICANT SYSTEM----. GROUNDED - YES. (RESOLVED ON W/O: 1968229 TASKCARD: N/R-00001 ) REMOVED AND REPLACED FILL VALVE IAW CMM 24-11-85 AND VENT VALVE IAW AMM 24-11-00-700-804. PERFORMED OPS CHK. OPS CHK GOOD. SEAMC PETER NOTIFIED.
APU EGT GUAGE READS 0 UPON START AND WHILE RUNNING, EVENTUALLY STARTED WORKING AFTER 5 MIN RUNTIME. GROUNDED - YES. ON DEFERRAL.
ELEC LIGHT ILLUMINATED ON AVH PANEL. GROUNDED - YES. ACCOMPLISHED FIM T/C 24-34/802. SPCU FAULT CLEARED. NO HISTORY PAST 30 DAYS. A/C OK FOR SERVICE.
LEFT PACK LIGHT ILLUMINATES ON RECALL. GROUNDED - YES. (RESOLVED ON W/O: 1961368 TASKCARD: N/R-00001 ) ACCOMPLISHED FIM TASK 21-62 TASK 801. ZONE TEMP 1 RETURNED FAULT TRIM VALVE ZONE ACCOMPLISHED FIM TASK 21-62 TASK 835. CIRCUT BRAKER RESET (CO1170, CO1158, CO1159). RE ACCOMPLISHED FIM TASK 21-62 TASK 801 AND FAULT WAS NO LONGER PRESENT. THIS CLEARS MEL FROM L/P 60495071. SEAMC ANDY NOTIFIED.
LEFT PACK LIGHT ON. GROUNDED - YES. REL PER MEL 21-32B L PACK CONT INOPAUTH BY SEAMC LAMONT @ 1721ZACCOMPLISHED B737-800 FIM 21-62 TASK 801#1 PZTC FAULT RAM AIR ACTUATOR ON PREVIOUS LEG.BITE/VERIFY TEST OF PZTC PASSED. NO FURHTER DEFECTS MEL 21-32B CLEARED.
FAULT LIGHT ILLUMINATES DURING APU START. GROUNDED - YES. ON DEFERRAL.
HF #2 RADIO DISPLAYS "FAIL-FAIL" ON THE DISPLAY. GROUNDED - YES. RESET CIRCUIT BREAKER FAILED CLEARED PERFORMED HF#2 COM SYSTEM BIT PROCEDURE IAW B737-800 FIM 23-11 TASK 801 BIT CHECK GOOD.
WIRING ATTACHED TO THE L1 WINDOW UPPER RIGHT HAND SIDE HAS SMALL ORANGE GLOW WHICH EXTINGUISHES WHEN FWD WINDOW HEAT IS TURNED OFF. GROUNDED - YES. VERIFIED "GLOW" IS BAD HEATER ELEMENT. REMOVED AND REPLACED L1 WINDOW, REF B737-800 AMM 56-11-11-000-801/-400-801. ACCOMPLISHED L1 WINDOW RESISTANCE TAP REF B737-800 AMM 56-11-11.
LEFT PACK LIGHT ILLUMINATED ON RECALL. GROUNDED - YES. PERFORMED PACK TEMP CONTROL BITE PROCEDURE REF B737-800 FIM 21-62 TASK 801 ON #1 AND #2 ZONE TEMP CONT'S FOUND TCV LIGHT ILLUMINATED ON #2 ZONE TEMP CONT. AND GOES AWAY WITH RESET. #1 ZONE TEMP CONTROL BITE CHECKS GOOD. PERFORMED A SECOND BITE CHECK NO FAULTS FOUND.
FWD WET AREA FLOOR PANEL 141A5810-175 CORNER TAB CRACKED. GROUNDED - YES. REPAIRED FLOOR PANEL CORNER TAB IAW B737-800 SRM 53-00-50-2R-4 AND 53-00-50-2R-0.
UPON REMOVAL OF AFT PIT DOOR SURROUND FWD SHIELD, FOUND SUPPORT ANGLE TO BE CORRODED.TIPR833K. GROUNDED - YES. REMOVED CORROSION FROM THE AFT PIT DOOR SURROUND ANGLE PER B737-800 SRM 53-60-15-1A-1.2.A. ORIG THICKNESS IS .050" PER B737-800 SRM 53-60-15-0I-1 TABLE 4. REMOVED .011", REMAINING THICKNESS IS .039" AND IS FOUND TO BE OUT OF LIMITS PER B737-800 SRM 53-60-15-1A-1.4.H.(2). REMOVED AND REPLACED AFT PIT DOOR SURROUND SUPPORT ANGLE PN: 146A8125-53 PO: 1054886.4 IAW B737-800 SRM 51-40-02 & SRM 51-40-05.
MAIN CABIN FLOR SUPPORT STRUCTURE IS CRACKED AT STA 540 APPROX LBL1. GROUNDED - YES. REMVOED CRACKED FLOOR SUPPORT /BREAK PNL ASSY IAW B737-800 SRM 51-40-02DRILLED TO FIX NEW FLOOR SUPPORT /BREAK PNL ASSY IAW B737-800 ARM 51-40-05 AND BAC DWG 143A0060 REV A.
MAIN CABIN, STA 344, LBL 10+-, CORROSION AROUND FASTENER HOLE. GROUNDED - YES. EVALUATED AND REMOVED CORROSION IAW B737-900 SRM 53-10-51-01-2 AND B737-800 SRM 53-10-51-1A-1. ORIGINAL T. .175", REMOVED .085", REMAINING .090", FOUND TO BE OUT OF LIMITS IAW B737-800 SRM 53-10-51-1A-1 DETAIL C. ACCOMPLISHED T. CHORD REPAIR AS REQUIRED IAW B737-800 SRM 53-10-51-2R-10.
AFT WET AREA RIGHT HAND SIDE @ STATION 992 +/- BL31 GALLEY SUPPORT INTERCOSTAL CORRODED. DOT: N713. GROUNDED - YES. REMOVED CORROSION. 100% MATERIAL LOSS, OUT OF LIMITS IAW B737-800 SRM 53-70-51-1A-1 FIG 104. REMOVED SUPPORT ANGLE IAW B737-800 SRM 51-40-02. DRILLED TO FIT NEW SUPPORT ANGLE IAW B737-800 SRM 51-40-05 AND BAC DWG 147A5700 REV A. INSTALLED NEW SUPPORT ANGLE IAW B737-800 SRM 51-40-02 AND BAC DWG 147A5700 REV A.
MAIN CABIN, STA 298+-, RBL 54, MOP SILL HAS CORROSION.DOT: N565. GROUNDED - YES. REMOVED CORROSION IAW B737-800 SRM 51-10-02.ORIGINAL THICKNESS 0.063, REMOVED 0.014, REMAINING THICKNESS 0.049. FOUND TO BE OUT OF LIMITS IAW B737-800 SRM 53-10-15-1A-2 DETAIL D. REMOVED OUT OF LIMITS MOP SILL STRAP IAW B737-800 SRM 51-40-02. DRILLED TO FIT NEW STRAP IAW B737-800 SRM 51-40-05 AND BAC DWG 141A8310 REV B. INSTALLED NEW STRAP IAW B737-800 SRM 51-40-02 AND BAC DWG 141A8310 REV B. REMOVED DOT: N565.
MAIN CABIN FLOOR SUPPORT STRUCTURE IS CRACKED AT STA 540 APPROX RBL 1. GROUNDED - YES. REMOVED CRACKED FLOOR SUPPORT / BREAK PNL ASSY IAW B737-800 SRM 51-40-02. DRILLED TO FIT NEW FLOOR SUPPORT/ BREAK PNL ASSY IAW B737-800 SRM 51-40-05 AND BAC DWG 143A0060 REV A.INSTALLED NEW FLOOR SUPPORT / BREAK PNL ASSY IAW B737-800 SRM 51-40-02 AND BAC DWG 143A0060 REV A.
AFT PIT DOOR SURROUND FWD SHIELD HAS CORROSION.TIPR833K. GROUNDED - YES. REMOVED CORROSION FROM THE AFT PIT DOOR SURROUND FWD SHIELD PER B737-800 SRM 53-60-15-1A-1.2.A. ORIG THICKNESS IS .050" PER B737-800 SRM 53-60-15-0I-1 TABLE 4. REMOVED .020", REMAINING THICKNESS IS .030" AND IS FOUND TO BE OUT OF LIMITS PER B737-800 SRM 53-60-15-1A-1.4.H.(2). REMOVED AND REPLACED AFT PIT DOOR SURROUND FWD SHIELD PN: 146A8127-12 PO: 1054886.5 IAW B737-800 SRM 51-40-02 & SRM 51-40-05.
EMERGENCY LIGHT BATTERY PACKS FAILED CAPACITY CHECK GROUNDED - YES. REPLACED FOUR BATTERY PACKS S/N 162201, 202540, 211441, 211447.
EMERGENCY LIGHT SYSTEM BATTERY PACK FAILED CAPACITY CHECK FOR BATTERIES M1670, M1671, M1672, M1673. GROUNDED - YES. REPLACED BATTERY PACKS M1670, M1671, M1672 AND M1673 IAW ASA B737NG MM 33-51-06-960-805, OP CHECK GOOD ASA B737NG MM 33-51-06-960-805.
NO N1 OR N2 ON #2 ENGINE START. GROUNDED - YES. REMOVED AND REPLACED #2 ENGINE START VALVE IAW B737-800 AMM 80-11-03.
BOTH PACK LIGHTS ILLUMINATE ON RECALL. LIGHTS EXTINGUISH WHEN MASTER CAUTION IN RESET. GROUNDED - YES. PERFORMED B737-800 AMM 21-61-00 PACK/ZONE TEMP CONTROL BITE TEST. FOUND FAULT FOR RIGHT AND LEFT RAM AIR DOOR ACTUATORS. FAULT WAS RESET AND OPS CHECKED GOOD. PERFORMED AMM 20-60-99 AIRCRAFT POWER DOWN FOR TROUBLESHOOTING AND PERFORMED AMM 21-61-00 PACK/ZONE TEMP CONTROL BITE TEST TO VERIFY NO FAULTS. NO FAULTS TRIGGERED. OPS CHECK GOOD.
WHILE ACCOMPLISHING TSR713599, FOUND #1 TANK UNITS, 5 AND 6, OUT OF LIMITS PER AMM 28-41-21-710-801. GROUNDED - YES. ACCOMPLISHED A TANK & COMP UNITS TEST REF B737-800 AMM 28-41-21/501. VERIFIED TU'S 5&6 REQUIRE REPLACEMENT. REMOVED PANEL 532EB AND 532FB FOR ACCESS. REPLACED TU'S 5&6 REF AMM 28-41-21/401. ALL CAPACITANCE VALUES NOW WITHIN LIMITS REF AMM 28-41-21/501. INSTALLED PANELS 532EB AND 532FB REF AMM 22-11-11-400-801. ACCOMPLISHED FUEL QTY AND SYS TEST, OPS NML REF AMM 28-41-00-730-801. ACCESS PANELS HAVE NO LEAKS REF AMM 28-11-00-400-801.
LEFT PACK LIGHT ILLUMINATES DURING RECALL AND RESETS WHEN MASTER CAUTION PUSHED. FOLLOWED ASA QRH AND BOTH PACK LIGHTS ARE EXTINGUISHED. GROUNDED - YES. #1 PACK TEMP CONTROL BITE LOGGED RAM AIR DOOR ACT, FAULT RESETS. ACCOMPLISHED BITE TEST FOUR MORE TIMES, NO FAULTS LOGGED. NO HISTORY. REF B737-800 FIM 21-62 TASK 801.
RIGHT PACK LIGHT ILLUMINATED, RESET ON MASTER CAUTION RESET. GROUNDED - YES. CONFIRMED FAULT, R/H PACK LIGHT ILLUMINATES WHEN RECALLED. NO.2 PACK/ZONE TEMP CONTROLLER SHOWS HARD FAIL "TCV-2". REMOVED & REPLACED TCV-2 (V141) REF B737-800 AMM 21-51-10.
#1 ENGINE FIRE DISCHARGE LIGHT WON'T ILLUMINATE. GROUNDED - YES. REMOVED AND REPLACED #1 ENGINE RIGHT CORE FIRE DETECTOR ASSY REF B737-800 AMM TASK 26-11-01-000/400-801. PERFORMED OP TEST REF TASK 26-11-00-710-801, OP TEST PASS WITH #1 ENGINE FIRE DISCHARGE LIGHT ILLUMINATING AS REQUIRED.
APU DET INOP LIGHT ILLUMINATED. GROUNDED - YES. REMOVED AND REPLACED APU FIRE DETECTION LOOP IN TAIL CONE. OPS CK GOOD. REF B737-800 AIPC 26-15-01. REF CMM 26-10-85.
APU DET INOP LIGHT ILLUMINATED. GROUNDED - YES. ON DEFERRAL.
DURING CLIMB A FUEL LIGHT WAS NOTICED ON THE LEFT FUEL TANK QUANTITY THE LEFT QUANTITY WAS 7.5 AND THE RIGHT QUANTITY WAS 8.5 THE CENTER WAS 22.5 ALL FUEL PUMPS WERE SELECTED ON AT THE TIME, AND THE CROSSFEED VALVE WAS CLOSED. WE RAN THE FUEL IMB CHECKLIST WHICH HAD US TRANSFER MAIN FUEL UNTIL BOTH WARMS EVEN AT 7.5 AND THEM RESUMED NORMAL OPS. GROUNDED - YES. C/W FUEL BOOST PUMPS OPERATIONAL TEST IAW B737-800 AMM 28-22-41. TRANSFERED FUEL FROM WINGS TO CENTER & BACK TO WINGS. NO DEFECT NOTED.
HEADING BUG LOCKED UP AT GATE ON 322 HEADING. GROUNDED - YES. REMOVED AND REPLACED MCP REF B737-800 AMM 22-11-34.
DURING CRUISE HEADING BUG LOCKED UP ON HEADING 336. UNABLE TO CHANGE HEADING. GROUNDED - YES. ACCOMPLISHED B737-800 FIM 22-11 TASK 801. DFCS BITE TEST GOOD. MCP LRU OPS TEST PASSED. ALL REQUIRED LLM TEST PASSED. HEADING KNOB ON MCP VERIFIED TO CHANGE HEADING ON MCP AND SELECTED HEADING INDICATIONS NORMALLY ON BOTH PDFS AND NDS.
#1 HANDLE DOES NOT ILLUMINATE DURING FIRE TEST. GROUNDED - YES. REPLACED FIRE DETECTION HARNESS MW0316 LOOP PER B737-800 AMM 26-11-02, INTERMITTENT FAULT. WHILE CLOSING T/R AND DOING A BITE TEST, LOOP B LIGHT FLICKERING. REF AMM 26-10-01/401 REMOVED AND REPLACED FIRE DETECTION UNIT, PERFORMED OPS AND BITE TEST SEVERAL TIMES AND PASSED BOTH #1,2 ENGINE FIRE LOOP-B WORKS NORMAL.
#1 ENGINE FIRE DETECT INOP IN SYSTEM A OVERHEAT. GROUNDED - YES. TESTED ENGINE FIRE DETECTION SYSTEM, FOUND #1 ENGINE WAS FAILING. PERFORMED BITE PROCEDURE FOR ENGINE FIRE DETECTION, #1 ENGINE CHANNEL A SHOWED TOP CORE LOOP FAILING. FOLLOWED BOEING B737-800 FIM 26-10-00 FOR RIGHT CORE FIRE DET. FOUND AN OPEN WHILE CHECKING RESISTANCE, FOUND FLUCTUATION WHILE MOVING A CORE LOOP. REMOVED AND REPLACED TOP RIGHT CORE ENGINE FIRE DETECTION LOOP FOR #1 ENGINE IN REFERENCE WITH B737-800 AMM 26-11-01, OPS CHECK FAILED. CONTINUED TROUBLESHOOTING, FOUND RING TERMINAL ON BOTTOM CORE FIRE DETECTION FIRE LOOP, REMOVED AND REPLACED RING TERMINAL FOR HARNESS IN REFERENCE WITH MEGGITT SAFTEY SYSTEMS 26-10-87, OPS CHECK GOOD.
MAP FLAG ON CAPT MFD. GROUNDED - YES. RESET RIGHT FMC REF B737-800 AMM 34-61-00-860-801. OPS TEST NORMAL.
WHILE ACCOMPLISHING ASA T/C SBCFM56-7B-72-1074-1 NOTED THAT THE AFT SIDE OF THE 3RD STAGE J-HOOK IS COMPLETELY WORN THROUGH AT BOTH THE 6 O'CLOCK AND THE 12 O'CLOCK POSITIONS. SEE INSP SERVER FOR PICTURES AND REPORT. PER T/C STEP 8 ENGINE MUST BE REMOVED WITHIN 10 CYCLES. ENGINE SERIAL # 894536 POSITION 1. GROUNDED - YES. REMOVED #1 ENGINE S/N 894536 REF ASA SHOP WO 1933328. INSTALLED ENGINE S/N 896992.
RIGHT WING ANTI-ICE VALVE FAILED IN THE CLOSED POSITION. GROUNDED - YES. REMOVED AND REPLACED RIGHT WING THERMAL ANTI ICING SHUTOFF VALVE REF B737-800 AMM 30-11-11. OPS AND LEAK CHECK GOOD. ETOPS GROUND VERIFICATION SUCCESSFUL.
#2 HF RADIO HEAD DISPLAYS "FAIL" ON BOTH ACTIVE & STANDBY FREQUENCY WINDOW- RADIO DOES RECEIVE & TRANSMIT. GROUNDED - YES. REBOOTED #2 HF XCVR HF BITE CK OK REF. B737-800 FIM 23-11 TASK 801 ALSO RADIO CK W/ SFO LOUD & CLEAR ON HF2. ETOPS GND VERIFICATION COMPLETE.
#2 DRIVE LIGHT ILLUMINATED ON CLIMB OUT. GROUNDED - YES. REMOVED AND REPLACED #2 IDG REF B737-800 AMM 24-11-11.
REPEATED ATTEMPTS TO CONTACT DISPATCH VIA SATCOM WAS UNSUCCESSFUL. WE COULD HEAR THEM, THEY COULD NOT HEAR US. SAME RESULT WHEN DISPATCH CALLED US. WE TRIED BOTH CAPT AND FO COMM PANELS BUT WITH THE SAME RESULT. GROUNDED - YES. PERFORMED OPS TEST OF SATCOM SYSTEM REF B737-800 AMM 23-15-00-730-801. DISPATCH HEARD VOICE CLEARLY FROM ALL POSITIONS. NO HISTORY 90 DAYS. A/C OK FOR SERVICE.
#2 ENGINE S/N 894549 REF ASA T/C SBC FM 56-7B-72-1074-1, THIRD STAGE VSV SEGMENT AT 4 O'CLOCK SEAL SEGMENT GAP IS GREATER THEN .500, J HOOK MISSING AND STATOR SHROUD HAS MATERIAL LOOSE & MISSING. GROUNDED - YES. REMOVED AND REPLACED #2 ENGINE. REF ASA SHOP W/O #1924396.
ELEC LIGHT ILLUMINATED. GROUNDED - YES. BITE SHOWS STAT INV INOP FAULT. ACCOMPLISHED B737-800 FIM 24-34 TASK 801. FAULT CLEARS AND OPS NORMAL REF B737-800 AMM 24-31 TASK 801 BITE PROCEDURE.
AUTO THROTTLE ARMED GREEN LIGHT IS INOP. AUTO THROTTLE WORKS FINE. GROUNDED - YES. AUTO THROUTTLE ARM GREEN LIGHT OPS NML. REF INSTLN TEST NOTE REF B737-800 AMM 22-11-34-860-004.
#2 ENGINE TAI VALVE CONNECTOR BACK SHELL IS BROKEN OFF. GROUNDED - YES. REMOVED AND REPLACED MW0313 ON #2 ENGINE ALL TESTS CK GOOD REF B737-800 AMM 71-51-03-000/400-801-F00.
#1 HF RADIO INDICATES FAIL ON PREFLIGHT CHECK. GROUNDED - YES. #1 HF TRANSCEIVER WILL NOT TEST. REPLACED #1 HF TRANSCEIVER REF B737-800 AMM 23-11-21-400-801. GROUND VERIFICATION OPS TEST NORMAL.
WHILE PERFORMING LEAK CHECK ON THE # 1 MOTOR NOTED THE FUEL FLOW TRANSMITTER LEAKING. GROUNDED - YES. REMOVED AND REPLACED # 1 ENG FUEL FLOW TRANSMITTER AND PERFORMED GOOD OP CHECK IAW B737-800 AMM 73-31-01, NO LEAK NOTED AT THIS TIME.
F/O F/D MASTER LIGHT INOP. F/D WORKS NORMALLY. GROUNDED - YES. REMOVED AND REPLACED MODE CONTROL PANEL REF B737-800 AMM 22-11-34-400-801, OPS NML PER AMM 22-11-34-740-801. ACCOMPLISHED DFCS MCP LRU REPLACEMENT TEST, GRP BITE 32, ALL TEST PASSED REF AMM 22-11-34/ 501. ACCOMPLISHED LAND VERIFY TEST, GRP BITE 49, ALL TEST PASSED REF AMM 22-11-00/ 201.
WHILE WORKING A T-101 FOR TRANSIT BLEED VALVE HARNESS CHANGE: FOUND LT & RT IGNITER LEAD COOLING TUBE (ORANGE) DISCONNECTED ON THE LT AND TORN ON THE RT. GROUNDED - YES. INSPECTED IGNITER LEADS FOR HEAT DAMAGE/TO INCLUDE IGNITER PLUG CONTACTOR. NO DEFECTS FOUND. PRECAUTIONARY CHANGED IGNITER PLUGS (LT & RT). PLUG INSP FOUND NO HEAT DAMAGE-PLUGS SHOWED NORMAL WEAR. REF FOR IGNITER LEAD B737-800 AMM 74-21-01, LEADS ARE CONNECTED TO PLUGS HOWEVER, CLAMPS-IN LINE AT THE 6 O-CLOCK STRUT. IGNITER PLUGS CHANGED REF AMM 74-21-02, IGNITER PLUG TEST COMPLETED.
EMERGENCY EXIT DOOR LIGHT INOP. GROUNDED - YES. PERFORMED OPERATION CHECK REF B737-800 AMM 33-51-00. OK FOR SVC.
WHILE PERFORMING ASA TC 78273000 FOUND FC 75-30602 THE TBV POSITION SIGNALS DISAGREE. ON LEGS 1 AND 5. ON #2 ENGINE. GROUNDED - YES. ACCOMPLISHED B737-800 FIM 25-23 802 & 803. FOUND TBV RESISTANCE BAD, PINS 2-3 87.1 OHMS PINS 4-5 31.4 OHMS PINS 5-6 31.3 OHMS ON DP0907. PINS 2-3 87.1 OHMS, PIN 4-5 31.5 OHMS 5-6 31.4 OHM ON DP1007. FOUND TBV BAD FROM STOCK WITH SIMILAR READINGS. J-9 & J-10 HARNESS CHECKS GOOD REF FIM 75-23 802 & 803. REMOVED AND REPLACED TRANSIENT BLEED VALVE REF B737-800 AMM 75-23-01-400-801-F00. LEAK CK PASSED. OPS CHK ACTUATORS TEST 12 FAILED W/EC 75-10592. LEAK CHECK GOOD. ACTUATOR TEST SHOWS FAULT 75-10592 AND TBV CH A BLANK IN INPUT MONITORING. REMOVED AND REPLACED J09 AND J10 ENG #2 HARNESS IAW AMM 73-21-06. OPS CHECK GOOD. PERFORMED FIM 71-00-00-700-807-F00 #2 ENG ACTUATORS TEST PASSED W/NO FAULTS.
PILOT (CA) #1 WINDOW HEAT INOPERATIVE. GROUNDED - YES. WHCU SYS TEST C/OUT IAW B737-800 AMM 30-41-11-710-801, TEST PASSED. BITE TEST OF #1 WINDOW WHCU PASSED. NO FAULTS NOTED. OK FOR SVC.
#2 ENG SHORT TIME(MSG NBR: 75-30602)THE TBV POSITION SIGNALS DISAGREE. DEFERRED PER T/C 78273000. GROUNDED - YES. REMOVED AND REPLACED TRANSIENT BLEED VALVE PER B737-800 AMM TASK 75-23-01,LEAK CHK GOOD, OPS CHK GOOD.
SHORT TERM FAULT 75-30602 (TBV POSITION SIGNALS DISAGREE) FOUND WHILE ACCOMPLISHING ASA T/C 78283000 FOR ENG #2. GROUNDED - YES. REMOVED AND REPLACED #2 ENGINE EEC. GROUND VERIFICATION PASS. REF B737-800 AMM 73-21-60-000/400-801-F00 FAULT NO LONGER EXISTS.
AFTER LANDING GOT FMC DISAGREE RAN FMC DISAGREE. GROUNDED - YES. RAN FMC DISAGREE QRH, MESSAGE DISAPPEARED SYS RESET.
SHORT TIME FAULT ENGINE NO. 2 75-10602, CHANNEL "A", "THE TBV POSITION SIGNALS DISAGREE." DEFERRED PER ASA TC 78273000. GROUNDED - YES. ACCOMP EEC BITE CHK ON #2 ENG FOUND FAULT 75-10602 ACTIVE ONLY ON LEG #4. FOUND FAULT 75-20602 ACTIVE ONLY ON LEG #10. REF OPEN ASA DEFECT 60465784 FOR PREVIOUSLY RECORDED FAULT 75-10592. ACCOMP B737-800 FIM 75-23 TASK 802. ALL RESISTANCE CHKS AT TBV CH A/B READ GOOD. ALL RESISTANCE CHKS THRU J9/J10 HARNESS GOOD. INSULATION CHKS ON J9/J10 HARNESS ALSO GOOD. ACCOMP FIM 75-34 TASKS 811 & 816 TO VERIFY NO EXCITATION CIRCUIT FAULTS. ALL CHKS GOOD. PER FIM 75-23-803 TBV POS DISAGREE FAULT. REMOVED & REPLACED #2 ENG TRANSIENT BLEED VALVE. OPS & LEAK CHECKS GOOD. REF B737-800 AMM 75-23-01-400-801-F00.
CONTROL CAB ZONE TEMP LIGHT EXTINGUISH ON RECALL. GROUNDED - YES. CONTROLLER BITE HAD HARD FAULT CALLING OUT CONTROL CABIN TRIM MODULATING VALVE. WOULDN'T RESET. REMOVED AND REPLACED CONTROL CABIN MODULATING VALVE IAW B737-800 AMM 21-61-21-000-801 AND AMM 21-61-21-400-801, ETOPS GROUND FUNCTIONAL CHECK OPS CHECK GOOD IAW AMM. 21-61-00-700-806-002.
DURING CRUISE FLIGHT @ FL360 (SAT-55C) IN BOTH SMOOTH AND LIGHT TURN CONDITIONS THE ENGINE #2 COWL VALVE OPEN LIGHT FLICKERED AND THEN MOSTLY STAYED ILLUMINATED BRIGHT BLUE. NO TAI INDICATION NEAR N1 GUAGE OR OTHER ABNORMALS. FOLLOWED QRH PROCEDURE. GROUNDED - YES. UNABLE TO VERIFY FAULTS-COMPLIED WITH TSR STEP 3-REMOVED & REPLACED #2 ENGINE COWL TAI VALVE IAW B737-800 AMM 30-21-11-COMPLIED WITH INSTALLATION TEST-OPS CHECKS NORMAL.
F/O FMC WONT STOP CYCLING THROUGH PAGES. UNABLE TO MAKE ANY INPUTS. GROUNDED - YES. PERFORMED B737-800 FIM 34-61 TASK 836, RECYCLE BREAKER AND FMC OPS CHECK NORMAL.
NUMBER 2 ENGINE HAS OIL LEAK. GROUNDED - YES. ENGINE #2 HAND CRANKING DRIVE COVER MINOR LEAK. REPLACED DRIVE COVER SEALS PER B737-800 AMM 72-63-01. ENG IDLE RUN COMPLETED. NO LEAKS, AIRCRAFT OK FOR SERVICE.
NUMBER 2 ENGINE B FIRE LOOP INOPERATIVE. GROUNDED - YES. REMOVED AND REPLACED ENGINE FIRELOOP HARNESS MW0316 AND CORE HARNESS MW0326 REF B737-800 AMM 26-11-02 AND PERFORMED OPS CHECK EVERYTHING GOOD GROUND VERIFICATION SUCCESSFUL.
ZONE TEMP ILLUMINATED FOR CONT CAB ON RECALL. LIGHT CLEARED WITH MASTER CAUTION RESET. GROUNDED - YES. REMOVED AND REPLACED CONTROL CAB TRIM AIR VALVE PER B737-800 AMM 21-61-21. OPS AND LEAK CHECK GOOD.
DURING FIRE DETECTION TEST, ENG #2 FIRE HANDLE DOES NOT ILLUMINATE. ENG# 2 HANDLE ILLUMINATES DURING TEST OF "A" LOOP. GROUNDED - YES. VERIFIED FOUND TERMINAL LUG PULLED OFF WIRE AT CORE DETECTOR. REF. B737-800 AMM 26-11-02, RE TERMINATED A NEW LUG ONTO WIRE. OPS NML REF AMM 26-11-00.
DURING FIRE TEST A FAULT OCCURRED ON B LOOP. #2 ENG. GROUNDED - YES. BITE TESTED FIRE DET MODULE WITH #2 FIRE DET SW IN NORMAL 2 ENG LOOP B AND ALL 3 FAULT DISPLAY LTS ON ALL THE TIME. SET ENG 2 FIRE DET SW BACK TO LOOP A ONLY LTS WENT OUT. FOUND WIRE PULLED OUT OF TERMINAL ON RT SIDE CORE ELEMENT. RETERMINATED MISSING TERMINAL REF B737-800 AMM 26-11-02. DISCONNEECTED WIRING TO ALL 4 "B LOOP DETECTORS AND PERFORMED RESISTANCE CHKS OF ALL 4 "B DETECTORS) REF B737-800 FIM 26-10 TASK 810. ALL 4 DET WELL WITHIN TOLERANCE.
DURING FIRE TEST A FAULT OCCURRED ON THE B LOOP. GROUNDED - YES. PERFORMED ENGINE APU FIRE DETECTION CONTROL MODULE BITE TEST ENGINE 2 LOOP B FAN UPPER DETECTOR FAULT. PERFORMED TEST ENGINE 2 LOOP FIRE DETECTOR, CHECK WAS LUGS, CLEANED, CONTACTS AND REINSTALLED FIRE DETECTOR ELEMENT. OPS CHECK GOOD NO MORE FAULTS. NO MORE MAINTENANCE MESSAGE IAW B737-800 FIM 26-10 TASK 805 AND FIM 26-10 TASK 801.
REF. LP 60336229. CAPT REPORTS STILL HAVING ISSUES W/ MCP BLANKING, GOING INTO LOCK OUT MODE. GROUNDED - YES. PERFORMED DFCS BITE IAW B737-800 FIM 22-11 TASK 801. NO RELEVANT FAULTS IN FAULT HISTORY FOR MCP. REMOVED AND REPLACED MCP AS PRECAUTIONARY, DUE TO HISTORY, IAW B737-800 AMM 22-11-34-000/400-801. PERFORMED INSTALL TEST IAW AMM 22-11-34-740-801. PASSES TEST. PERFORMED DFCS LAND VERIFY IAW AMM 22-11-00-700-801. PASSES TEST. PERFORMED HGS SYSTEM TEST IAW SMM 34-36-00 SEC 500. PASSES TEST. NO FAULT IN RECORDED OR EXISTING. ALL TESTS PASS. A/C OK FOR SERVICE. CAT III DUAL AP AND HGS AUTHORIZED. APPROACH SURVEY COMPLETE.
CAPT REPORTS F/OS MCP CRS WINDOW DISPLAYS AL 888 ON PWR XFER GND TO APU. GROUNDED - YES. REBOOTED A/C. PREFORMED MCP TEST PER B737-800 AMM 22-11-34. GND TEST OK.
1 LCD SEGMENT ALWAYS ILLUMINATED IN MCP VERTICAL SPEED WINDOW. GROUNDED - YES. REPLACED THE MCP, ALL TEST PASSED. REF B737-800 AMM TASK 22-11-34-400-801.
#2 ENGINE FIRE HANDLE LIGHTS DO NOT ILLUMINATE DURING TEST. GROUNDED - YES. C/W VISUAL AND PHYSICAL INSPECTION. NO DEFECTS NOTED. REMOVED AND REPLACED FIRE LOOP B HARNESS MW0326 REF B737-800 AMM 26-11-02-000-802, 26-11-02-400-802, GROUND VERIFICATION GOOD.
CONT CAB ZONE TEMP LITE ILLUMINATED ON MATER CAUTION RECALL DURING THE DESCENT CHECK. THE LITE EXTINGUISHED WHEN MASTER CAUTION WAS RESET. GROUNDED - YES. VERIFIED FAULT. REPLACED FWD ZONE TRIM AIR MODULATING VALVE PER B737-800 AMM 21-61-21/401. OPS CHECK NORMAL. NO AIR LEAK NOTED. ETOPS SIGNIFICANT SYSTEM GROUND CHECK SUCCESSFUL.
F/O SIDE WINDOW OVERHEAT REMAINED ILLUMINATED AFTER QRH. GROUNDED - YES. NO 2 SLIDER WINDOW REPLACED REF B737-800 AMM TASKS 56-12-11-000-801 AND 56-12-11-400-801. PUT TAP INTO THE PROPER POSITION (#1) PER B737-800 WDM 30-41-11 PG 6 SHEET 2. OPS TEST GOOD AND LEAK CHECK GOOD.
A COUPLE HOURS INTO THE FLIGHT THE LEFT MAIN QUANTITIY INDICATOR SHOWED 8.29 WHEN THE CENTER STILL HAD 4.32 AND RIGHT QUANTITY SHOWED FULL 8.58. WHEN THE CENTER TANK WAS EMPTY THE LEFT SHOWED 8.12 AND RIGHT 8.58. FUEL TOTAL WAS EXACTLY +.2 COMPARED TO FLIGHT PLAN UP TO THIS POINT. APPROACHING THE NEXT WAYPOINT LEFT MAIN WENT TO 5.65 & 6.87 ON THE RIGHT - MORE HAD 1200LBS. AS WE RAN THE FUEL LEAK CHECKLIST IT RETURNED TO 1000LBS IMBALANCE. ON DECENT LEFT QUANTITY GRADUALLY ROSE TO PERFECT BALANCE BY ITSELF. GROUNDED - YES. PER B737-800 FIM 28-41 TASK 814 PERFORMED FQIS BITE PROCEDURE. GROUND TEST PASSED. ALSO PERFORMED CROSSFEED VALVE FUNCTIONAL TEST REF B737-800 AMM 28-22-00 AND FUEL BOOST PUMP OPS TEST REF AMM 28-22-41. NO DEFECTS NOTED. NO HISTORY 30 DAYS. GROUND VERIFICATION SUCCESSFUL. SEAMC ANDY NOTIFIED.
#2 ENGINE FIRE HANDLE WILL NOT ILLUMINATE DURING FIRE TEST. BITE SHOWS UPPER FAN LOOP B DETECTOR FAULT. GROUNDED - YES. INITIAL EVALUATION, PERFORMED FIRE DET OPS TEST IAW B737-800 AMM 26-10-00-710-801. FIRE HANDLE FOR #2 ILLUMINATED NORMALLY. SWITCHED BETWEEN A/B LOOPS ONLY, CHECKS GOOD STILL ILLUMINATED. PERFORMED ENGINE APU FIRE DETECTION CONTROL MODULE BITE IAW B737-800 FIM 26-10 TASK 801, PASSES BITE ON NORMAL AND FOR LOOP A/B ONLY. REMOVED ENG/APU FIRE DET CONT MOD IAW B737-800 AMM 26-10-01-000-801/FIM 26-10 TASK 805. RECHECKED PINS 10-12 ON D998, =100 OHMS, STILL OUT OF LIMITS. REF B737-800 WDM 26-11-11/21. FOLLOWING FIM 26-10 TASK 805 STEP F(4)D(2) - DISCONNECTED D1601 AND INSTALLED JUMPER AT PINS 1-2, DISCONNECTED DP1620 AND READ PINS 3-4 = 1.5 OHMS. REMOVED JUMPER, RECONNECTED D1601 AND READ 2.5 OHMS. RECONNECTED DP1620 AND READ AGAIN AT D998 ON M279 PINS 10-12 = 2.8 OHMS. ALL RESISTANCE NOW WITHIN NORMAL LIMITS. CONNECTORS WERE VERY DIRTY AND DIFFICULT TO REMOVE. CLEANED AS APPROPRIATE WITH IPA AND RECONNECTED. NO DEFECTS REMAIN. GVI OF MW316 AND MW326 HARNESS, NO DEFECTS NOTED. PERFORMED WIGGLE TEST FOR BOTH HARNESSES IAW FIM 26-10 TASK 805, ALL READINGS NORMAL. REINSTALLED ENG/APU FIRE DET CONT MOD M279 IAW AMM 26-10-01-400-801. PERFORMED OPS TEST AND CONT MOD BITE AGAIN, NO FAULTS FOUND.
HF 2 SHOWS FAIL LIGHTS IF HF SENSOR SWITCH IS INCREASED (DIALED CLOCKWISE), FAIL LT EXTINGUISHES. INTERMITTENT FAILURE. GROUNDED - YES. PERFORMED THE TEST OF #2 HF REF B737-800 FIM 23-11 TASK 801 OPS NORMAL - NO FAULTS ON PANEL ETOPS SIGNIFICANT SYSTEM GROUND VERIFICATION SUCCESSFUL SEAMC RAY NOTIFIED.
#2 AMBER TAI ILLUMINATED W/ ENG HEAT ON. GROUNDED - YES. REMOVED AND REPLACED TAI VALVE PER B737-800 AMM 30-21-11 OP CHECKS NORMAL AT THIS TIME.
L/H HORIZONTAL LOWER SKIN IS CRACKED AT STA 138.0 9 INCHES FWD OF T/E. GROUNDED - YES. CUT OUT DAMAGE AND REPAIRED LOWER SKIN IAW B737-800 SRM 55-10-01-2R-11 REPAIR 11. THIS IS A CATEGORY B REPAIR WITH AN INSPECTION THERESHOLD OF 56,0000 TOTAL FLIGHT CYCLES AND A REPEAT INTERVAL OF 9,0000 FLIGHT CYCLES.
L/H HORIZONTAL LOWER SKIN IS CRACKED AT STA 147.0 31 INCHES FWD OF T/E. GROUNDED - YES. CUT OUT DAMAGE AND REPAIRED LOWER SKIN IAW B737-800 SRM 55-10-01-2R-11 REPAIR 11. THIS IS A CATEGORY B REPAIR WITH AN INSPECTION THRESHOLD OF 56,000 TOTAL FLIGHT CYCLES AND A REPEAT INTERVAL OF 9000 FLIGHT CYCLES.
L/H HORIZONTAL LOWER SKIN IS CRACKED AT STA 175.08 INCHES FWD OF T/E. GROUNDED - YES. CUT OUT DAMAGE AND REPAIRED LOWER SKIN IAW B737-800 SRM 55-10-01-2R-11 REPAIR 11. THIS IS A CATEGORY B REPAIR WITH AN INSPECTION THRESHOLD OF 56,000 TOTAL FLIGHT CYCLES, AND A REPEAT INTERVAL OF 9,000 FLIGHT CYCLES.
DURING LEFT ENGINE START, NO IGNITION, FUEL FLOW DROPPED, ABORTED START. GROUNDED - YES. P6-3, B4 SPAR VALVE ENG 1, P18-2, A1 ENG 1 RIGHT, A3 ENG 1 LEFT (IGNITION). C/B'S RESET, NO HISTORY. REF B737-800 AMM 20-60-01. GATE #1 ENG RUN OPS NML.
ATTEMPTED AUTOLAND & HGS AIII, DEVELOPED A HIGH SINK RATE AND DID NOT FLARE. THEN APP/WARN IN THE HUD. DISCONNECTED A/P A/T AND LANDED MANUALLY. GROUNDED - YES. CHECKED FOUND HGS APCH WARN FOR LEG 6 AIRSPEED EXCEEDANCE. HGS SYSTEM TEST PASSED REF HGS 4000 SSM 34-36-00. ACCOMPLISHED LAND VERIFY TEST. TEST PASSED GROUND VERIFICATION TEST PASS. REF B737-800 AMM 22-11-00-700-801.
TEMP PROBE ANTI - ICE MASTER CAUTION ILLUMINATED IN CRUISE. INDICATIONS NORMAL. GROUNDED - YES. REMOVED AND REPLACED TAT PROBE IAW B737-800 AMM 34-21-06. OPS CHECK OKAY.
MID CABIN EXIT SIGN LENS COVER HAS FALLEN OFF. GROUNDED - YES. (RESOLVED ON W/O: 1879171 TASKCARD: N/R-00001 ) REMOVED AND REPLACED MID CABIN EXIT SIGN LIGHT ASSY PER B737-800 AMM 33-51-01. OPS CHECK GOOD. THIS CLEARS PLT, SEAMC JAKE NOTIFIED.
#2 ENG HAS EXCESSIVE AMOUNT OF OIL DRIPPING FROM BOTTOM OF THE FAN COWL. GROUNDED - YES. PERFORMED IDLE RUN LEAK CHECK ON #2 ENG FOUND OIL LEAK FROM QAD ADAPTOR STARTER REF B737-800 MM 71-00-00. REPLACED BOTH PACKINGS ON STARTER REF AMM 80-11-01. IDLE LEAK CHK GOOD REF AMM 71-00-00.
EQUIP COOLING FAN ALTN LT. ON. GROUNDED - YES. DIVERSION TIME 31 MINUTES - REF LP 60175101 EQUIP COOLING EXH. NORM INOP AS WELL. FOUND EQUIP COOLING EXH LOW FLOW SENSOR COMPLETELY CLOGGED CAUSING BOTH NORM & ALT TO FAIL. VERIFIED BOTH FANS ARE RUNNING - AFTER REPLACING LOW FLOW SENSOR REF B737-800 AMM 21-27-03-400-802 OPS TEST OK.
NO ROTATION WHEN TRYING TO START #1 ENG. GROUNDED - YES. ATTEMPTED MANUAL START VALVE ACTUATION FROM GROUND START VALVE MOVES FREELY AS REQUIRED,CKD START VALVE CIRCUIT BREAKERS ALL SET NO POPPED BREAKERS SUSPECT BAD STARTER REF B737-800 FIM 80-07 TASK 802. REMOVED STARTER REF B737-800 AMM TASK 80-11-01-000-801-F00. REMOVED QAD ADAPTER,CLEANED CHIPS REF AMM TASK 80-11-02-000-801-F00, REINSTALLED QAD ADAPTER REF AMM TASK 80-11-02-400-801-F00, INSTALLED NEW STARTER REF AMM TASK 80-11-01-400-801-F00. RAN ENGINE, CHECKED FOR LEAKS, GROUND VERIFICATION GOOD.
CAPTAINS MCDU SCREEN BLANKED, WARNING LIGHT CAME ON, AND BIT MESSAGE DISPLAYED ON SCREEN. SEQUENCED AT LEAST 10 CYCLES. NO ASSOCIATED MAP OR VTK WARNING ON CDU'S. GROUNDED - YES. REMOVED, REPLACED, AND TESTED CAPTAIN'S MCDU PER B737-800 MM 34-61-01-000-802 / AMM 34-61-01-400-802 - OPS NORMAL.
FMC L RECYCLED RESET TEST 8 TO 10 TIMES WORKED PROPERLY AFTER FINAL RESET. GROUNDED - YES. RESET FMC PER FIM TASK 34-61 TSK 836 OPS CHECK OK.
L NAV WOULD NOT ENGAGE . SELECTED A DIFFERENT DEPARTURE L NAV ENGAGED. GROUNDED - YES. PERFORMED FIM 22-11 TASK 830, VERIFIED CORRECT FLIGHT PLAN WAS ENTERED. L NAV NOW ENGAGES, NO FURTHER MAINT ACTION REQUIRED VERIFICATION SUCCESSFUL.
ACCOMPLISHED TROUBLESHOOTING RECOMMENDATIONS PER TSR705030 FOR HISTORY OF #1 ENGINE B LOOP NOT TESTING PROPERLY AND CAUSING DELAYS. RESISTANCE CHECK OF ENG 1 LOOP B FROM CONNECTOR D1002. CHECKS WITHIN LIMITS. REF B737-800 FIM 26-10 TASK 805. RIGHT CORE DETECTOR TERMINAL FOUND LOOSE ON MW0326 HARNESS. GROUNDED - YES. REINSTALLED M279 AND SECURED. REPLACED MW0326 HARNESS. OPERATIONAL TEST PASSES REF B737-800 AMM 26-11-02/401.
#1 ENGINE FIRE LIGHT FAILS TEST. TEST OK WITH "A" SELECTED . GROUNDED - YES. PERFORMED B737-800 FIM 26-10 TASK 801 WITH NO FAULTS AND OPS NORMAL. PERFORMED GVI OF FAN & CORE # 1 ENGINE LOOP WITH NO DEFECTS NOTED. PLACARDS REMOVED.
#2 ENGINE OIL CAP SEAL BROKEN. GROUNDED - YES. REPLACED #2 ENGINE OIL CAP PACKING. OK FOR SERVICE.
NR 1 ENGINE FIRE LOOP B WILL NOT TEST. GROUNDED - YES. NR 1 ENGINE FIRE LOOP B INOP. ACCOMPLISHED FIM 26-10 TASK 801. OPS CHECK NORMAL. UNABLE TO DUPLICATE. MOVED LOOP SELECTOR SWITCH BACK TO NORMAL POSITION. REMOVED MEL.
ON RECALL CONT CAB ZONE TEMP LIGHT ILLUMINATES. EXTINGUISHES WITH RESET. NO TEMPERATURE FLUCTUATIONS. GROUNDED - YES. PERFORMED BITE CHECK, FOUND FLT DECK TRIM VALVE BAD. REMOVED AND REPLACED FLT DECK TRIM VALVE, REF AMM 21-61-21. OP CHECK GOOD.
NR 1 ENG HPT ACC LEAKING 4 DROPS PER MIN. GROUNDED - YES. REMOVED AND REPLACED THE NR 1 ENG HPT ACC VALVE IAW AMM 75-21-01-000-801-F00, & AMM 75-21-01-400-801-F00. LEAK CHECKED GOOD AND ACTUATOR TEST C/W -OPS NORMAL.
NO 1 ENG LUBRICATION UNIT CLOGGING INDICATOR GLASS BOWL BROKEN. GROUNDED - YES. REMOVED AND REPLACED NO 1 ENG LUBRICATION UNIT CLOGGING INDICATOR GLASS BOWL REF B737-800 CMM 79-21-16 PG 302 & 305 STEP 4 I 1 & 2 AND PGS 703,706 & 709 STEPS 4.C. 26&27.
#1 ENG EXHAUST CONE FLANGE MISSING ON BOLT @ 3 O'CLOCK POSITION. GROUNDED - YES. FOUND AND REINSTALLED BOLT AT 3 O'CLOCK POSITION ON THE #1 ENG EXHAUST FLANGE REF B737-800 AMM 72-56-00-400-801-F00.
FUEL LEAKING CONTINUOUSLY FROM #1 ENGINE HMU DRAIN LINE. GROUNDED - YES. REMOVED AND REPLACED #1 ENGINE HMU REF T/C N8473001
NR 1 ENGINE HAS A DRAIN LEAKING FUEL. FOUND HPTACC VALVE DRAIN AT 4 DROPS PER MINUTE. ALLOWABLE LIMITS LESS THAN 90 DPM. GROUNDED - YES. REMOVED AND REPLACED THE NR 1 ENG HPTACC VALVE IAW AMM 75-21-01-000-801-F00, & AMM 75-21-01-400-801-F00. LEAK CHECKED C/W NO LEAKS NOTED AND ACTUATOR TEST C/W -OPS NORMAL.
FUEL LEAK, #1 ENGINE, AT THE PUMP/HMU MATING SURFACE. GROUNDED - YES. REMOVED AND REPLACED FUEL PUMP REF B737-800 AMM TASK 73-11-11-400-801-F00 3.A THRU 6.
REF T/C 78472000 #1 ENGINE INLET AND FAN BLADES- DETAILED INSPT. FOUND R/H MIDDLE FASTENER AND #6 STRUT PANEL DAMAGED DUE TO FASTENER BEING LOOSE. (M) ALF. GROUNDED - YES. REMOVED AND REPLACED #6 STRUT PANEL PN:340-084-003-0 REF B737-800 AMM 72-23-07.
#1 ENGINE INLET AND FAN BLADES - DETAILED INSPT. FOUND FUEL LINE FROM IDG OIL COOLER HAS DAMAGED OUTER RUBBER COVER TORN. GROUNDED - YES. REMOVED AND REPLACED IDG OIL COOLER FUEL LINE P/N 340-016-251-0. REF B737-800 AMM 73-11-06-000-801-F00. AMM 73-11-01-000-801-F00 STEP 2. AMM 73-11-06-400-801-F00 STEP 3. AND AMM 73-11-01-400-801-F00 STEP 3. REQUIRES TEST 3A IDLE POWER LEAK CHECK. AMM 71-00-00-700-801-F00. ASA 83 INSP. LEAK CK 3A WILL BE PERFORMED AT NEXT ENGINE INSTALLATION, THIS ENGINE REMOVED FOR REPAIR.
EMERGENCY LIGHT EXIT LOCATOR SIGN AT RIGHT AFT OVERWING EXIT HAS MULTIPLE LAMPS INOP. GROUNDED - YES. RELAMPED AND TESTED PER B737-800 MM 33-51-01-960-801 - OPS NORMAL.
#1 ENG "A" LOOP INOP. GROUNDED - YES. CONFIRMED FAULT, #1 ENGINE A-LOOP WILL NOT TEST. FOUND R/T CORE FIRE DETECTOR HARNESS (MW0315) TERMINAL LUG BROKEN AT THE DETECTOR, TOO SHORT TO REPAIR WIRING. REMOVED & REPLACED MW0315 CORE FIRE DETECTION HARNESS (A-LOOP) REF B737-800 AMM 26-11-02, OPS CK NML REF AMM 26-11-00-710-801. AIRCRAFT RELEASED FROM MEL 26-2B, C/N 03023587. REPOSITIONED #1 ENGINE OVHT DET SWITCH BACK TO NORMAL.
NO. 1 ENGINE WOULD NOT LIGHT OFF RIGHT OR LEFT IGN. GROUNDED - YES. FOUND 3 C/B OUT. ACCOMPLISHED C/B. RESET PROCEDURE. NO DEFECTS NOTED. REF B737-800 AMM 20-60-01. ACCOMPLISHED ELECTRICAL CONTROL AND INDICATION TEST FOR #1 ENGINE FUEL SPAR VALVE. TEST PASSED. REF AMM 28-22-00. PERFORMED #1 ENGINE START PROCEDURE. #1 ENGINE START SUCCESSFUL ON RIGHT AND LEFT IGN. REF AMM 71-00-00. GROUND VERIFICATION TEST GOOD.
NR 1 ENG A LOOP INOP. GROUNDED - YES. ACCOMPLISHED FIRE DETECTION CONTROL MODULE BITE TEST PER FIM 26-10 TASK 801. PERFORMED VISUAL INSPECTION OF FIRE LOOPS AND HARNESSES FOUND RT CORE A LOOP WIRE BROKEN AT TERMINAL LUG. REPLACED TERMINAL PER AMM 26-11-002-960-802. TERMINAL REPLACEMENT IS APPLICABLE PER WIRE HARNESS P/N 325-027-506-0 HARNESS IS CORRECT EFFECTIVELY FOR AIRCRAFT.
ETOPS VERIFICATION FLIGHT FOR HF1 UNSATISFACTORY- HF1 TESTED WITH SFO RADIO ARINC AND THEY REPORTED THAT OUR TRANSMISSIONS WERE WEAK AND UNREADABLE. TESTED ON MULTIPLE FREQUENCIES. SENSITIVITY WAS SET TO 100- HF1 TUNING TOOK SLIGHTLY LONGER THAN NORMAL AS WELL. GROUNDED - YES. REMOVED AND REPLACED HF1 COUPLER REF B737-800 AMM 23-11-61 OP CK GOOD.
UNABLE TO TRANSMIT ON HF1. GROUNDED - YES. CYCLED POWER TO HF1 OPS RESTORED AND CHECKS OKAY REF B737-800 FIM 23-11 TASK 806 + 801
HF #1 WILL TUNE & RECEIVE BUT WILL NOT TRANSMIT VOICE. GROUNDED - YES. R&R #1 HF TRANSCEIVER REF AMM 23-11-21 GROUND VERIFICATION NML
MAP FLAG ON FIRST OFFICERS INBOARD DISPLAY UNIT. GROUNDED - YES. PERFORMED SYSTEM RESET PER B737-800 FIM 34-61 TASK 836 & CYCLED POWER TO SYSTEM PER B737-800 AMM 20-60-05 OPS CHECK NORMAL.
RADAR ONLY SWEEPS FROM LEFT TO RIGHT ON BOTH SIDES. CAPT RADAR BLANKS FOR 1 SECOND EACH SWEEP. GROUNDED - YES. COULD NOT DUPLICATE. OPS CHECK WX RADAR GOOD. REF B737-800 AMM 34-43-00.
UNABLE TO TRANSMIT ON HF 1 WHEN TUNING SIDETONE LAST FOR ABOUT 5 SECONDS RECEIVING WORKS AND SELCAL FUNCTIONS NORMALLY. GROUNDED - YES. PERFORMED OPS TEST OF HF COMM SYS IAW B737-800 AMM 23-11-00-710-801 OPS CHECK AND GROUND VERIFICATION SUCCESSFUL.
FUELER REPORTS #1 FUEL GAUGE AT FUELING PANEL IS BLINKING. GROUNDED - YES. REMOVE AND REPLACED #1 FUEL QTY INDICATOR PER B737-800 AMM 28-41-61. OPS CHECK GOOD. CHP 5 ALTERNATE DEACTIVATION TABLE 3 ITEM 1 USED. REVERSE ALTERNATE DEACTIVATION.
REFUELER REPORT THAT THEY ARE UNABLE TO ADD FUEL TO TANK #1. GROUNDED - YES. PERFORMED FQIS BITE CHECK, NO CURRENT FAULTS NOTED, PERFORMED FUEL QUANTITY COMPARISON CHECK IAW AMM 28-41-00, NO DEFECTS NOTED, #1 TANK FOUND TO BE FULLY FUELED.
EMERGENCY LIGHT SIGNS AR R1 DOOR AREA ARE INOP. GROUNDED - YES. REMOVED & REPLACED EMER, LIGHT PWR SUPPLY M1674, OPS CHECKS GOOD ALL R1 LIGHTS IAW 737NG AMM 33-51-06-960-805.
EXTERIOR EMERGENCY LIGHT AT LH FWD OVERWING DOOR AREA IS INOP. GROUNDED - YES. REMOVED AND REPLACED BATTERY PACK IAW B737-NG AMM 33-51-06-960-805. OPS CHECK GOOD.
EMERGENCY LIGHT SIGNS AR R1 DOOR AREA ARE INOP. GROUNDED - YES. REMOVED & REPLACED EMER, LIGHT PWR SUPPLY M1674, OPS CHECKS GOOD ALL R1 LIGHTS IAW 737NG AMM 33-51-06-960-805.
EMERGENCY LIGHT SIGN AT L2 DOOR AREA INOP. GROUNDED - YES. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY M1673 S/N 66253. PERFORMED SUCCESSFUL OP CHECK ON EMERGENCY POWER SUPPLY M1673 IAW B737-800 AMM 33-51-06-960-805.
EMERGENCY LIGHT SIGN AT R1 DOOR AREA INOP GROUNDED - YES. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY M1674 S/N 36074, OPS CHECKED GOOD ALL R1 LIGHTS IAW B737-800 AMM 33-51-06-960-805.
EMERGENCY EXIT O/W LIGHTS OUT GROUNDED - YES. REMOVED AND REPLACED BATTERY PACK AND CHARGER.
EMERGENCY LIGHT SIGNS AT L2 DOOR AREA ARE INOP. GROUNDED - YES. REMOVED AND REPLACED PERFORMED SUCCESSFUL SYSTEM OP CHECK ON EMERGENCY POWER SUPPLY M1673 IAW B737NG AMM 33-31-06-960-805.
MAIN CABIN FLOOR SUPPORT INTERCOSTAL AT STA 312-328 LBL46 IS CRACKED. GROUNDED - YES. REMOVED AND REPLACED INTERCOSTAL IAW B737-800 SRM 51-40-02. REMOVED DOT A621 REF BAC DWG 141A5400 REV "-".
MAIN CABIN, PANEL BREAK SUPPORT CHANNEL CRACKED AT STA 540 BL0-LBL24. GROUNDED - YES. REMOVED AND REPLACED PANEL BREAK AT STA 540 BL 0 - LB L 24 IAW B737-800 SRM 51-40-02 AND BOEING DWG 143A0060 REV-.
CRACKS ON CABIN FLOOR SUPPORT ANGLE AT STA. 380-400, LBO 14 GROUNDED - YES. REMOVED AND REPLACED UPPER CHORD IAW BAC DWG 143A5400 AND B737-800 SRM 51-40-02
L1 DOOR AFT GIRT BAR MOUNT FITTING HAS CORROSION. GROUNDED - YES. REMOVED AND REPLACED TIEDOWN FITTING P/N 141A5220-4 PO. 951405.2 IAW B737-800 SRM 51-40-02 AND AMM 20-50-11 TOOL # T8482Q DUE 11/14/2019
AFT CABIN FLOOR SUPPORT CORRODED BS 947, BL 5L - BL 10R. GROUNDED - YES. REMOVED DAMAGE AND CHECKED LIMITS ORIGINAL THICKNESS .180 REMAINING 0.151,REMOVED 0.029. OUT OF LIMITS IAW B737-800 SRM 53-70-51. CUT OUT DAMAGE ANDINSTALLED "T" CHORD REPAIR STA 947 LBL 16 TO RBL 58.6 IAW B737-800 SRM 53-70-51-2R-5 REPAIR 5 ATTERNATIVE 2.
L1 DOOR MOP SILL HAS MULTIPLE AREAS CHAFED FROM FLOOR PANEL INSERTS. GROUNDED - YES. REMOVED CORROSION, ORIGINAL THICKNESS OF .090, REMAINING THICKNESS OF .062, MAT LOSS OF .028 USING TOOL T8225G DETERMINED TO BE OUT OF LIMITS IAW B737-800 SRM 53-10-15, RECEIVED NEW PART (INNER CHORD) ON L-1 DOOR MOP SILL P/N 654A0004.1073 LOCATED, DRILLED , COUNTERSUNK AND INSTALLED IAW BAC DWG 141A8110 REV E
L1 DOOR FWD GIRT BAR MOUNT FITTING HAS CORROSION GROUNDED - YES. REMOVED AND REPLACED TIEDOWN FITTING P/N 141A5220-2 PO. 951405.1 IAW B737-800 SRM 51-40-02 AND AMM 20-50-11 TOOL # T8482Q DUE 11/14/2019
MAIN CABIN AFT GALLEY SERVICE DOOR CUTOUT FWD FRAME EXTERNAL SKIN EDGE GOUGED JUST ABOVE UPPER TORQUE TUBE MOUNT. GROUNDED - YES. REMOVED AND REPLACED SKIN CORNER 147A3110-6 REF B737-800 SRM 51-40-02 AND BAC DWG 147A0020 REV -.
FUSELAGE FRAME, STATION 325.6 STRINGER 25L LBL 40, HAS FAIL SAFE ANGLTHAT IS DENTED. GROUNDED - YES. REMOVED AND REPLACED FUSELAGE FRAME, STA 325.6 STR 25L LBL 40 FAIL SAFE CHORD PER B737 DWG 141A1360 REV.- AND B737-800 SRM 51-40-02.
AFT PIT LOWER MAIN SILL THRESHOLD WEB BETWEEN BS794- BS847 IS CORRODED GROUNDED - YES. REMOVED AND REPLACED AFT PIT LOWER MAIN SILL THRESHOLD WEB BETWEEN BS794- BS847 PER BAC DWG 146A8340 REV -
#1 FIRE SWITCH DOES NOT TEST. GROUNDED - YES. VERIFIED DISCREPANCY. RESISTANCE AT D1002 PIN 24 TO 25 READING 3.7K OHMS SHOULD READ <3 OHMS. AT PINS 25 TO 2 READING 2.35K OHMS. SHOULD READ 862 OHMS. INSPECTED AND FOUND BROKEN TERMINAL AT M1758. AFTER NEW TERMINAL INSTALL READINGS WERE PINS 24 TO 25 1.9 OHMS. PINS 25 TO 2 READINGS WAS 859 OHMS. PERFORMED FIRE DETECTION OPS TEST REF AMM 26-11-00/501. SYS CHKS NML.
#1 ENG "A" LOOP INTERMITTENTLY INOP. PRIOR TO TAXI #1 FIRE HANDLE DID NOT ILLUMINATE DURING TEST. AFTER TAXI TEST WAS NORMAL. GROUNDED - YES. WHILE PERFORMING GVI OF CORE FIRE DETECTION HARNESS MW0325 FOUND BROKEN WIRE AT HEAT DETECTOR M1759 REF WDM 26-11-11 PG 1. RETERMINATED 1 EA BROKEN LUG REF AMM 26-11-02-960-801. ACCOMPLISHED ENGINE FIRE DETECTION OPERATIONAL TEST REF AMM 26-11-00-710-801. OPS CK GOOD.
OVHT/FIRE WARNING TEST FAILED "FAULT" ILLUMINATED, #1 FIRE WARNING SWITCH DOES NOT ILLUMINATE. GROUNDED - YES. PERFORMED FUNCTIONAL TEST PER AMM 26-11-00. NO FAULTS NOTED AT THIS TIME. OPS CHECK OK.
FIRE DETECTION TEST FAULT ENGINE #1. GROUNDED - YES. THE SYSTEM STARTED TESTING PROPERLY, PROBLEM IS INTERMITTENT. THE ENG/APU FIRE DETECTOR MODULE PREVIOUSLY HAD A LOWER FAN DETECTOR FAULT. REMOVED AND REPLACED LOWER FAN FIRE DETECTOR HARNESS IAW B737-800 AMM 26-11-02-000-801 AND 26-11-02-400-801.
L1 DOOR HARD TO ARM AND DISARM. GROUNDED - YES. REPACKED L1 DOOR SLIDE PER AMM 25-56-01. ARMS NORMAL.
RELEASED PER MEL 21-32B RT PACK PRIMARY TEMP CONTROL INOP. NOTE: CREW SAID THEY HAD A RIGHT PACK LIGHT - EXTINGUISHED WITH MASTER CAUTION RESET. GROUNDED - YES. PERFORMED CABIN TEMP CONTROLLER BITE PROCEDURE PER FIM 21-61 TASK 801 FOR R/H PACK. NO FAULTS FOUND. PERFORMED GOOD OPS TEST OF CABIN TEMP CONTROL ON R/H SIDE PER AMM 21-61-00-700-807.
REPORTS OF LT PACK TRIP OFF IN FLIGHT. GROUNDED - YES. C/W TSR NO DEFECTS FOUND. REPLACED LT RAM DOOR ACTUATOR PER AMM 21-51-21 AS REQUESTED BY TECH SERV.
LEFT PACK LIGHT ILLUMINATED IN CRUISE AT 350. RAN QRH PROCEDURE . LIGHT EXTINGUISHED AFTER SELECTING WARMER TEMP. LIGHT ILLUMINATED AGAIN ON RECALL AT TOP OF DESCENT AND EXTINGUISHED WITH MASTER CAUTION RESET. GROUNDED - YES. PERFORMED PACK/ZONE TEMP CONTROLLER BITE CHECK. NO FAULTS FOUND. PERFORMED FIM 21-53 TASK 813 NO DEFECTS NOTED, CHECKED WIRING ON LEFT PACK COMPRESSOR DISCHARGE OVERHEAT SWITCH (S2) NO DEFECTS NOTED. CHECKED LEFT PACK TURBINE INLET OVERHEAT SWITCH (S938) NO DEFECTS NOTED. CHECKED LEFT PACK DISCHARGE DUCT OVERHEAT SWITCH (S934) NO DEFECTS NOTED.
PACK LIGHT ON WITH RECALL. RESETS WITH MASTER CAUTION. GROUNDED - YES. PERFORMED PACK ZONE TEMP CONTROL BITE PER AMM 21-61-00 FAULTED LT PACK TCV. REMOVED TCV PER AMM 25-51-10-000-801. INSTALLED TCV PER AMM 21-51-10-400-801 OPS TEST IS GOOD BITE TEST IS GOOD AND LEAK CHECK IS GOOD.
LEFT PACK LIGHT IN FLIGHT WENT OUT AFTER 15 MINUTES AND CHECKLIST COMPLETED. WOULD NOT GO OUT WITH JUST MASTER CAUTION RESET. GROUNDED - YES. ACCOMPLISHED PACK/ZONE TEMP. CONTROLLER BITE AMM 21-61-00 GRD VERIFICATION SUCCESSFUL.
FOUND 8 CONSECUTIVE HPT, NGV DAMAGED MISSING MATERIAL AT TRAILING EDGE, 1 VANE WITH BURN THROUGH HOLE. ALL DAMAGE LOCATED WITHIN 90' ARC , DAMAGE LOCATED BETWEEN 3 AND 6 OCLOCK POSITION ALF BURN THROUGH AT HPT SHROUD. GROUNDED - YES. ENGINE REPLACED.
NR 2 ENG NR 10 FAN BLADE ROOT AT CONCAVE SIDE HAS CUNI COATING DAMAGE OUT OF LIMITS. GROUNDED - YES. REMOVED AND REPLACED BOTH NR 10 AND NR 22 FAN BLADES IN CONJUNCTION WITH FAN BLADE LUBRICATION. REF T/C FOR WORK ACCOMPLISHED AND VIB SURVEY.
DURING CLIMB OUT, LEFT PACK LIGHT ILLUMINATED, EXTINGUISHED ON MASTER CAUTION RECALL RESET. ACFT GROUNDED. REMOVED AND REPLACED THE LT TCV REF AMM 21-51-10/401. BITE CHECK AND LEAK SATISFACTORY.
L2 WINDOW HAS DELAMINATION UPPER RIGHT CORNER AND WINDOW VERY HOT IN WINDOW CENTER. GROUNDED - YES. REPLACED L2 WINDOW HEAT CONTROL UNIT IN REF TO B737-800 AMM 30-41-11. REMOVED AND REPLACED L2 SLIDING WINDOW- OPS CKS OPEN & CLOSE & ELECTRICALLY OK- REF AMM 56-12-11-400-801 NEW RESISTANCE CODE IS H-15.
#1 ENGINE FUEL SERVO FOUND LEAKING DURING IDLE ENG RUN. GROUNDED - YES. REPLACED #1 ENG SERVO FUEL HEATER REF B737-800 AMM 73-11-07-000/400-801-F00. INSTALLATION TEST GOOD. LEAK CHECK GOOD.
EMERGENCY EXIT SIGN AFT OF L2 DOOR WILL NOT ILLUMINATE. GROUNDED - YES. REMOVED & REPLACED EMERGENCY EXIT SIGN ASSY REF AMM 33-51-01-960-802. OPS CK GOOD PER THE SAME.
CONT CAB TEMPERATURE CONTROLLER DOES NOT CHANGE TEMPERATURE IN FLIGHT DECK FLIGHT DECK REMAINED VERY COLD FOR DURATION OF FLIGHT. GROUNDED - YES. PERFORMED BITE CHECK ON PACK TEMP CONTROLLER NO FAULTS FOUND ACCOMPLISHED FIM 21-61 TASK 858, CONTROL CABIN TEMP CONTROL OPS CHECK GOOD.
THE 'A' AUTO PILOT IS NOT WORKING. THE 'B' AUTOPILOT OPERATES NORMALLY. GROUNDED - YES. PERFORMED DFCS BITE PROCEDURE REF FIM 22-11 TASK 801. CURRENT STATUS SHOWED NO FAULTS. FAULT HISTORY HAD ONE OCCURRENCE OF FAULT #22-11251 AFCS ENGAGE INTLK ON LEG 14 (09 MAR 2019). PERFORMED LAND VERIFY TEST REF AMM 22-11-00 AND HGS SYSTEM TEST REF SMM 34-36-00 ALL TESTS PASSED. A/C APPROACH SURVEY COMPLETED. CLEARS MELS 22-1F AND 22-99B.
WHILE IN CRUISE, 300 NM NORTH OF HNL, LEFT F/D MASTER, LNAV/VNAV DROPPED OFF & AUTOPILOT WENT TO CWS R. NO OTHER INDICATIONS, SWITCHED TO AUTOPILOT B, LNAV/VNAV ENGAGED, THEN GOT VTK ON LEFT NAV DISPLAY. SOON 10-15 SEC LATER LNAV/VNAV AGAIN DROPPED OFF & AUTOPILOT WENT TO CWS R. LEFT VTK WENT AWAY AND RIGHT NAV VTK CAME ON. PUT AUTOPILOT A ON IT ENGAGED. GROUNDED - YES. CYCLED AIRCRAFT POWER, PERFORMED FMC BITE CHECK REF FIM TASK 34-61-TASK 801 ON FMC #1 & #2. BOTH FMC BITE CHECK PASS.
#1 ENGINE THRUST REVERSER HAS INTERMITTENT HISTORY OF LIGHT ON AND NOT DEPLOYING AND SETTING NO EAU FAULTS. GROUNDED - YES. PERFORMED B737-800 FIM 78-32 TASK 814. NO FAULTS FOUND. REMOVED AND REPLACED THE AUTOTHROTTLE SWITCHPACK IAW B737-800 AMM 76-11-07. GROUND VERIFICATION TEST CHECKS GOOD. NO FAULTS ON EAU.
LEFT PACK LIGHT ILLUMINATED DURING TAXI, EXTINGUISHED UPON RESETTING AMBER CAUTION. GROUNDED - YES. REMOVED LH PACK TEMP CONTROL VALVE (TCV) PER B737-800 AMM 21-51-10-000-801. INSTALLED TCV PER AMM 21-51-10-400-801. PERFORMED TCV INSTALLATION TEST PER SAME, INSTALLATION TEST PASSED PACK ZONE TEMP. CONTROLLER BITE PASS NO FAULTS.
REF LOG 11903751, EGT CONNECTOR CLEANING WAS ACCOMPLISHED PER FIM TASK 77-21-00-839-007. POST CLEANING RECHECK PER T/C 78273000, FOUND FAULT 77-20861 ON LEGS 1, 2, AND 3 (ENGINE 1). GROUNDED - YES. PERFORMED EGT SYSTEM RESISTANCE CHECK (ENG NR 1) REF AMM 77-21-01-200-801-F00. HIGH RESISTANCE FROM CJ10 + T49.5 PROBE (29K OHMS). COULD NOT ISOLATE FAULTY COMPONENT. RESISTANCE WENT TO NORMAL AFTER DISCONNECTING CJ10 FROM T49.5 PROBE AND RECONNECTING. AS A PRECAUTION, REMOVED/REPLACED CJ10 AND S3 PROBE REF AMM 73-21-06, 73-21-01. ALL RELATED TESTS CHECK NORMAL.
REF T/C NG-28FCD-18090-1 FOUND TWO PROBES OUT OF TOLERANCE, COMP PROBE AND NR 1 PROBE, TANK 2. GROUNDED - YES. REMOVED AND REPLACED TANK 2 COMPENSATOR PROBE AND TANK NR 1 PROBE REF AMM 28-41-21-400-801, OPS NML REF AMM 28-41-00-730-801. COMPENSATOR ACCESS PANEL SECURED AND NO LEAKS.
AIR CONDITIONING MASTER CAUTION WITH ASSOCIATED AUTO FAIL LIGHT ILLUMINATED DURING DESCENT. CONTINUED IN ALTN MODE PER QRH. PRESSURIZATION WAS NORMAL. GROUNDED - YES. ACCOMPLISHED AUTO FAIL LIGHT ON FAULT PER FIM 21-31 TASK 827 OPS CHECKS NORMAL.
WHEN WEATHER RADAR IS ON IN WX-T AUTO MODE, A VIBRATION COULD BE FELT IN COCKPIT FLOOR EVERY 10 - 15 SECONDS LASTING 2-3 SECONDS IN DURATION. VIBRATION GONE WITH WXR RADAR OFF. ACFT GROUNDED. REPLACED THE WX RADAR ANTENNA DRIVE UNIT. ALL OPS NORMAL IAW AMM 34-43-11, AND 34-43-00.
WEATHER RADAR DISPLAYS GHOST RETURNS AT 85 NM. MANUAL MODE APPEARS TO WORK NORMALLY. ACFT GROUNDED. REMOVED AND REPLACED WEATHER RADAR TRANSCEIVER IAW AMM 34-43-41, OPS CHECKED NORMAL IAW AMM 34-43-00-710-802-001.
AUTO MODE ON RADAR DISPLAYS SIGNIFICANT GROUND CLUTTER AT 85 NM RANGE AND BEYOND. TILT IN AUTO MODE -2 DEGREES AT 37000 AND DOES NOT ADJUST WHEN SELECTING LONGER RANGE. MANUAL MODE AT -1 DEGREE. ELIMINATES GROUND CLUTTER THE DISPLAY IS SAME ON BOTH CAPTAIN`S AND FIRST OFFICER`S N.D. ACFT GROUNDED. PERFORMED A WEATHER RADAR SYS OPS TEST IAW AMM 34-43-00-710-802-001, OPS TESTED GOOD. ALSO PERFORMED A WEATHER RADAR BITE TEST IAW FIM 34-43-00-810-801. NO FAULTS NOTED.
ON FINAL APPROACH, DESCENDING OUT OF 1000 MSL THE RIGHT FORWARD WINDOW OVERHEAT LIGHT ILLUMINATED. PERFORMED WINDOW OVERHEAT QRH ON TAXI IN AND THE OVERHEAT LIGHT ILLUMINATED AGAIN. GROUNDED - YES. ACCOMPLISHED WINDOW HEAT BITE TEST. WINDOW IS FAULTING SENSOR. SWAPPED SENSOR NO CHANGE REF FIM 30-41 TASK 801. REMOVED AND REPLACED R1 WINDOW REF AMM 56-11-11. OPS CHECKS FOR AIR AND WINDOW HEAT GOOD REF AMM 30-41-00-710-801.
SATCOM LOCKUP GROUNDED - YES. PERFORMED SATCOM LOCKUP QRH. SATCOM RETURNED TO MENU SATISFACTORY.
NR 2 ENGINE HAS PREVIOUS REPORTS OF FUEL FILTER BYPASS LIGHT ILLUMINATION ALONG WITH FUEL FILTER SIGNAL DISAGREE FAULTS. GROUNDED - YES. REPLACED FUEL DIFF PRESSURE SWITCH ON RT ENGINE REF AMM 73-34-01/401. REPLACED J8 HARNESS PER AMM 73-21-06 OPS CHKS GOOD NO DEFECTS NOTED, CLEARS TSR.
AFTER ENGINE START NR 2 ENGINE FILTER BYPASS CAUTION LIGHT AND FUEL ANNUNCIATOR LIGHT ILLUMINATED. GROUNDED - YES. NR 2 EEC F/C 73-31072, FUEL FILTER SIGNALS DISAGREE. FOUND CONNECTOR TO NR 2 ENG FFDPS/FFCI DIRTY. CLEANED & SECURED SAME. NR 2 FUEL FILTER BYPASS LITE IS OUT. RAN ENG NR 2. OPS CHECK DURING & AFTER ENG RUN GOOD. NO SAID LITE. REF FIM 73-05 TASK 801.
LT ACM DAMAGED. GROUNDED - YES. REMOVED AND REPLACED LT ACM REF AMM 21-51-04-400-802-002. OPS CHECK GOOD AND NO LEAKS FOUND.
WHILE ACCOMP T/C 78472002 FAN LUBE/INSP ON NR 1 ENG S/N 894549 FOUND ALL PLATFORMS HAD TORN/DAMAGED ELASTOMER SEALS OVER 38 INCHES. GROUNDED - YES. INSTALLED SERVICEABLE REPLACEMENT FAN BLADE PLATFORMS IN CONJUNCTION WITH IN PROGRESS NR 1 ENGINE FAN LUBE TASK CARD 78472002 UNDER W/O 414082.
WHILE ACCOMP T/C 78472002 FAN LUBE/INSPECTION NR 1 ENG S/N 894549 FOUND 2 EACH BLADE SPACERS WITH DISBONDED ELASTOMER. GROUNDED - YES. INSTALLED SERVICEABLE REPLACEMENT FAN BLADE SPACERS IN CONJUNCTION WITH IN PROGRESS NR 1 ENGINE FAN LUBE TASK CARD 78472002 UNDER W/O 414082.
WHILE ACCOMP T/C 78472002 FAN LUBRICATION NR 1 ENG S/N 894549 FOUND 4 EACH FAN BLADES WITH CONCAVE WEAR AT AFT END OF BLADE FROM SHIM CONTACT BLADE 9, 14, 20, 24. GROUNDED - YES. PER PAR K OF AMM SUBTASK 72-21-02-200-001-F00 MEASURED ABOVE BLADES USING REPORUBBER & STARLIGHT MEASURING SCOPE. 9 = 0.0065, 14 = 0.0065, 20 = 0.0070, 24 = 0.0063. REPLACED DEFECTIVE NR 1 ENGINE FAN BLADES & ASSOCIATED PAIRS. REINSTALLED BLADES MAPPED IAW BLAMAP 856A3770 V3 REFERENCE AMM 72-21-02-000-802-F00 & IN PROGRESS FAN LUBE TASK CARD 78472002 UNDER W/O 414082. PN & SN CHANGES RECORDED ON FIG 400 OF SUBJECT TASK CARD.
L1 DOOR HARD TO OPEN AND APPEARS TO BE OUT OF RIG. GROUNDED - YES. FOUND L1 DOOR GUIDE ARM RADIUS LINK PIN RETAINING SCREW SHEARED. L1 DOOR UPPER GUIDE PLATE REPLACED REF BDWG 141A8205, L1 DOOR GUIDE ARM REPLACED REF AMM 52-11-21/401. DOOR ADJUSTED TO WITHIN LIMITS REF AMM 52-11-00-820-801. DOOR SYSTEM TEST PASS REF AMM 52-11-00-700-804.
L1 DOOR BINDING AND DIFFICULT TO OPEN AFTER ARRIVAL. 15 MINUTES FOR MAINTENANCE AND F/A TO OPEN DOOR. ACFT GROUNDED. FIRST FEW TRIES DOOR WAS NOT EASY TO OPEN. ONCE IT OPENED, TRIED A FEW TIMES AFTER IT SEEMS OPERATIONAL. CONSULTED WITH OUTBOUND CREW, THEY OK IT. L1 DOOR OK FOR SERVICE, NO RECENT HISTORY.
DURING FAN BLADE LUBRICATION ON THE NR 2 ENGINE. ALL 24 PLATFORMS WERE MISSING RUBBER SEALS BEYOND TOTAL LIMITS. ACFT GROUNDED. REMOVED AND REPLACED THE PLATFORMS IAW T/C 78472002.
DURING A FAN BLADE LUBRICATION ON THE NR 2 ENGINE. FOUND THE NR 3 BLADE CU-NI-IN COATING MISSING BEYOND LIMITS. ACFT GROUNDED. REMOVED AND REPLACED THE NR 3 AND 15 FAN BLADES IAW T/C 78472002.
DURING MASTER CAUTION RECALL, CONTROL CABIN ZONE TEMP AMBER LIGHT ILLUMINATED. ACFT GROUNDED. PERFORMED FIM 21-62-00-810-801, PACK TEMPERATURE CONTROL-BITE PROCEDURE, ALL TESTS PASSED.
BACK SIDE OF OVERHEAD EXIT ROW, THE EXIT SIGN LENS WAS MISSING. ACFT GROUNDED. INSTALLED A NEW SIGN LENS IAW AMM 33-51-01-410-004. LIGHT CHECKED GOOD.
AUTO FAIL LIGHT & ALTN BOTH ON ON PRESSURIZATION PANEL. ACFT GROUNDED. REPOSITIONED MODE SELECTOR TO MANUAL AND THEN BACK TO AUTO. AUTO FAIL LIGHT EXTINGUISHED WITH THE PRESSURIZATION MODE SECTOR IN AUTO. OK FOR SERVICE.
ZONE TEMP ON CONTROL CABIN CAME ON WITH MC RECALL, WENT OUT WHEN RESET. ACFT GROUNDED. PERFORMED A BITE ON THE NR 1 AND 2 PACKS TEMP CONTROL. BITE TESTED GOOD, NO FAULTS. IAW FIM 21-62 TASK 801. NO HISTORY IN LAST 30 DAYS.
LEFT PACK LIGHT ILLUMINATED. EXTINGUISHED WITH A MASTER CAUTION RESET. ACFT GROUNDED. IAW FIM 21-53 TASK 807, 1 & 2 PZTC BITE TESTED GOOD. NO PREVIOUS FLT FAULTS LOGGED. VERIFIED LEFT PACK OPS CHECKED NORMAL ON GROUND WITHOUT FAULTS.
NR 2 ENGINE FIRE HANDLE & OVERHEAT LIGHTS DO NOT ILLUMINATE DURING FIRE TEST. ACFT GROUNDED. PERFORMED RESISTANCE CHECKS. CHECKED GOOD IAW FIM 26-10 TASK 805. REMOVED AND REPLACED THE UPPER FAN DETECTOR ASSEMBLY. OPS CHECKED GOOD IAW AMM 26-11-01.
CONTROL CABIN ZONE TEMP LIGHT ON CLIMB OUT. RESET WITH MASTER CAUTION RECALL. ACFT GROUNDED. REPLACED CONTROL TRIM VALVE IAW AMM 21-61-21-000-801, AND 21-61-21-400-801, OPS CHECKED GOOD.
LEFT PACK LITE ILLUMINATES ON RECALL. LITE EXTINGUISHES WHEN MASTER CAUTION RESET PUSHED. GROUNDED - YES. ACCOMPLISHED FIM 21-53 TASK 807 AND PACK CONTROLLER BITE REF AMM 21-61-00. NO FAULTS. LEFT PACK OPS CK NRML REF AMM 21-00-00.
NR 2 ENG FIRE DETECTION LOOP B TEST FAULT. GROUNDED - YES. ACCOMPLISHED TSR 701294, FIM 26-10 TASK 805 ENGINE - WIRING HARNESS/FIRE DETECTOR. M01759 LEFT CORE FIRE DETECTOR AND M01760 RIGHT CORE FIRE DETECTOR FOUND BAD. REMOVED AND REPLACED M01759/M01760 ENGINE FIRE DETECTORS IAW AMM TASK 26-11-01/401. PERFORMED OPERATIONAL ENGINE FIRE DETECTION OPERATIONAL TEST IAW AMM TASK 26-11-000-710-801, TEST GOOD.
NUMBER 2 ENGINE FIRE TEST DOES NOT TEST NORMAL WITH BOTH LOOPS SELECTED. DOES TEST NORMAL WITH ONLY THE A LOOP SELECTED. ACFT GROUNDED. PERFORMED AN ENGINE FIRE DETECTION IAW FIM 26-10 TASK 801, INDICATED THE NR 2 ENG LOOP B FAULTED. CYCLED THE NR 2 ENGINE FIRE HANDLE AND NR 2 ENGINE FIRE LOOP GROUND. TESTED GOOD. CONTROL MODULE BITE SHOWS NO FAULTS. NO HISTORY PREVIOUS 30 DAYS.
NR 2 TAI INDICATION AMBER AFTER ENGINE START AND ANTI-ICE SELECTED ON. ACFT GROUNDED. REMOVED AND REPLACED THE NR 2 TAI VALVE IAW AMM 30-21-11/401. OPS TESTED GOOD. LEAK CHECKED GOOD. ALL INDICATIONS NORMAL. PERFORMED BONDING TEST. BONDING TESTED GOOD IAW AMM 30-21-11.
AFTER ENGINE START "ELEC" LIGHT ON OVERHEAD PANEL ILLUMINATED. ACFT GROUNDED. PERFORMED FIM 24-31 TASK 801 & LOGGED SPCU INOPERATIVE FAULT. PERFORMED FIM 24-34 TASK 804 & FAULT CLEARED. BITE CHECK PASSED & GROUND FUNCTIONAL CHECKED GOOD.
DURING ACCOMPLISHMENT OF E/C SBCFM56-7B-72-0986 ENG S/N #2 ENG FOUND STAGE NR 2 ANTI-ROTATION PIN AT 9 O'CLOCK ROTATED ABOUT 80 DEG. ACFT GROUNDED. REPLACED THE NR 2 ENGINE IAW T/C 7847100, & 78471001.
#2 ENGINE IDG AIR/OIL COOLER LEAKING. GROUNDED - YES. REMOVED AND REPLACED THE #2 ENGINE IDG AIR/OIL COOLER, LEAK CHECK GOOD, REF B737-800 AMM 24-11-21/401.
R1 WINDOW OVERHEAT LIGHT ON. ACFT GROUNDED. RESET THE SYSTEM AND PERFORMED WINDOW HEAT SYSTEM OPERATIONAL TEST IAW AMM 30-41-00-710-801. R1 WINDOW OVERHEAT LIGHT EXTENGUISHED. TESTED MULTIPLE TIMES, LIGHT REMAINED OUT. NO OTHER DEFECTS WITH SYSTEM NOTED.
EXPERIENCED 4 DUAL FMC FAILURES WITHIN AN HOUR. EACH TIME THE FMCS RECOVER BUT DUMPED ALL FMC DATA. NO FAILURES EXPERIENCED WITHIN LAST 3 HOURS OF FLIGHT. ACFT GROUNDED. REPLACED THE LT AND RT FMC COMPUTERS IAW AMM 34-61-02-400-801. LOADED ALL SOFTWARE IAW AMM 34-61-00/201, USING LAPTOP SYSTEM. ENTERED PERFORMANCE FACTORS IAW AMM 34-61-00-800-801, USING TABLE 501 IN AMM 34-61-00-730-801. DRAG FACTOR -1.3 FOR ETOPS WITH SPLIT SCIMITAR WINGLETS. VERIFIED ALL VALUES CORRECT, FMCS OPS TEST OK IAW AMM 34-61-00-710-801.
APU FAULT LIGHT ILLUMINATED DURING ATTEMPTED TO START AT THE GATE. QRH PROCEDURE ACCOMPLISHED. LIGHT WENT OUT. SECOND START ATTEMPT WAS SUCCESSFUL. GROUNDED. OPS CHECKED APU, APU STARTED 1ST TRY, OPS NORMAL, NO HISTORY.
AFTER ENGINES STARTED THE LT ELEVATOR PITOT LIGHT ILLUMINATED. ACFT GROUNDED. IAW WDM 30-31-11 FOUND THE LT ELEVATOR PITOT HEATER OPEN D644 PIN 40 TO GND OPEN. REPLACED LT ELEVATOR PITOT TUBE IAW AMM 27-31-94-000-801 & -400-801. OPS NORMAL. LEAK CHECKED GOOD IAW AMM 27-31-17-790-801.
AFT CARGO BAY, LT TRANSITION PANEL UPPER AND LOWER SURFACES, SEVERAL AREAS CORROSION, BS 727 - 790, LBL 20 - 20.5. ACFT GROUNDED. REMOVED THE CORROSION IAW SRM 53-00-53. FOUND TO BE OUT OF LIMITS. REMOVED THE TRANSISTION PANEL AND FABRICATED A NEW TRANSITION PANEL IAW SRM 53-00-53-2R-5, REPAIR 5. ALODINED AND PRIMED IAW SRM 51-20-01 AND INSTALLED IAW SRM 53-00-53-2R-5, REPAIR 5.
AFT CARGO BAY RT TRANSITION PANEL CRACKED BS 727J, RBL 22. ACFT GROUNDED. REMOVED THE TRANSITION PANEL, FABRICATED A NEW TRANSITION PANEL IAW SRM 53-00-53-2R-5, REPAIR 5. ALODINED AND PRIMED IAW SRM 51-20-01, AND INSTALLED IAW SRM 53-00-53-2R-5, REPAIR 5.
FORWARD CARGO COMPARTMENT, LT INTERCOSTAL AT STRINGER 25L STA 500H HAS CRACKED SUPPORT ANGLES ON FWD AND AFT SIDE. GROUNDED - YES. REMOVED AND REPLACED SUPPORT BRACKETS AT STA 500H LT FWD AND AFT SIDES IAW BAC DWG 143A7505 REV A.
COCKPIT FLOOR DENTED BS 263 - 264, BL 0. ACFT GROUNDED. REPAIRED THE FLOOR WEB IAW SRM 53-10-51-2R-2.
FORWARD CARGO COMPARTMENT, LT INTERCOSTAL AT STRINGER 25L STA 500G HAS CRACKED SUPPORT ANGLES ON FWD SIDE. GROUNDED - YES. REMOVED AND REPLACED SUPPORT BRACKET STA 500G LT FWD SIDE IAW BAC DWG 143A7505 REV A.
DURING THE NR 1 ENGINE SHUTDOWN , AN EGT RED BOX APPEARED. THIS WAS A TAKEOFF EXCEEDANCE. ACFT GROUNDED.
AFTER TAKE OFF. LEFT PACK LIGHT ILLUMINATED. ACCOMPLISHED QRH. PACK LIGHT DID NOT RESET. TURNED OFF THE LEFT PACK AND CLOSED ISOLATION VALVE. LEVELED OFF AT FL 250. ACFT PRESSURIZED NORMALLY. ACFT GROUNDED. PACK ZONE TEMP CONTROLLER 1 SHOWS TCV FAULT LAST AND PREVIOUS FLTS. REMOVED AND REPLACED TEMPERATURE CONTROL VALVE ON THE NR 1 PACK IAW AMM 21-51-10-000-801. LEAK CHECKED GOOD, GROUND VERIFICATION GOOD. ACCOMPLISHED ENGINE RUN.
ON APPROACH, AUTO FAIL LIGHT ILLUMINATED. SWITCHED TO ALTERNATE MODE. CONTINUED NORMALLY. ACFT GROUNDED. CABIN PRESSURE CONTROLLER NR 1 AND 2 FAULT LOW INFL/HIGH LEAKAGE. ACCOMPLISHED PRESSURIZATION CONFIDENCE CHECK.IAW AMM 21-00-05-780-801. OPS CHECKED GOOD.
FORWARD RIGHT OVERHEAT LIGHT ILLUMINATED ON GROUND. GROUNDED - YES. SWITCHED RIGHT FORWARD WINDOW SENSOR TO THE SPARE SENSOR IAW FIM 30-41, TASK 812. RIGHT FORWARD WINDOW HEAT DETECTION OPS CHECKED GOOD.
FAULT LIGHT ILLUMINATED DURING APU START. FOLLOWED QRH. AFTER 5 MIN RE-ATTEMPTED START AND LIGHT ILLUMINATED AGAIN. GROUNDED - YES. APU LAST FLIGHT LEG FAULT HISTORY SHOWS FAULT LIGHT MAINTENANCE MESSAGE 49-61157, ECU INTERNAL FAILURE. PERFORMED APU BITE PER FIM 49-60 TASK 804. PERFORMED APU BITE PER FIM 49-60 TASK 801. NO MAINTENANCE MESSAGES WERE SHOWN ON CURRENT STATUS PAGE. APU STARTED NORMALLY.
NR 1 ENGINE FRONT SPINNER CONE PAINT WORN BELOW LIMITS. ACFT GROUNDED. REMOVED AND REPLACED THE NR 1 ENGINE FRONT SPINNER CONE IAW T/C 78072002.
ALL 24 BLADE SHIMS FOUND TO BE WORN ON THE NR 1 ENGINE. ACFT GROUNDED. REMOVED AND REPLACED THE BLADE SHIMS IAW T/C 78472002.
MCP N1 BUTTON DOES NOT ILLUMINATE. ACFT GROUNDED. CONFIRMED N1 BUTTON LIGHT DOES NOT ILLUMINATE WHEN PRESSED. ACCOMPLISHED ALT DEACTIVATION IAW CHAPTER 5, TABLE 3, ITEM 1. REMOVED AND REPLACED MODE CONTROL PANEL IAW AMM 22-11-34-401. ACCOMPLISHED OPS TESTS, OPS TESTED NORMAL. ACCOMPLISHED LAND VERIFY TEST 49. ALL REQUIRED TESTS PASSED.
TRU UNIT LIGHT ILLUMINATED ON PREFLIGHT. GROUNDED - YES. VERIFIED DISCREPANCY T3 LIGHT ON. REMOVED AND INSTALLED NEW TR3 UNIT, REF FIM 24-31 TASK 826. PERFORMED TR3 OPS TEST - NO HELP, REF AMM 24-32-11. REMOVED AND INSTALLED NEW SPCU, REF AMM 24-34-11. PERFORMED STANDBY POWER OPS TEST, SYS CHECKS NORMAL, REF AMM 24-34-11.
REF MEL 21-32B RH PACK LIGHT FAILS TO EXTINGUISH AFTER RECALL AND MASTER CAUTION RESET. GROUNDED - YES. REF AMM FIM TASK 21-61-801 RESET BOTH ZONE TEMP CONTROLLERS ALL FAULTS CLEARED MASTER CAUTION LT NOW DOES NOT ILLUMINATE AND EXTINGUISHED OK FOR CONTINUED SERVICE
RT PACK LIGHT FAILED TO EXTINGUISH AFTER RECALL AND MASTER CAUTION RESET. GROUNDED - YES. REF AMM TASK 21-61-801. PERFORMED TEMP CONTROLLER BITE, CLEARED FAULTS, RESET SYSTEM. PACK TEMP CONTROL IN CABIN NOW RESETS WITH MASTER CAUTION. OK FOR SERVICE.
RIGHT PACK LIGHT WAS ILLUMINATED AFTER TAKEOFF. PACK LIGHT EXTINGUISHES WHEN MASTER CAUTION RESET IS PUSHED. GROUNDED - YES. PERFORMED RT PACK ZONE TEMP CONTROLLER BITE AND FOUND TCV FAULT IN VERIFY ONLY, REF AMM 21-51-00. REMOVED AND REPLACED RT PACK TEMP CONTROL VALVE, REF AMM 21-51-10. INSTALLATION TEST, LEAK CHECK, AND BITE TEST GOOD. NO NEW FAULTS. ETOPS SIGNIFICANT SYSTEM GROUND VERIFICATION SUCCESSFUL.
SATCOM INOPERATIVE. GROUNDED - YES. ACCOMPLISHED SATCOM TST REF AMM 23-15-00-780-801. OPS TST NRML PER SAME. NO HISTORY LAST 30 DAYS. CLEARED MEL 23-18.
SUPPLY DUCT IN FWD AND CONTROL CABIN INDICATED 100+ DEGREES. INDICATION FLUCTUATED, NO ZONE TEMP LIGHTS. ACFT GROUNDED. REMOVED & REPLACED TEMP CONTROL MODULE P5-17 IAW AMM 21-61-15 & 401. CHECKED GOOD IAW AMM TASK 21-61-00-700-807-002. OPS NORMAL.
AIR TEMP CONT CAB IN "FWD" POSITION INDICATES 100+ AT CRUISE. FLIGHT ATTENDANT REPORTS HOT AIR IN CABIN ROWS 6-10. GAUGE FLUCTUATES AT TIMES WHEN IN FWD AND CONT CAB POSITION. GROUNDED - YES. INITIAL EVALUATION SHOWED ALL GAUGE READINGS NORMAL. SUSPECT INTERMITTENT FAULT. CLEANED FLIGHT DECK AND CABIN SENSOR FILTERS. PERFORMED FIM TASK 21-61 TASK 858 AND 21-61 TASK 859. SYSTEM OPERATED NORMALLY. TEMP IN CABIN AND FLIGHT DECK REFLECTED WHAT WAS ON GAUGE.
AIR TEMPERATURE SOURCE SELECTOR SWITCH INDICATES ERRATIC TEMP IS WHEN MOVED. ACFT GROUNDED. FOUND AIR TEMP SELECTOR SWITCH EXTREMELY LOOSE IN PANEL. REMOVED CONTROL PANEL LIGHT PLATE, NUT SECURING SWITCH TO PANEL WAS 5 FULL TURNS FROM TIGHT. TIGHTENED THE NUT. RE-SECURED LIGHT PLATE & KNOBS. OPS NORMAL IAW AMM 21-61-32, ALL TEMP SELECTIONS READ STEADY.
NR 2 ENGINE FAN BLADE SHIMS 24 EA REQUIRE REPLACEMENT. GROUNDED - YES. REMOVED AND REPLACED ALL 24 SHIMS ON NR 2 FAN BLADES REF TASK 78472002.
ENGINE 1 SHOW ECONOMIC FAULT. EGT SIGNAL IS OUT OF RANGE. BOTTOM LEFT. GROUNDED - YES. NR 1 ENGINE FAULT 77-20861 WAS LOGGED ON ALL TEN STARTS IN EEC MEMORY AND INPUT MONITORING SHOWED BOTTOM LEFT PROBE (T495S3) TO BE ALL DASHES. REMOVED AND REPLACED BOTTOM LEFT EGT PROBE (T495S3) PER AMM 77-21-01-000-801-F00 / 77-21-01-400-801-F00. INPUT MONITORING NOW SHOWS NORMAL READINGS FOR ALL NR 1 ENGINE EGT PROBE INPUTS. PERFORMED EEC TEST PER AMM 73-21-00-700-804-F00 - ALL TESTS PASS. CLEARS PLT DEFERRAL.
NR 1 ENGINE BLEED DUCT INTERSECTION HAS WORN BUSHING AT SUPPORT ROD. ACFT GROUNDED. REMOVED THE INTERSECTION DUCT AT NR 1 ENGINE IAW AMM 36-11-01-000-802 STEP E. INSTALLED NEW INTERSECTION MANIFOLD DUCT ON NR 1 ENGINE IAW AMM 36-11-01-400-802.
LEFT PACK LIGHT ILLUMINATES ON RECALL, WILL RESET WITH MASTER. GROUNDED - YES. REMOVED AND REPLACED LEFT PACK PRIMARY TEMP CONTROL VALVE REF AMM 21-51-10. PACK/ZONE TEMP CONTROLLER BITE TEST SATISFACTORY. REF AMM 12-61-00. LEAK CK. GOOD. CLEARS MEL 21-32B.
EMERGENCY LIGHT LENS ON INSIDE OF L1 DOOR BROKEN. ACFT GROUNDED. REMOVED AND REPLACED THE LENS.
NR 2 IDG DPI TRIPPED. ACFT GROUNDED. COMPLETED NR 2 IDG DPI INSPECTION IAW AMM 12-13-21. REMOVED AND REPLACED THE NR 2 IDG FILTERS IAW AMM 12-22-41. LEAK CHECKED OK.
MESSAGE 73-31371 FOR UPPER EGT SECTORS READING HIGH ILLUMINATED. ACFT GROUNDED. REMOVED AND REPLACED THE NR 1 ENGINE FUEL NOZZLES, IAW TC 73CMPT-07267-2 AND EA 800-36EA-18334.
DURING PDC, FOUND THE NR 2 IDG DPI TRIPPED. ACFT GROUNDED. PERFORMED FIM 24-11 TASK 803 ALONG WITH AMM 24-11-41-200-801 & AMM 24-11-41 IDG SCAVENGE FILTER INSP & CHANGE. NO DEFECTS NOTED. LEAK CHECKED GOOD. FIRST DPI RESET ON NR 2 IDG.
NR 1 ENGINE RIGHT FAN COWL ALIGNMENT BRACKET AT THE 6 O'CLOCK POSITION FOUND BROKEN. ACFT GROUNDED. REMOVED THE BRACKET, POSITIONED NEW BRACKET IAW AMM 20-50-11.
CAPTAIN`S MCP CRS SELECTOR WINDOW HAS DAMAGED SEGMENTS. ACFT GROUNDED. REMOVED & REPLACED THE MODE CONTROL PANEL IAW AMM 22-11-34, INSTALLATION TEST PASSED. ACCOMPLISHED DFCS LRU INTERFACE TEST FOR MCP 32, LAND VERIFY TEST 49 & HGS SENSOR TEST FOR FCC/AT IAW AMM 22-00-01 & SMM 34-36-00, ALL TEST PASSED. ACFT REMAINS CAT III A AUTOLAND & HGS QUALIFIED, STATUS SCREW REFLECT SAME.
DURING 800-28EA-16443, FOUND THE NR 1 FUEL QUANTITY FAILS SYSTEM TEST IAW AMM TASK 28-41-00-730-801. ACFT GROUNDED. REPLACED THE TANK UNIT NR 1 AND COMPENSATOR PROBE. FQIS READS NORMAL IAW AMM 28-41-21, AND 28-41-00.
DURING 800-28EA-16443, FOUND THE NR 2 FUEL QUANTITY FAILS SYSTEM TEST IAW AMM 28-41-730-801. ACFT GROUNDED. ACCOMPLISHED TANK AND COMPENSATOR TEST IAW AMM 28-41-21. FOUND F15R COMPENSATOR AND F1R, F8R, F9R, AND F10R BAD. REMOVED AND REPLACED TANK AND COMPENSATOR UNITS IAW AMM 28-41-21. FUEL QUANTITY SYSTEM TEST WITHIN LIMITS IAW AMM 28-41-00. COMPARISON CHECKED GOOD IAW AMM 28-41-00-720-801.
OVERHEAT LIGHT ON FOR LH FWD WINDOW. ACFT GROUNDED. REPLACED LT NR 1 WINDOW IAW AMM 56-11-11-000-801 AND 56-11-11-400-801. GROUND VERIFICATION OF WINDOW HEAT IS GOOD.
DURING DESCENT, ENGINE ANTI-ICE TURNED ON. COWL VALVE OPEN LIGHT REMAINED ON. AMBER TAI ON ENGINE DISPLAY INDICATING ANTI-ICE VALVE FAILED CLOSED. CONFIRMED WITH FLIGHT CREW NR 2 ENGINE WAS THE ISSUE. ACFT GROUNDED. REPLACED NR 2 ENGINE INLET COWL ANTI-ICE VALVE, REF AMM 30-21-11. OPS NORMAL.
28 VOLT DC CHARGER HAD BRIEF ELECTRICAL ODOR WHEN PLUGGED INTO SERVICE OUTLET. REMOVED AND NO LONGER HAD ODOR THOUGH OUTLET PLUG NO LONGER HAS GROUND ATTACHED. ACFT GROUNDED. 28 VOLT DC CHARGER IS INOPERATIVE, GROUND CONNECTOR BROKEN. IAW WDM 25-29-11, CONFIRMED 28 VDC AT CONTROL CABIN DC SERVICE OUTLET P6-6. OPS TEST NORMAL.
FLIGHT DECK ZONE TEMP LIGHT ILLUMINATES ON RECALL, EXTINGUISHES WITH MASTER CAUTION RESET. ACFT GROUNDED. NR 2 ZONE TEMP CONTROLLER LOGGED FLIGHT DECK TRIM VALVE FAULT. RESET FAULT. ACCOMPLISHED ZONE TEMP CONTROLLER BITE IAW AMM 21-61-00,TEST PASSED.
DURING POST RUN LEAK CHECK FOR NR 2 HPTACC VALVE CHANGE, FOUND RT VSV LEAKING AT A RATE OF 4 DROPS PER MINUTE. ACFT GROUNDED. R & R RT VSV ACTUATOR, REF AMM 75-31-01. ACCOMPLISHED VSV ACTUATOR LEAK TEST ON NR 2 ENGINE, RT VSV ACTUATOR NO LEAKS NOTED, REF AMM 75-31-01.
FOUND ECONOMIC FAULT NR 1 ENGINE 73-31371 UPPER EGT SECTORS READING HIGH. ACFT GROUNDED. FOUND FAULT ON LEG 6 ONLY. ACCOMPLISHED NR 1 ENGINE EGT INDICATING SYSTEM CLEANING IAW AMM 77-21-00-140-801. INTERROGATED NR 1 EEC, NO RECENT FAULTS LOGGED.
ELECTRIC LIGHT WITH MASTER CAUTION ELECTRIC LIGHT ILLUMINATED ON GROUND AFTER LANDING. ACFT GROUNDED. ACCOMPLISHED SUCCESSFUL GROUND VERIFICATION, PERFORMED ELEC LIGHT MESSAGE BITE IAW FIM 24-31 TASK 801, FAULTED "AUX BATTERY CHARGER INOPERATIVE CLEARED FAULT. ACCOMPLISHED BITE, NO FAULTS NOTED. PERFORMED AUX BATTERY CHARGER INOPERATIVE MESSAGE TASK IAW FIM 24-31 TASK 825. AUX CHARGER SHOWING 2 GREEN LIGHTS, NO FAULTS NOTED.
DURING PREFLIGHT, DISCOVERED ELECTRIC LIGHT ILLUMINATED. ACFT GROUNDED. BITE CHECK OF P5-13 SHOWS AUX BATTERY CHARGER INOPERATIVE. REPLACED AUX BATTERY CHARGER IAW AMM 24-31-31. INSTALLATION TEST NORMAL.
WHILE PERFORMING TC 78273000, FOUND NR 1 ENGINE TO HAVE ECONOMIC MESSAGE 73-31371 ON FLIGHT LEG 2. NO HISTORY 90 DAYS. ACFT GROUNDED. NOT SHOWING ANY RECENT FAULTS OR LOGGING ANY FAULTS IN FAULT HISTORY. FAULT CODE 73-31371 UPPER EGT SECTORS READING HIGH. PERFORMED EEC BITE TEST REF FIM 73-00, TASK 801. NO DEFECTS NOTED.
SATCOM LOCKUP. ACFT GROUNDED. ACCOMPLISHED SATCOM RESET PROCEDURE IAW QRH. SATCOM OPS RESTORED NORMAL.
NR 2 ENGINE ANTI-ICE LIGHT ON WITH ENGINE ANTI-ICE ON TAI AMBER LIGHT NR 2 ILLUMINATED. RECYCLED LT OUT. ACFT GROUNDED. RAN NR 2 ENGINE CYCLED, ENGINE ANTI-ICE NO DISCREPANCY NOTED. IAW FIM 30-21, TASK 801 AND LIGHT NOT ON. SUSPECT INTERMITTENT FAULT. NO HISTORY OK FOR SERVICE AT THIS TIME.
AFTER ENGINE START, FLOW DISCONNECTED CONTROL CAB ZONE TEMP LIGHT ON MASTER CAUTION RECALL. ACFT GROUNDED. PERFORMED BITE TEST OF PACK/ZONE TEMP CONTROLLERS IAW AMM 21-61-00. FOUND NR 2 CONTROLLER WITH FLIGHT DECK ZONE TRIM VALVE RED FAULT LIGHT ON DURING TEST. FAULT LIGHT EXTINGUISHED AT CONCLUSION OF TEST AND DURING SUBSEQUENT BITE TEST. OPS NORMAL IAW ABOVE REF. NO CURRENT FAULTS AND CONTROL CABIN ZONE TEMP LIGHT REMAINS EXTINGUISHED WITH MASTER RECALL.
NR 1 HF RADIO TRANSMIT FUNCTION IS INTERMITTENT. RECEIVE FUNCTION IS NORMAL. ACFT GROUNDED. ACCOMPLISHED NR 1 HF COMMUNICATION TEST, AIRPLANE TO AIRPLANE, WITH NORMAL OPERATION IAW AMM 23-11-00-730-801.
WHILE PERFORMING T/C 78273000, FOUND NR 1 ENGINE, ESN 849549 HAS ECONOMIC MESSAGE 77-20861, THE BOTTOM LT EGT SIGNAL, T495S3 IS OUT OF RANGE. ACFT GROUNDED. ENGINEERING REQUEST ACCOMPLISHED, REF TSR907942. R & R CJ10 HARNESS ON THE NR 1 ENGINE, REF AMM 73-21-06. OPS CHECKS COMPLETE.
EMERGENCY OVERWING FWD OUTSIDE LIGHT INOPERATIVE. ACFT GROUNDED. R & R EMERGENCY OVERWING FWD OUTSIDE LIGHT BULB WITH A SERVICEABLE UNIT AS REQUIRED. OPS CHECK GOOD AT THIS TIME.
DURING ACFT TOW, ALL ATC RADIO READ BACKS UNREADABLE. ACFT GROUNDED. PERFORMED RADIO CHECK. OPS CHECK OF RADIOS IAW AMM 23-12-00. UNABLE TO DUPLICATE DEFECT. ALL GROUND TESTS PASS.
FMC DISAGREE DURING TAXI OUT. ACFT GROUNDED. ACCOMPLISHED RESET PROCEDURE IAW QRH. FMCS RESTORED NORMAL.
FOUND NR 1 ENGINE WITH ECONOMIC FAULT MESSAGE 77-20871, TOP LT EGT SIGNAL IS OUT OF RANGE. ACFT GROUNDED. ENGINE 1 ELECTRONIC ENGINE CONTROL SHOWS NO RECENT AND FAULT HISTORY FAULTS LAST 10 FLIGHTS. IAW FIM 77-21, TASK 804, T495 PROBES CLEANING REF AMM 77-21-00, BEFORE CLEANING S1 TO S4 GOOD. S2 TO S3 WERE OUT OF TOLERANCE. AFTER CLEANING S1 TO S4 AND S2 TO S3 GOOD. ELECTRONIC ENGINE CONTROL TEST REF AMM 73-21-00 GOOD. ENGINEERING REQUEST ACCOMPLISHED - T49.5 PROBE AND EGT SYS INSPECTED, CLEANED CONNECTIONS. OPS GOOD. GROUND VERIFICATION SUCCESSFUL.
AIRCRAFT HAS RECENT HISTORY OF THE RT PACK TRIP. ACFT GROUNDED. TSR ISSUED. INSPECTED FAN BYPASS CHECK VALVE IAW AMM 21-51-03, NO DEFECTS NOTED. R & R RT PACK FLOW CONTROL VALVE IAW AMM 21-51-01, OPS AND LEAK CHECKED GOOD.
"ELECTRIC" LIGHT AND MASTER CAUTION ILLUMINATED AFTER SWITCHING POWER SOURCE FROM EXTERNAL TO APU. ACFT GROUNDED. PERFORMED FIM TASK 24-31, TASK 801, P5-13 PANEL BITE NORMAL WITHOUT FAULTS. FOUND APU GCU UNABLE TO BITE. RERACKED APU GCU. PERFORMED FIM TASK 24-21, TASK 801. NO FAULTS FOUND.
RIGHT PACK LIGHT ILLUMINATED ON TAXI OUT. IAW PILOT DEBRIEF, WITH THROTTLES ADVANCED, RT PACK TEMP INDICATOR INCREASED WITH THROTTLES. TEMP IN 60 DEGREE C RANGE. RT PACK LIGHT WOULD NOT RESET. ACFT GROUNDED. BITE OF PACK ZONE TEMP CONTROLLERS, NO FAULTS LOGGED. NO HISTORY LAST 60 DAYS. ACCOMPLISHED HEALTH CHECK ON RT ENGINE, TC NG-36WC-00001, NO DEFETS NOTED. ACCOMPLISHED A LEAK CHECK OF RT PACK FCSV, NO DEFECTS. REF FIM TASK 21-53, TASK 802, STEP F 5. ACCOMPLISHED ENGINE BLEED AIR CROSSOVER TEST AND RAN PACKS. NO DEFECTS NOTED, REF MM TASK 26-11-00-710-801.
CUSTOMER WALKAROUND: L1 DOOR MAKING POPPING SOUND ON OUTSIDE NEAR UPPER HINGE WHEN CLOSING. ACFT GROUNDED. R & R L-1 DOOR CENTER ASSIST SPRING IAW AMM 52-11-41. OPS CHECK GOOD IAW AMM 52-11-41.
LT HORIZONTAL STABILIZER HAS CRACK INDICATION APPROXIMATELY 2.5" IN LENGTH, STABILIZER BS 95 AT FWD FASTENER ROW OF AFT SPAR. ENDS ARE MARKED IN RED. ACFT GROUNDED. REMOVED DAMAGED AREAS IAW SRM 55-10-01, PERFORMED HFEC ON CUT OUT IAW NDTM 51-00-00 PROCEDURE 23 TOOL, T8257A MATERIAL ID FOR REPAIR PARTS IS 2024-T3 .071, PO 850337.1 & 2024 T3 .100, PO 833494.2. FABBED, LOCATED & DRILLED REPAIR PARTS IAW SRM 55-10-01-2K-11. INSTALLED REPAIR PARTS IAW SRM 51-40-02. PAINTED REPAIR AREA IAW SRM 55-10-01-2R-11.4.0. REPAIR IS CATEGORY "B" WITH AN INSPECTION THRESHOLD OF 56,000 TOTAL COMPONENT FLIGHT CYCLES AND AN INTERVAL OF 9,000 FLIGHT CYCLES IAW SRM 55-10-01-2R-11.5.A TABLE 204.
DURING ACCOMPLISHMENT OF T/C 78273000, FOUND MSG NR 77-20861. BOTTOM LT EGT SIGNAL, 7495S3, OUT OF RANGE NR 1 ENGINE. ACFT GROUNDED. IAW FIM TASK 77-21, TASK 803 EXAMINED AND CLEANED CONNECTOR FOR T49.5 S3 ON NR 1 ENGINE PRE-CLEAN READINGS FOR T49.5S3 WAS 214.14, POST CLEAN READING FOR T49.5S3 AS 18.75 IAW AMM 70-70-01-200-801-F00. ENGINE NR 1 EEC BITE PASSED IAW AMM 73-21-00-700-804-400. NO FAULTS FOUND.
UNABLE TO CONTROL CABIN TEMPRATURE PROPERLY. FWD AND AFT CAB KNOBS IN FULL COLD DRIVE SUPPLY DUCTS TO 10 DEG, IF MOVE THEM TO 12 O`CLOCK POSITION, SUPPLY DUCTS STAY AT 10 DEG C, MUST MOVE THEM TO 1 O`CLOCK POSITION FOR TEMP TO INCREASE. IN "FIXED CABIN TEMP MODE", ALL 3 OFF, LEFT PACK READ 30 DEGREES INSTEAD OF 24 DEGREES IAW SYSTEMS MANUAL AND RT PACK READS 24 DEGREES INSTEAD OF 18 DEF IAW SYS MANUAL. ACFT GROUNDED. FOUND FWD & AFT CABIN SENSORS FILTERS CLOGGED. CLEANED FWD & AFT CABIN SENSORS & REPLACED FWD & AFT CABIN SENSOR FILTERS. OPS CK GOOD. REF AMM 21-61-10, 21-61-06, 21-61-00-700-807-002.
FMC DISAGREE MESSAGE ON GROUND. ACFT GROUNDED. QRH FOLLOWED NORMAL OPS RESTORED.
WHILE ACCOMPLISHING T/C 78237000, FAULT 77-20871. TOP LT EGT SIGNAL, T49554, OUT OF RANGE, ON LEGS 0123. ACFT GROUNDED.
FAULT LIGHT ILLUMINATED DURING INFLIGHT START FL 340 LIGHT EXTINGUISHED WITHIN 5 MINUTES. SUBSEQUENT START SUCCESSFULL. ACFT GROUNDED.
ON RECALL CONT CAB ZONE TEMP LIGHT CAME ON WHEN MASTER CAUTION LIGHT RESET PUSHED LIGHT WENT OUT. ACFT GROUNDED. NR 2 ZTC LOGGED FLT DECK TRIM VALVE - BITE TEST GOOD - FAULT RESET.
FAULT LIGHT ILLUMINATED DURING APU START ATTEMPT, FL 380. ACFT GROUNDED. IAW POWERPLANT ENGINEERING REQUEST, REPLACED APU INLET TEMPERATURE SENSOR REF AMM 49-61-31 AND APU INLET PRESSURE SENSOR, REF AMM 49-52-31. APU GROUND VERIFICATION STARTS AND OPS NORMAL.
FOUND MCDU NR 1 INOPERATIVE. ACFT GROUNDED. VERIFIED CAPT MCDU IS INOPERATIVE. REPLACED CAPTAINS MCDU, ALL OPS NORMAL, REF MM 34-61-01.
ELECTRIC LIGHT ON. ACFT GROUNDED. ACCOMPLISHED ELECTRIC LIGHT BITE REF FIM 24-31, TASK 824. "BATTERY CHARGER INOPERATIVE" ILLUMINATED. RESET, FAULT EXTINGUISHED, NO RECALL. NO HISTORY PAST 90 DAYS. BOTH GREEN LIGHT ON CHARGER ON. OPS CHECK NORMAL.
FIRST ATTEMPTED APU START AT FL 400. APU START FAILED ON FIRST ATTEMPT WITH FAULT LIGHT. QRH FAULT LIGHT EXTINGUISHED AFTER 5 MINUTES. DESCENDING TO FL 340 FOR 2ND ATTEMPT, APU START SUCCESSFUL AT FL 340. ACFT GROUNDED. R & R APU START POWER UNIT AND START CONVERTER UNIT IAW AMM REF'S 49-41-71-801/49-41-71-400-801 AND 49-41-61-000-801/49-41-61-400-801. OPS CK GOOD.
FAILED EMERGENCY LIGHTING SWITCH, OPS CHECK AND BATTERY PACKS FUNCTION CHECK. ACFT GROUNDED. REPLACED BATTERY PACKS.
FAULT LIGHT ILLUMINATED DURING APU START ATTEMPT FL 380. ACFT GROUNDED.
ACCOMPLISHED THREE START ATTEMPTS, EACH ATTEMPT RESULTED IN AUTO SHUTDOWN, HI START EGT AND ILLUMINATED FAULT LIGHT. NOTE APU GROUND OPS NORMAL. ACFT GROUNDED. APU R & R REF T/C 78349010, OPS TEST PASS.
RT CENTER FUEL PUMP ILLUMINATED ON GROUND WITH 20,000 LBS OF FUEL IN TANK. ACFT GROUNDED. ATTEMPTED TO RESET GFI FOR BOOST PUMP. NO HELP. REPLACED THE RT FUEL BOOST PUMP MOTOR IMPELLER IAW AMM 28-22-41-000-801 AND -400-801. INITIALLY NO POWER TO NEW PUMP, PRESSED ON GFI RELAY, POWER RETURNED. GROUND VERIFICATION OPS CHECK OF RT BOOST PUMP IS GOOD. MAINTENANCE CONTROLS REQUESTS REPLACEMENT OF THE RT CTR TANK BOOST PUMP GFI RELAY R55 IN THE P92 PANEL. REPLACED THE R55 RELAY IN THE P92 PANEL, C/W OPS TEST OF THE GFI IAW AMM 28-22-41-720-802. GROUND VERIFICATION IS GOOD
ENGINE 1 SHOWS ECONOMIC FAULT. NR 77-20871 EGT SIGNAL IS OUT OF RANGE. ACFT GROUNDED. ON DEFERRAL.
FMC DISAGREE ILLUMINATED ON FMC SCRATCH PAD. ACFT GROUNDED. FOLLOWED QRH PROCEDURE. ALL SYSTEMS OK.
RT FMC BLANKED OUT IN CRUISE, FMC CDU ANNUNCIATORS FLASHED AND SCREEN SHOWED "BITE TEST", THEN ALL RETURNED TO NORMAL. ALSO DROPPED SID ON DEPARTURE. ACFT GROUNDED. RT FMC TESTED IAW MM 34-61-00 AND NO CURRENT FAULTS. INFLIGHT FAULT PAGE ONLY LOGGED F/O CDU FAULT. F/O'S FMC CDU OPS CK NORMAL. NO HISTORY 30 DAYS.
MCP COURSE INDICATOR ON COPILOT SIDE HAS DIGIT LINE INDICATOR LINE BURNED OUT. ACFT GROUNDED. R & R DFCS MODE CONTROL PANEL IAW AMM 22-11-34-000-801 AND 22-11-34-400-801, OPS CHECKED GOOD. GROUND FUNCTIONAL CHECKED GOOD IAW AMM 22-11-34-740-801. BITE GROUP NR 32, DFCS LRU INTERFACE TEST FOR MCP, AND LAND VERIFY TEST, AMM REF. 22-11-00, ALL PASS.
NR 1 ENGINE CHIP DETECTOR FOUND WITH CONTAMINATION. ACFT GROUNDED. DETERMINED MATERIAL TO BE MAGNETIC M-50 BEARING METAL. TECH SERVICES CONFIRMED AND VERIFIED, INITIATED INVESTIGATION AT STEP 7B, EXAMINE ENGINE STARTER MAG PLUG REF AMM 79-00-00-200-804-F00. PERFORMED INSPECTION OF ENGINE STARTER MAG PLUG, AND FOUND CLEAN. INSPECTED TGB FOR INTERNAL DAMAGE, NO DAMAGE NOTED. REMOVED THE NR 1 ENGINE IAW T/C 78471000. INSTALLED NR 1 ENGINE.
NR 1 ENGINE SPINNER FRONT CONE IS MISSING, OVER 50 PRECENT BLACK ANTI-EROSION PAINT. ACFT GROUNDED. ON DEFERRAL.
RIGHT CTR PUMP FUEL PRESSURE LOW LIGHT ILLUMINATED. ACFT GROUNDED. REPLACED RT CENTER FUEL BOOST PUMP IAW AMM 28-22-41-000-801 & AMM 28-22-41-400-801. OPS CHECK GOOD. LEAK CHECK GOOD.
DURING TAXI OUT, FMC DISAGREE WARNING ILLUMINATED. ACFT GROUNDED. QRH PROCEDURE ACCOMPLISHED, NORMAL. OPS RESTORED ON GROUND.
ON RECALL, CONTROL CABIN ZONE TEMP ILLUMINATED. RESET WITH MASTER CAUTION. ACFT GROUNDED. ACCOMPLISHED BITE TEST ON NR 1 AND NR 2 PACK ZONE TEMP CONTROLLERS, FOUND FAULT LIGHT FOR FLIGHT DECK TRIM VALVE ON NR 2 PACK ZONE TEMP CONTROLLER. IAW MM 21-61-00. OPERATED EACH PACK SEPARATELY AND BOTH PACKS TOGETHER. IN ALL CONFIGURATIONS WAS ABLE TO MODULATE CONTROL CABIN SUPPLY DUCT TEMPERATURE FROM 6-60 DEGREES C, WITH TEMPERATURE STABLE AT AT 24 DEG C IN AUTO WITH MOVEMENT OF TEMP CONTROL KNOB. CONTROL CABIN ZONE TEMP LIGHT DID NOT ILLUMINATE. REACCOMPLISHED BITE OF BOTH PACK, ZONE TEMP CONTROLLERS, NO DEFECTS NOTED. SUSPECT INTERMITTENT FAULT, NO HISTORY LAST 60 DAYS.
CRACK FOUND ON RT HORIZONTAL LOWER SKIN AT STAB, STA 138.7 APPROXIMATELY 6" FROM AFT SPAR. ACFT GROUNDED. REPAIRED RT HORIZONTAL LOWER SKIN AT STAB STA 138.7 IAW SRM 55-10-01-2R-11, REPAIR 11, FIG 204, SHEET 2. THIS REPAIR IS A CAT B REPAIR WITH AND INSPECTION THRESHOLD STARTING 2 56,000 FLIGHT CYCLES AND 9,000 FLIGHT CYCLES INTERVALS IAW SRM 55-10-01-2R-1, FIG 206, TABLE 204. STA RSS 138.7.
LEFT HORIZONTAL STABILIZER LOWER SKIN CRACKED 8" FROM SPAR LT SS 101.9. ACFT GROUNDED. REPAIRED LT HORIZONTAL LOWER SKIN IAW SRM 55-10-01-2R-11, REPAIR II, FIG 204, SHEET 2. THIS REPAIR IS A CAT-B REPAIR WHICH HAS AN INSPECTION THRESHOLD STARTING AT 56,000 FLIGHT CYCLES AFTER REPAIR INSTALLATION AND REPEAT INSPECTIONS AT 9,000 FLIGHT CYCLE INTERNALS, IAW SRM 55-10-01-2R-11, TABLE 204, FIG 206. LEFT STABILIZER STA 101.9.
FMC DISAGREE ON RAMP, ACFT GROUNDED. PERFORMED QRH PROCEDURE, OPS GOOD.
RIGHT COWL VALVE OPEN LIGHT REMAINS ILLUMINATED AFTER BEING TURNED OFF. ACFT GROUNDED. ACCOMPLISHED FIM TASK 30-21-00-810-804. REPLACED INLET COWL THERMAL ANTI-ICE VALVE IAW AMM 30-21-11-401 BEFORE COMPLETION OF STEP I IN TASK 30-21-11-401, FOUND DP1102 REMOVED FROM ENGINE BLEED AIR PRESSURE REGULATOR PLUG HAD COME APART. STEP I IS NOT COMPLETE. REPLACED MW0311 HARNESS, REF AMM 73-21-06-400-802. ACCOMPLISHED BLEED AIR REGULATOR INSTALLATION TEST, TESTED GOOD REF AMM 36-11-03-400-801. ACCOMPLISHED GROUND WING THERMAL ANTI-ICING SOLENOID VALVE TEST, TESTED GOOD REF AMM 30-11-12-710-801. FINISHED INSTALL OF INLET ANTI-ICE VALVE TESTED GOOD NO LEAKS REF AMM 30-21-11-400-801. ACCOMPLISHED FFCC VIBRATION SENSOR POST INSTALLATION TEST. OPS CHECK GOOD. REF MM TASK 73-21-06-400-802-F00, STEP 5.F.(1)(D)3).
NR 1 ENGINE FAN BLADE SHIM WORN. ACFT GROUNDED. R & R FAN BLADE SHIM IAW T/C 78472002.
APU FAULT LIGHT ILLUMINATED ON START NO LIGHTOFF, TWO START ATTEMPTS. ACFT GROUNDED. PERFORMED FIM 49-40, TASK 803, NO FAULTS NOTED. FAULT CORRECTED IAW STEP E.12, D.
SATCOM LOCKUP DURING POWER TRANSFER AFTER ENGINE START. SATCOM SELECTION MISSING ON MCDU MENU PAGE. ACFT GROUNDED. COMPLETED QRH 5.3 SAT PROMPT RESTORED.
DURING DEPARTURE, PRIOR TO TAKEOFF NOTICE MCDU DID NOT SHOW THE SATCOM PROMPT ON MENU PAGE. ACFT GROUNDED. ACCOMPLISHED SATCOM LOCKUP ON GROUND QRH SYSTEM RETURNED TO NORMAL.
APU FAULT 49-7210. ACFT GROUNDED. FOUND BAD DATA MEMORY AND CHANGED IAW MM 49-72-11. FAULT CLEARED. SYSTEM GROUND VERIFICATION ACCOMPLISHED IAW APU BITE MM 49-61-00.
NR 1 ENG EEC FAULT CODE 73-20011 AND 73-20621 WERE PRESENT AFTER SOFTWARE UPLOAD. ACFT GROUNDED. REPLACED NR 1 ENG EEC IAW AMM 73-21-60, OPS CHECKED GOOD.
AUTOPILOT "B" INOPERATIVE IN VERTICAL SPEED MODE. OPERATES NORMALLY IN ALL OTHER MODES. AUTOPILOT "A" OPERATES NORMALLY IN ALL MODES. ACFT GROUNDED. CONFIRMED FAULT, MCP VERTICAL SPEED CH B FAILS MCP INTERACTIVE TESTS MSG 22-11063. ACCOMPLISHED FIM 22-11, TASK 817 AND RECONFIRMED MCP FAULT. REPLACED MCP IAW AMM 22-11-34. ACCOMPLISHED DFCS LRU INTERFACE TESTS, GP 32, IAW AMM 22-11-34/501, DFCS LAND VERIFY TEST (GP 49) IAW AMM 22-11-00/ 201, AND HGS SENSOR TEST IAW SMM 34-36-00, OPS CK NORMAL.
FMC DISAGREE MESSAGE ON GROUND. ACFT GROUNDED. QRH WAS FOLLOWED AND FMC DISAGREE MESSAGE DID NOT REAPPEAR.
FOUND BULLNOSE INTERIOR EMERGENCY SPOTLIGHT AT ROW 18L INOPERATIVE. ACFT GROUNDED. REPLACED THE LAMP FOR 18L BULLNOSE EMERGENCY LIGHT. OPS NORMAL.
DURING CRUISE FLIGHT, THE FMC P/RST LIGHT ILLUMINATED ALONG WITH VTK ON CAPTAINS ND. PERFORMED FMC FAIL CHECKLIST IN QRH AND DETERMINED THAT THE LT FMC FAILED. BEARING/DISTANCE INFORMATION FOR LT FMC DID NOT RETURN. CONTINUED WITH FMC SWITCH BOTH ON "RIGHT". ACFT GROUNDED. PERFORMED FIM 34-61, TASK 836 AND SUCCESSFULLY RESET NR 1 FMC. PERFORMED BITE CHECK IAW FIM TASK 34-61, TASK 801 NO FAULTS NOTED. ACFT OK FOR CONTINUED SERVICE.
ELECTRICAL LIGHT ILLUMINATED ON THE OVERHEAD PANEL AMP METER & VOLT. MASTER CAUTION ON 6 PACK & OVERHEAD. ACFT GROUNDED. ACCOMPLISHED FIM 24-31-00-810-801. SPCU INOPERATIVE FAULT STORED. RAN FIM 24-34 TASK 802. FAULT CLEARED NO HISTORY. GROUND VERIFICATION GOOD.
RIGHT ENGINE "COWL VALVE OPEN" LIGHT STAYED ILLUMINATED AFTER ANTI-ICE WAS TURNED OFF. ACFT GROUNDED. RAN NR 2 RT ENG AND PERFORMED ENG COWL ANTI-ICE OPS TEST IAW AMM 30-21-00-710-80. ALL TESTS NORMAL. NO FAULTS FOUND.
APU HAS A HISTORY OF OIL SERVICING CURRENT OIL CONSUMPTION IS HIGHER THAN EXPECTED GROUNDED. C/W FIM TASK 49-95-00-810-801. FOUND APU TO BE LEAKING FROM AFT DRAIN. FOUND OIL COOLER LEAKING ON SHUTDOWN. REPLACED THE APU OIL COOLER, REF AMM 49-91-41/401. NO LEAKS NOTED DURING APU OPERATION.
MODE CONTROL PANEL IS BLANK. ACFT GROUNDED. CYCLED MCP DC1 AND DC2 CIRCUIT BREAKERS. MCP RETURNED TO NORMAL. NO HISTORY. MODE CONTROL PANEL BITES NORMAL IAW GRP 32-22-11-34/501. LAND VERIFY TESTS NORMAL BITE GRP 49 22-11-00/201. HGS SENSOR TEST NORMAL REF 34-36-00. ACFT REMAINS CAT 3A AUTOLAND AND HGS QUALIFIED, STATUS PLACARD CHECKED. GROUND VERIFICATION SUCCESSFUL.
EMERGENCY LIGHT EXTERIOR SLIDE LIGHT ADJACENT TO LT FORWARD OVERWING EXIT IS INOPERATIVE. ACFT GROUNDED. REPLACED LAMP AND TESTED L1210 OVERWING ESCAPE LIGHT IAW MM 33-51-04-960-801. OPS NORMAL.
LEFT PACK ANNUNCIATION ON MASTER CAUTION RECALL DURING DECENT. ANNUNCIATION EXTINGUISHED ON MASTER CAUTION RESET. ACFT GROUNDED. ACCOMPLISH PACK - ZONE TEMP. CONTROLLER BITE TEST, NR 1 CONTROLLER SHOWS FAULT FOR LT RAM AIR ACTUATOR IAW MM 21-61-00-700-806-002. R & R LEFT RAM AIR ACTUATOR REF MM 21-51-21. OPS CHECKED GOOD.
LAV G LOWER EMERGENCY LIGHT LENS, CRACKED. ACFT GROUNDED.
LEFT PACK LIGHT ILLUMINATED ON RECALL. ACFT GROUNDED. PERFORMED RESET ON CPC NR 1 AND RAN PRESSURIZATION SYS GROUND TEST WITH NO FURTHER FAULTS NOTED IAW AMM 21-31-00-700-802.
BOTH OVERWING FWD LOWER EXIT LIGHTS ARE INOPERATIVE. ACFT GROUNDED. R & R FUSES ON BATTERY PACK IAW AMM 33-51-06. OPS CHECKED GOOD IAW AMM 33-51-06.
STA 727B, SEAT TRACK, LBL 45.50 INBD FLANGE IS CRACKED AT FASTENER HOLE. ACFT GROUNDED. REPAIRED IAW REO G17114, REV A AND EA SB737-53-1296, NG-104.
BS 727B, SEAT TRACK RBL 45.50 INBD AND OTBD FLANGES ARE CRACKED AT FASTENER HOLE. ACFT GROUNDED. REPAIRED IAW REO G17114, REV A AND EA SB737-53-1296-NG-104.
NR 2 ENGINE SPAR VALVE CLOSED LIGHT ILLUMINATED. ENG INDICATES NORMAL. ACFT GROUNDED. GROUND VERIFICATION CHECK PASSES. ACCOMPLISHED MMEL 28-22 RESTORATION FUEL SPAR VALVE CLOSED LIGHT OPS NORMAL. ACCOMPLISHED FIM 28-22, TASK 812 & FIM 28-22, TASK 810 BOTH FIM REPAIR CONFIRMATION TESTS PASSES.
TWICE ON ILS, LOC AND G/S CAPTURED, ACFT NOSED OR PITCHED DOWN EXCESSIVELY. VISUAL CHECK END OF RUNWAY G/S TRANSMITTER WAS NOT BLOCKED, AUTOPILOT. ACFT GROUNDED. C REW VERBAL INFO -A/P DID NOT DISCONNECT ON EITHER TIME. CREW DISCONNECTED A/P. NO FLT FAULTS LOGGED EITHER FCC A OR FCC B. PERFORMED ILS, SYSTEM TEST W/IFR-4000 AND PERFORMED LAND VERIFY BITE NR 49. FCC A PASS, FCC B DID NOT PASS DUE TO SPOIL 4 POSITION, SENSOR 2 FAULT. PERFORMED FIM 22-12, TASK 801. SPARE FCC USED FOR TROUBLESHOOTING. NO HELP REINSTALLED ORIGINAL FCC B. ADJUSTED NR 4 SPOILER SENSOR. LAND VERIFY TEST NOW PASS. INSTALLATION TEST FOR FCC GOOD REF AMM 22-11-33. DFCS A PASS LAND VERIFY TEST ILS SYS GOOD REF 34-31-00. NO HISTORY LAST 90 DAYS. ACFT WILL SHOW CAT IIIA HGS ONLY -STATUS SCREW SAME.
HF NR 1 RADIO DOES NOT TRANSMIT. AIRCRAFT GROUNDED. ACCOMPLISHED FIM 23-11 TASK 806. MADE SUCCESSFUL HF NR 1 PLANE TO PLANE AND TRANSMIT AND RECEIVE COMMUNICATIONS FROM BOTH CAPT AND F/O POSITIONS. OPS NORMAL. HF 1 TRANSCEIVER BITE CHECKED NORMAL REF FIM 23-11, TASK 801.
NR 2 ENGINE WOULD NOT START WITH IGNITION IN LT OR RT POSITION. EGT WOULD GO NO HIGHER THAN 180 DEG. HUNG START. ACFT GROUNDED. ACCOMPLISHED FIM TASK 73-00-801, NO FAULTS FOUND. IAW FIM TASK 80-05-806 PERFORMED GVI OF NR 2 ENGINE, NO DEFECTS NOTED. STARTED NR 2 ENGINE NORMAL, NO FURTHER DEFECTS NOTED. NO HISTORY FOR 30 DAYS.
APU BITE TEST INOPERATIVE, CHECK APU OR ECU INTERFACE MESSAGE DISPLAYED ON CDU. ACFT GROUNDED. CYCLED ACFT POWER, APU BITE BACK TO NORMAL. ACCOMPLISHED APU CURRENT STATUS CHECK & NO FAULTS IN HISTORY. CHECKED NORMAL IAW 49-61-00. NO HISTORY 30 DAYS & SEAM C.
DURING T/C 7823307, EMERGENCY LIGHT BATTERY PACKS FAILED OPS CHECK. ACFT GROUNDED. R & R BATTERY PACK IAW MM 33-51-06.
ON RECALL, CONT CABIN ZONE TEMP LIGHT ILLUMIINATED. RAN QRC AND LIGHT STAYED ON. ACFT GROUNDED. FLT DECK TRIM VALVE FAULT NR 2 ZONE TEMP CONTROLLER. RESET AND TESTS NORMAL IAW FIM 21-61, TASK 801. GROUND VERIFICATION SUCCESSFUL.
AFCS SYS A ENGAGE INTERLINK CIRCUIT BREAKER FOUND TRIPPED. ACFT GROUNDED.
NR 1 ENGINE INLET SPINNER FRONT CONE MISSING PAINT AND ANODIZED COATING. ACFT GROUNDED. NR 1 ENGINE R & R INLET SPINNER FRONT CONE IAW TC 78472002.
NR 1 ENGINE, TWENTY FOUR FAN BLADE SHIMS WORN. ACFT GROUNDED. R & R SHIMS IAW T/C 78472002.
FMC DISAGREE. ACFT GROUNDED. ACCOMPLISHED FMC DISAGREE CHECKLIST 11.2. OPS NORMAL.
RT ENG VALVE LT - CAME ON DURING FLIGHT (BRIGHT). ACFT GROUNDED. RAN NR2 ENG, ENG VALVE LT FLICKERED THEN WENT OUT, RANG OUT SW DP1207 ON HMU. FOUND HPSOV SW TO BE BAD WDM 76-21-21. REPLACED NR 2 ENG HPSOV SW REF MM 73-21-09. OPS CK GOOD GROUND VERIFICATION SUCCESSFUL.
OVERHEAT DETECTOR FAULT LIGHT ENGINE NR 2. ACFT GROUNDED. REPAIRED BROKEN TERMINAL MW0326. REF SWPM20-30-11, WDM26-11-11, AMM 26-11-00. GROUND VERIFICATION SUCCESSFUL.
FOS NR 2 WINDOW FELL OFF WHEN TRYING TO CLOSE. ACFT GROUNDED. REINSTALLED NR 2 FOS SLIDING WINDOW REF MM 56-12-11. OPS NORMAL, OK FOR SERVICE.
ZONE TEMP CONT CAB ILLUMINATED ON RECALL. ACFT GROUNDED. TESTED RT PACK/ZONE CONTROLLER IAW FIM 21-62, TASK 801. FOUND A FAULT LIGHT FOR THE CONTROL CABIN TEMP VALVE. RESET PACK/ZONE CONTROLLER AND RETESTED 3 TIMES. NO FURTHER FAULT INDICATED. ALSO, DID NOT FIND ANY MX HISTORY WITHIN THE PAST 30 DAYS.
RIGHT PACK AND MASTER CAUTION LIGHTS ILLUMINATED ON CLIMBOUT (APPROX 11,000). PERFORMED QRH PROCEDURE - SELECTED WARMER TEMP. PACK RESET OK. NO FAULTS LOGGED ON ZONE TEMP CONT, HOWEVER NOTICED RT RAM AIR DEFLECTOR DOOR REMAINS DEPLOYED DURING CYCLE/TEST. FOUND MODULATION PANELS & RAM AIR ACTUATOR OPERATE NORMAL. LUBRICATED DEFLECTOR DOOR PIANO HINGE & LINKAGE POINTS ON LT & RT SIDES. GROUND VERIFICATION PASS, ZONE TEMP BITE GOOD REF 21-61-00. SYS OPS NORMAL. REPLACED RT RAM-AIR ACTUATOR IAW AMM 21-51-21-000-801/-400-801 AS A PRECAUTIONARY MEASURE. OPS AND BITE CK GOOD. NO FURTHER DEFECTS NOTED.
ON CLIMB OUT, RT PACK TRIPPED, RESET PACK IAW QRH. RT PACK TRIPPED A SECOND TIME AND REMAINED OFF FOR THE REMAINDER OF FLIGHT IAW QRH. UNABLE TO DUPLICATE.
ON DESCENT AT 6000 FT, THE IMBALANCE LIGHT ILLUMINATED. FUEL STATE WAS 7.62 LT MAIN, 5.56 CTR, 8.62 RT MAIN. CROSSFEED TO BALANCE WORKED. NO LOW PRESSURE BOOST PUMP LIGHTS ILLUMINATED. REMOVED ICE AND RESIDUAL WATER FROM NR 2 FUEL TANK. R & R NR 2 F/Q COMPENSATOR UNIT REF AMM 28-41-21-000-804/-400-801. NR 2 FUEL QTY OPS NORMAL REF MM 28-41-00-730-801.
WHILE CLIMBING THROUGH HIGH 20S AT 3201/.792 COST INDEX 45, FUEL HAD DEVELOPED A 600 LBS IMBALANCE WITH LT SIDE HEAVY. TURNED LT CENTER PUMP OFF, CROSSFEED CLOSED AND ALL OTHER BOOST PUMPS ON. ABOUT 4 MINUTES LATER AT ABOUT 33,000 LEFT ENGINE VARIED AT MODERATE RATE FROM 101 TO 87. SLOW RETARD TO 86 SETTLED ENG NR 1 AND IT RAN FINE FOR REST OF FLIGHT. -PERFORMED NR 1 ENG EXCEEDANCE FIM TASK 71-00-00-740-801, NO ENGINE EXCEEDANCES NOTED. PERFORMED NR 1 EEC BITE FIM TASK 73-00 TASK 801 FOUND FAULT CODE 73-20331 THE FMV DEMAND AND POSITION SIGNALS DISAGREE. PULLED PCMCIA CARD DOWN LOADED TO DOWNLOADED DATA & REINSTALLED PCMCIA CARD HMU. R & R NR 1 HMU IAW EA 800-73EA-09873. EA 800-73EA-09873 COMPLIED WITH.
RADAR CONTROL PANEL CRACKED AROUIND IDNT BUTTON. REPLACED RADAR CONTROL PANEL, REF M/M 34-43-91. TESTS NORMAL.
ON CLIMBOUT, RT PACK LIGHT ILLUMINATED. FOLLOWED QRH AND LIGHT RESET WITH THE TRIP RESET BUTTON. OPERATED NORMALLY THEREAFTER. ACCOMPLISHED FIM TASK 21-52, TASK 821. PACK OPERATES NORMAL. PACK OPERATED NORMALLY THROUGHOUT FLIGHT, SUCCESFUL GROUND VERIFICATION.
WEATHER RADAR SPOKING IN ALL MODES. ACCOMPLISHED WEATHER RADAR SYS, OPS TEST. NO DEFECT. GROUND VERIFICATION SUCCESSFUL. REF AMM 34-43-00-710-802-001.
ON SHUTDOWN, AMBER SPEED TRIM FAIL ANNUNCIATOR ILLUMINATED. AFTER CREW REALIGNED IRUS, SPEED TRIM LIGHT WENT OFF. PERFROMED DFCS BITE IAW SIM 22-11, TASK 801 AND FIM 22-13, TASK 817. NO DEFECTS NOTED. PERFORMED STAB/SPEED TRIM BITE TEST 14 WITH NO FAULTS FOUND. ACFT OK FOR SERVICE.
AFTER STARTING TAXI RECEIVED FMC DISAGREE LIGHT. PERFORMED QRH CHECK LIST. FAULT CLEARED.
AUTOLAND APPROACH WARNING IN FLARE & LINED UP 20 TO THE RT OF CENTERLINE. HEADINGS FFR SHOWED RADAR ALTIMETER INVALID FOR LAST FLT, DFCS RECORDED NO FAULT. PERFORMED LAND VERIFY AND HGS SYS TEST REF MM 22-00-01-730-801 ALL TEST PASSED.
FMC DISAGREE ANNUNCIATED. ACFT GROUNDED. PULLED AND RESET FMSC CMPTR 1 &2 CIRCUIT BREAKERS IAW QRH FMC DISAGREE CHECKLIST PROCEDURE.
FMC DISAGREE MESSAGE DISPLAYED. ACFT GROUNDED. ACCOMPLISHED QRH PROCEDURE AND FMC DISAGREE MESSAGE NO LONGER DISPLAYED. BOTH SYSTEMS OPS CHECKED GOOD IAW AMM 34-61-00.
ON TAXI OUT GOT FMC DISAGREE MESSAGE. ACFT GROUNDED. RESET SUCCESSFUL IAW FMC/QRH PROCEDURES. OPS NORMAL.
FMC DISAGREE MESSAGE DISPLAYED AFTER ENGINE START. QRH PROCEDURE ACCOMPLISHED. MESSAGE CLEARED.
OVERHEAD EXIT SIGN NEAR ROW 16 FELL OFF. FOUND EXIT LENS OFF SECURED LENS BY SNAPPING ONTO RETAINING TABS . TABS FULLY ENGAGED IN HOLES. LIGHT OPS CHECKED GOOD.
SPAR VALVE CLOSED LIGHT ILLUMINATED BRIGHT BLUE. QRH PROCEDURE ACCOMPLISHED LIGHT REMAINS ON WITH START LEVER IN IDLE POSITION. SYS REPORTED IS NR 1 SIDE AND THERE WERE NO OTHER PROBLEMS NR1 ENGINE RAN FINE IAW PILOT PASS DOWN.) ACFT GROUNDED. WHEN ACCOMPLISHING FIM 28-22-00-810-809, THE SYSTEM WORKED FINE. THE FIM STATES TO CHANGE THE SPAR VALVE ACTUATOR IN THIS TYPE OF SITUATION. REPLACED SPAR VALVE ACTUATOR IAW AMM 28-22-11-000-804 AND AMM 28-22-11-400-804 GROUND FUNCTIONAL CHECK GOOD IAW AMM 28-22-00-710-801.
NR 2 CSD DRIVE LIGHT ILLUMINATED WHILE AT GATE AND NR 1 CSD DRIVE LIGHT NOT ILLUMINATED. CONFIRMED NR 1 ENGINE DRIVE LIGHT DOES NOT ILLUMINATE WITH ENGINE OFF. LIGHT DOES PRESS TO TEST. CHARGE PRESSURE SWITCH IN IDG IS READING OPEN THROUGH PINS 5/6 OF DP1206, SHOULD BE CLOSED. VERFIED USING SRM 24-11-11 AND READING NR 2 IDG SWITCH STATUS, ITS CLOSED AS SHOULD BE. REMOVED NR 1 IDG, INSTALLED SERVICEABLE IDG, OPS AND LEAK CHECKED GOOD REF MM 24-11-11, PB401.
RADAR TILT SEEMS TO SLOWLY DRIFT DOWN AFTER ABOUT 10 MINUTES OF USE. TILT UP HAS LITTLE EFFECT ON TOTALLY GREEN SCREEN IE +5 AT FL 380 IN CLEAR SCREEN. ALL GREEN TILT ON OR OFF WX T MAP NO CHANGE TURNING RADAR OFF FOR 5 MINS THEN ON. RADAR WILL WORK AGAIN BUT SLOWLY, TURNS GREEN AGAIN. ACFT GROUNDED. PERFORMED FIM 34-43, TASK 814, WEATHER RADAR SYS OPS TEST CHECKED GOOD WITH NO FAULTS. REPLACED WEATHER RADAR TRANSCEIVER REF 34-43-41. GROUND VERIFICATION TEST GOOD REF 34-43-41 & 34-43-00 WEATHER RADAR SYS OPS TEST.
AFTER PUSH BACK AND INITIAL TAXI, FMC DISAGREE ILLUMINATED. ACFT GROUNDED. ACCOMPLISHED QRH PROCEDURE. OPS NORMAL.
WEATHER RADAR UNRELIABLE. WORKS NORMALLY FOR A WHILE THEN PAINTS SOLID GROUND CONTACT FOR 320 NM (IN RANGE REGARDLESS OF TILT POSITION) THEN CYCLES BACK TO NORMAL OPERATION. COULD NOT DUPLICATE. OPS CHECKED NORMAL AND GROUND CLUTTER SUPPERSSION TEST REF MM 34-43-00 GROUND VERIFICATION TEST SUCCESSFUL.
R1 DOOR HANDLE BINDS WHEN CLOSING. ACFT GROUNDED. ADJUSTED GUIDE ARM IAW MM 52-41-00.
L2 WINDOW HANDLE BINDS WHEN CLOSING. ACFT GROUNDED. CLEANED L2 WINDOW TRACKS IAW SOPM 20-30-03. LUBED L2 WINDOW TRACKS IAW NG AMM 12-25-81-600-801. OPS CHECK OF L2 WINDOW GOOD IAW AMM 56-12-11-710-803.
FUSELAGE SKIN GOUGED BETWEEN STA 727G - 727F AT STRINGER 23 LEFT. ACFT GROUNDED. FOUND GOUGE TO BE OUT OF LIMITS IAW SRM 53-00-01. REMOVED AFT CARGO COMPARTMENT LT SIDEWALL PANEL IAW NG AMM 25-52-06-000-801. REMOVED DAMAGED AREA OF SKIN FABRICATED 1 EA REPAIR DOUBLER AND 3 EA FILLERS IAW SRM 53-00-01, REPAIR 12, FIG 201. ALODINE AND PRIMED ALL REPAIRS PARTS IAW SRM 52-20-01 AND INSTALLED DOUBLER AND FILLERS IAW SRM 53-00-01, REPAIR 12, FIG 201. REINSTALLED LT SIDEWALL PANEL IAW NG AMM 25-52-06-400-801.
FORWARD CARGO PIT AFT FLOORBEAM CORRODED SEVERAL LOCATIONS. ACFT GROUNDED. R & R IAW SRM 51-40-05.
FWD CARGO PIT AFT FLOOR ATTACH ANGLE CORRODED, SERVERAL LOCATIONS. R & R IAW SRM 51-40-005.
RT SIDE WINDOW HEAT, OVERHEAT LIGHT ILLUMINATED ON APPROACH. ACCOMPLISHED QRH PROCEDURE AND LIGHT REMAINED EXTINGUISHED. GROUNDED. DUE TO UNIT HISTORY ENGINEERING REQUESTS REPLACEMENT OF WCHU. REPLACED RT SIDE WINDOW HEAT CONTROL UNIT. OPS CHECKED GOOD, REF AMM 30-41-11.
RT WINDOW (F/O SLIDER) OVERHEAT LIGHT ILLUMINATED FL 270 ON ARRIVAL/APPROACH. ACCOMPLISHED QRH PROCEDURE. LIGHT ILLUMINATED AGAIN ON TAXI IN. GROUNDED. ACCOMPLISHED FIM TASK 30-41-00-810-801. PERFORMED WHCU BIT PROCEDURE. INTERMITTENT FAULTS. NO FAULTS NOTED. NO HISTORY NOTED. COULD NOT DUPLICATE FAULTS.
SPEED CONTROL WOULD GO FROM SLOW & THE THROTTLES WOULDN'T INCREASE. MANUALLY MOVEED THOTTLES. SPEED WOULD GO TOO FAST AND HAD TO MANUALLY MOVE THROTTLES BACK. HAPPENED IN VPATH AND LEVEL CHANGE. MAINLY HAPPENED IN DESCENT. NOT AS BAD IN THE CLIMB. AUTOTHROTTLES NO FAULTS. PERFORMED AUTOTHROTTLE CURRENT STATUS TEST SERVO MOTOR TEST AND TORQUE TEST PER FIM 22-31-00-810-801 ALL TESTS PASSED. AOA VANE DATA SHOWED VANE DIFF WITHIN LIMITS. ADIRU NO FAULTS PER FIM 34-21-00-810-801. PERFORMED DFCS GROUP NR 10 (CURRENT STATUS) NR 11 (A/P) NR 12 (FD) NR 14 (SPEED TRIM) AND NR 49 (LAND VERIFY) TESTS PER MM 22-11-00. ALL TESTS PASS. ALSO PERFORMED HGS FAULT REVIEW AND HGS SYS TEST PER HGS SMM 34-36-00, ALL TESTS PASSED.
NR 2 ENGINE HARNESS MW0316 IS CHAFED ONE INCH FROM TERMINAL LUG AT CONNECTION TO UPPER FAN FIRE DETECTOR ASSY. REMOVED HARNESS IAW MM 26 11 02 000 801. INST HARNESS IAW MM 22 11 02 400 801. OPS CHECK NORMAL REF MM 26 11 00 710 801.
AT FL 260 LEFT SIDE WINDOW "OVERHEAT" LIGHT ILLUMINATED FOLLOWED BY ELECTRICAL ARCING ON L2 WINDOW FOLLOWED BY L2 CRACKING OUTER PANE. DIVERSION TIME: 2 HOURS. REPLACED LT NR 2 SLIDING WINDOW PER AMM 56 12 11 400 801, OPERATION CHECK NORMAL.
RIGHT PACK LIGHT ILLUMINATES ON RECALL. EXTINGUISHES WITH MASTER CAUTION RESET. PERFORMED PACK ZONE TEMP CONTROLLER BITE. FAULTED RAM AIR ACT. VERIFY TEST PASS FAULT RESET REF FIM 21 62 00 810 836.
LEFT PACK LIGHT ILLUMINATED ON GROUND. ACCOMPLISHED BITE PROCEDURE ON PACK/ZONE TEMP CONTROLLERS. A TCV FAULT SHOWED ON THE NR 1 TEMP CONTROLLER. FAULT CLEARED & TEMP CONTROLLERS SHOW NO NEW FAULTS. GROUND VERIFIED BY RUNNING APU & A/C PACKS. NO FAULTS INDICATED OKAY FOR CONT BITE PROCEDURE REF FIM TASK 21 62 00 810 801.
ON RECALL RT PACK LIGHT ILLUMINATES LIGHT RESETS DURING MC RESET. PERFORMED PACK/ZONE TEMP CONTROLLER BITE TEST. NO FAULTS LOGGED. REF AMM 21 61 00 700 806 002.
RADAR SPOKES INTERMITTENTLY ALL QUADRANTS/RANGES/TILTS. CONFIRMED RADAR SPOKES. VERIFIED RECEIVER/TRANSMITTER COOL FAN OPERATES PER AMM 34 43 41 400 801 FAN CIRCULATES NORMAL. REPLACED RADAR RECEIVER/TRANSMITTER PER AMM 34 43 41 400 801. PERFORMED RADAR SYSTEM OPERATIONAL TEST PER AMM 34 43 00 710 802 001. WEATHER RADAR OPERATIONAL TEST SUCCESSFUL.
AFTER PUSHBACK FMC DISAGREE MESSAGE. PERFORMED PROCEDURE IN THE QRH. FMC OPERATION RESTORED.
AFTER ENGINE START FWD WINDOW HEAT "OVERHEAT" LIGHT CAME ON. REFERRED TO QRH AND TURNED SWITCH OFF AND WAITED 2 MINUTES. PLACED SWITCH BACK ON AND OVERHEAT LIGHT CAME BACK ON. ACCOMPLISHED FIM 30 41 TASK 801. WINDOW SENSOR FAULT ILLUMINATED LAST SEVERAL LEGS. SELECTED ALT SENSOR ON S1079 WINDOW (R1 WINDOW) HEAT OP TEST GOOD PER MM 30 41 00. GROUND VERIFICATION SUCCESSFUL.
WINDOW HEAT OVERHEAT LIGHT ILLUMINATED. PERFORMED BITE TEST OF WINDOW HEAT CONTROL PER FIM 30 41 00 810 801, NO FAULTS FOUND.
AUTO FAIL AND ALTN LIGHTS ON PRESSURIZATION PANEL. VERIFIED AUTO FAIL AND ALTN LIGHTS ON. LIGHTS EXTINGUISHED BY SELECTING MANUAL AND RETURNING TO AUTO. GROUND VERIFICATION NORMAL BOTH PRESSURE CONTROLLERS OK FOR SERVICE REF MM 21 31 0.
CONTROL CABIN ZONE TEMP LIGHT ILLUMINATED ON TAXI OUT. PACK/ZONE TEMP CONTROLLERS PASS BITE PROCEDURE. OPENED A/C ZONE TEMP VALVE FAN CONT FLT DECK (B3 ON P6 4 PANEL). CLEANED FLIGHT DECK TEMP SENSOR. OPERATED AIR CONDITIONING SYSTEM. ZONE TEMP LIGHT NEVER CAME ON. REF AMM 21 61 06 000 801 FIM 21 62 00 810 842 FIM 21 62 00 810 801.
ON CLIMBOUT NOTICED APU MAINT LIGHT ON. C/W APU BITE PROCEDURE PER AMM 49 60 00 810 801. FAULT CODE 49 91227 LOW OIL QUANTITY LOGGED. SERVICED 2 QTS OF OIL IN APU. REF 12 13 31 FAULT CLEARED FROM CURRENT STATUS APU OPS NORMAL. TSR ISSUED DUE TO HISTORY OF HIGH OIL CONSUMPTION. REPLACED APU REF T/C 78349010. LEAK AND OPS CHECK NORMAL.
AFTER LANDING IN PDX SHUTDOWN NR 2 ENGINE. NEEDED TO RESTART NR 2 AND DID NOT GET A START VALVE OPEN LIGHT. PERFORMED FIM TASK 80 07 00 810 803 F00 INST JUMPER BETWEEN PINS 9 & 5 ON DP1202. MOVED START SWITCH TO GND & START VLV OPEN INDICATES ON CDS. REPLACED NR 2 ENG START VALVE PER AMM 80 11 03 400 801 F00. PERFORMED INSTALLATION TEST PER AMM 71 00 00 800 811 F00 TEST 1 NO LEAKS NOTED & OPS NORMAL.
APU OIL CONSUMPTION CONTINUES TO BE HIGHER THAN EXPECTED CURRENT CONSUMPTION. TSR ISSUED. REPLACED APU OIL COOLER REF MM 49 91 41 400 801. LEAK AND OPS CHECK GOOD.
FOUND METAL SHAVINGS ON THE AFT SUMP MAGNETIC CHIP DETECTOR FOR THE NR 2 ENG. NON MAGNETIC. MATERIAL IS NON MAGNETIC OR METALLIC HAIR LIKE DEBRIS. OK FOR CONTINUED SERVICE REF MM 79-00-00-200-804-F00, STEP F (7) (K). REPLACED NR 2 ENGINE REF T/C 78471000.
IDG DRIVE ANNC INOP. REPLACED 1 ENG IDG PER MM 24 11 11 000 801 AND 24 11 11 400 801. LEAK AND OPS CHECK GOOD.
DURING PREFLIGHT FOUND OPEN C/B ON P18 2 (B 10) "FMCS BITE DC". RESET C/B PER MM 20 60 01 REF WDM 34 61 22. TESTED FMC REF MM 34 61 00 710 801. TESTS OK. SUCESSFUL GROUND VERIFICATION.
DURING ENG FIRE TEST LIGHTS IN FIRE SWITCH HANDLE NR 2 FAILED TO ILLUMINATE. PERFORMED ENG/APU FIRE DET CONT MODULE BITE TEST PER FIM 26 10 TASK 801. FAULTED NR 2 ENG LOOP B UPPER FAN DETECTOR. FOUND WIRE AT UPPER FAN DET BROKEN OFF TERMINAL. RE-TERMINATED PER SWPD 20 30 11 WDM 26 11 21 AND 26 11 11. ENG FIRE DETECTOR OPS TEST NML PER AMM 26 11 00 710 801.
NR 2 HF RADIO WILL NOT TRANSMIT MIC WILL EITHER NOT CYCLE OR RADIO STICKS IN TUNING MODE WITH A CONTINOUS TUNNING TONE. MUST CYCLE TRANSMIT SWX TO STOP. CONFIRMED FAULT. REPLACED NR 2 HF TRANSCEIVER PER AMM 23 11 21 400 801. GROUND SYSTEM VERIFICATION CHECK GOOD. ACFT OK FOR SERVICE.
F/O OUTER WINDOW FRACTURED. F/O NOTED ARCING ON UPPER RT FRAME FOLLOWED BY FRACTURE. ACCOMPLISHED CHECKLIST. NO FURTHER DETERIORATION. REMOVED AND REPLACED R FRONT WINDOW CONTROLLER PER MM 30-41-11. REPLACED F/O'S NR 1 WINDOW PER MM 56-11-11. WINDOW HEAT CONTROLLER OPS CHECK GOOD PER MM 30-41-11.
RT BLEED TRIP OFF ILLUMINATED AT START OF DESCENT, QRH ACCOMPLISHED LIGHT EXTINGUISHED. FOUND EXPOSED WIRE ON BLEED AIR REG. REPLACED RT BLEED AIR REG. PERFORMED CHECK OF PRECOOLER SYSTEM REF MM 36 12 00 700 801, PRECOOLER VALVE TEST FAILED. CONTINUED W/ CHECK OF PRSOV & HIGH STAGE VALVE & HIGH STAGE REG REF AMM 36 11 00 700 801 HIGH STAGE REG FAILED STEPS 12 & 16 ON PAGE 8 OF 23. REPLACED RT PRECOOLER CONTROL VALVE IAW AMM 36 12 02 000 801 & 36 12 02 400 801. REPLACED RT HIGH STAGE REG IAW AMM 36 11 07 000 801 & 36 11 07 400 801. PERFORMED ENG BLEED AIR SYSTEM HEALTH CHECK IAW 36 11 00 700 801. FOR THE HIGH STAGE REG & IT PASSED. PERFORMED PRECOOLER CONTROL VALVE SYSTEM HEALTH CHECK IAW AMM 36 12 00 700 801 & IT PASSED. VERIFICATION FLIGHT SUCCESSFUL.
LEFT FMC L 6 BUTTON STUCK DOES NOT RESPOND TO SELECTED INPUTS. REPLACED CAPT'S FMCS CDU PER AMM34 61 01, OPS CHECK NML.
AUTOLAND UNSAT AIRCRAFT LINED UP WITH LEFT SIDE OF APPROACH END OF RUNWAY AND WANTED TO DRIFT FURTHER LEFT. TOUCHDOWN HOWEVER WAS IN TOUCHDOWN ZONE. ACCOMPLISHED DFCS LAND VERIFY GP49 TESTS REF AMM22 11 00 OPS CHECK NML. PER NEW PROCESS CHECKED FOR REPETITIVE & CHRONIC HISTORY LAST 10 DAYS NO HISTORY.
PILOT REPORTS FIRE DECTECTION TEST WILL NOT ILLUMINATE T HANDLE FOR ENGINE NR 2 IN LOOP B. FOUND WIRE BROKEN INSIDE TERMINAL AT ENG FAN UPPER LOOP B/2 WIRE MW0316. CRIMPED NEW TERMINAL END TO WIRE MW0316 PER SWPM 20 30 11. ENG 2 FIRE LOOP B TESTS GOOD.
WHILE IN E & E BAY FOUND FAULT LOGGED ON ENGINE/APU FIRE DETECTION UNIT FOR NR 2 ENGINE UPPER FAN LOOP B DETECTOR. CLEANED TERMINAL CONNECTIONS TO THE NR 2 ENGINE UPPER FAN FIRE DETECTOR ASSY AND PERFORMED ENGINE FIRE DETECTION OPERATIONAL TEST REF MM 26 11 00 OPS NORMAL. NO FAULTS NOTED.
FMC DISAGREE ON TAXI OUT. RESET CB AS PER QRH PROCEDURE. FMC DISAGREE EXTINGUISHED.
RIGHT FMC INOP WITH " VTK" FLAG. VERIFIED DISCREP WITH FMC 2 C/B'S IN NR 2 FMC LRU GREEN "POWER ON AND FMC VALID" LIGHTS NOT ILLUMINATED. FMC CDU'S SHOW FMC RIGHT BITE INOP. REPLACED NR 2 FMC COMP REF MM 34-61-02. PERFORMED FMC CROSS LOAD REF 34-61-00. OPS NORMAL REF SAME MM AND 34-61-00 FMCS OPERATIONAL TEST.
THE "ELEC" LIGHT ON OVERHEAD PANEL ILLUMINATED. ELEC PANEL SHOWED "AUX CHARGER BATT FAULT" INSP AUX BAT CHARGER CONNECTIONS FOUND NO DISCREPANCIES. RESET THE SYSTEM PERFORMED AMM TASK 24 31 31 710 801 AUX BAT CHARGER OPS TEST. GRN VERIFICATION NORMAL.
THE "STAB OUT OF TRIM" LIGHT ILLUMINATED WITH AUTOPILOT ON. MAIN ELECTRIC TRIM WORKS NORMAL. FCC B RECORDED TWO OCCURRENCES OF FAULT CODE 22 11830 "ELEVATOR AUTHORITY LIMITED". PERFORMED DFCS GROUP NR 1 (CURRENT STATUS) NR 11 (AUTOPILOT) AND NR 49 LAND VERIFY TESTS PER MM 22 11 00 AND HGS SYSTEM TEST PER HGS SMM 34 36 00 ALL TESTS PASS. A/C APPROACH SURVEY COMPLETED.
GENERATOR DISCONNECT NR 2 DRIVE LIGHT NOT WORKING. BULB CHECKS GOOD. REMOVED AND REPLACED NR 2 ENG IDG IAW AMM 24-11-11-400-801. OPS CHECK GOOD PER AMM 24-11-00.
ON MASTER CAUTION RECALL CONT CAB ZONE TEMP CAUTION LT ILLUMINATED. NR 2 CTRLR SHOWS "FLT DECK TRIM VALVE" FAULT ON BIT & PREV FLT TESTS. VERIFY TEST GO. RESET FAULT. FAULT DID NOT RETURN. INTERMITTENT FAULT. BITE TEST NR 2 CTRLR GOOD. GND VERIFICATION GOOD. REF FIM 21 62 T832 & 21 62 T801.
DESCENDING THROUGH 5000 FEET SOUR "DIRTY SOCKS" SMELL PRESENT IN FLT DECK. CONFIRMED APU IS THE SOURCE OF CABIN ODOR REF TASK 05 60 00 280 801C1. ALSO RAN BOTH PACKS WITH BOTH ENGINES. SMELL ONLY RETURNED WHEN APU WAS SELECTED. REMOVED AND REPLACED APU PER MM 49 11 00 400 803 AND TC 78349010. ACCOMPLISHED EA 800 05EA 04407. NO ODORS NOTED.
NR 2 ENG COWL VALVE OPEN LIGHT REMAINED BRIGHT BLUE AFTER COMMANDED ON. ASSOCIATED AMBER TAI WARNING ON CTR DISPLAY. REPLACED WITH SERVICEABLE COWL ANTI ICE VALVE REF AMM 30 21 11 400 801. RAN ENGINES PROBLEM STILL EXISTS SUSPECT OVERHEAD MODULE. REPLACED P5 OVERHEAD PANEL 30 11 41 PERFORMED OPS CHECK PER AMM 30 11 41 710 801 PROBLEM STILL PERSIST. OPERATIONAL CHECK VALVE OPS NORMAL ASSOCIATED LIGHTS ARE INDICATION ONLY. AIRCRAFT RELEASED FOR FERRY FLIGHT TO ANC PER FERRY PERMIT DATED 11 27 2010 TO ACCOMPLISH REPAIR TO NR 2 ENGINE ANTI ICE INDICATION SYSTEM. REPLACED NR 2 ENGINE TAI VALVE. REF MM 30 21 11 400 801. PERFORMED ENGINE COWL ANTI ICING OPERATIONAL TEST. NO FAULTS FOUND.
MAIN FUEL TANK NR 2 / AFT "LOW PRESSURE" LIGHT ILLUMINATED C/B CHECKED IN. FOLLOWED QRC AFT FUEL PUMP OFF. "LOW PRESSURE" LIGHT STILL ILLUMINATED (WITH 8.00 FUEL INDICATION). RANG OUT INTERNAL WIRING OF NR 2 AFT PUMP RANG BAD WDM 28 23 11. REMOVED AND REPLACED NR 2 AFT BOOST PUMP IMPELLER OP. LEAK CHECK GOOD REF AMM 28 22 41 400 801 AND 28 22 41 710 801.
CROSSFEED VALVE CB OPEN. ACCOMPLISHED C/B RESET PROCEDURE PER AMM 20 60 01 CB DID NOT REMAIN SET. REMOVED & REPLACED FUEL CROSSFEED VALVE ACTUATOR ASSY PER AMM 28 22 21. ACFT OK FOR SERVICE.
PRIOR TO LANDING ON SHORT FINAL FUEL CROSSFEED "VALVE OPEN" BLUE LIGHT FLICKED BRIGHT BLUE. ON TAXI IN LIGHT FLICKERED ALSO. CROSSFEED SEL CLOSED. PERFORMED FIM TASK 28 22 00 810 807 A/C CHECKS GOOD CROSS FEED VALVE OPS CHECKS GOOD ON GROUND. VERIFICATION FLIGHT SUCCESSFUL.
DURING ACCOMPLISHMENT OF NR 2 ENG FAN LUBE DETERMINED BLADE SHIMS PRESSURE FACE COATNG WORN. REMOVED AND REPLACED 24 EA BLADE SHIMS PER T/C 78472002.
"FMC DISAGREE" WARNING ON THE GROUND IN OGG. RAN THROUGH THE QRH CHECKLIST OF RESETTING C/B'S. "FMC DISAGREE" WARNING WENT AWAY.
NR 2 IDG HAS RECENT HISTORY OF FREQUENT SERVICING. REPLACED THE NR 2 ENGINE IDG REF MM 24 11 11. ALL OPS AND LEAK CHECKS GOOD. OK FOR SERVICE.
ON CLIMBOUT ABOUT 18,000 FT MSL LEFT DUCT PRESSURE 42 PSI RIGHT 42 PSI, ON LEVEL OFF LEFT 42 PSI RIGHT 12 PSI AT 41 000 FT. REPLACED THE NR 2 ENG HIGH STAGE VALVE REF MM 36 11 06 000 801 AND 36 11 06 400 801 STEP E THROUGH H. (2) OPS CHECK GOOD. REPLACED THE NR 2 ENG PRECOOLER CONTROL VALVE REF MM 36 12 02 000 801 AND 36 12 02 400 801 STEP F THROUGH H. (2) OPS CHECK GOOD. ACCOMPLISHED FIM 36 10 00 810 804, OPS CHECK GOOD.
DUCT SPLIT ON CLIMBOUT. CLIMBING THROUGH FL360 RT SIDE 20 PSI LT SIDE 42 PSI. N1'S 100.9 N2'S 97.1 OAT 49C. DURING THE HEALTH CHECK THE HIGH STAGE REGULATOR FAILED THE OVERPRESSURE FUNCTION AND BACKFLOW TESTS. REPLACED NR 2 ENG HIGH STAGE REGULATOR PER MM 36 11 07. TESTED AND LEAK CHECKED GOOD. ACCOMPLISHED REPAIR CONFIRMATION IAW FIM 36 10 00 810 807 PARA G, OPS NORMAL.
DUCT PRESSURE DIFFERENTIAL EXCEEDS 20 PSI DURING CLIMB: FL 370 100.1 PERCENT N1 53 DEG C L. 45 PSI R. 22 PSI FL 380 99.7 PERCENT N1 54 DEG C L. 43 PSI R. 22 PSI (CLIMB PWR) FL 380 90.2 PERCENT N1 54 DEG C L. 41 PSI R. 25 PSI (CRUISE PWR). REPLACED NR 2 ENGINE PRECOOLER CONTROL VALVE SENSOR. LEAK CHECKS NORMAL. REF M/M 36-12-03-400-801. REPLACED NR 2 ENGINE 450 DEGREE THERMOSTAT LEAK CHECKS NORMAL. REF M/M 36-11-05-400-801. ACCOMPLISHED REPAIR CONFIRMATION REF FIM 36-10-00-810-807 STEPS G (1) (13), ALL OPERATION TESTS PASS.
DUCT PRESSURE SPLIT L=44 PSI R= 26 PSI AT CRUISE 35000FT N1 = 89.1 N2= 93.2 AFTER 4 HOURS OF FLIGHT THE PRESSURE BUMP LEFT CABIN RATE DESCENDED 400FPM AND DUCT PRESSURE SPLIT CHANGE TO L=40 PSI AND R= 32 PSI THAN BOTH TO ORIGINAL SPLIT 44/26. PERFORMED ENGINE BLEED AIR SYSTEM HEALTH CHECK ON NR 2 ENG REF MM 36 11 00 700 801 ENG FAILS THE REVERSE FLOW CHECK PROTECTION TEST STEP I. REPLACED THE HIGH STAGE REGULATOR REF MM 36 11 07. RE-PERFORMED THE TEST AND TEST NOW PASSES. OPS NORMAL.
NR 2 IDG HAS RECENT HISTORY OF FREQUENT SERVICING. ACCOMPLISHED IDG OIL SYSTEM STATIC LEAK CHECK REF AMM 24 11 00 700 801. NO LEAK NOTED. REMOVED AND REPLACED IDG PUSH TO VENT VALVE REF AMM 24 11 00 700 804. REMOVED AND REPLACED PRESSURE FILL HALF COUPLING REF CMM 24 11 85. LEAKS CHECKED GOOD.
APU FAULT LIGHT ON START UNABLE TO START. FOUND FAULT CODE 49 61224 INLET TEMP SENSOR SHOWS OUT OF RANGE HIGH. REMOVED AND REPLACED INLET TEMP SENSOR PER MM 49 61 31 400 801. OPS CHECK GOOD.
WHILE PERFORMING OTHER MAINTENANCE FOUND CONNECTOR BASE MISSING SCREW AND BASE LOOSE ON NR 2 ENG HYD PUMP. REMOVED AND REPLACED NR 2 ENG DRIVEN HYDRAULIC PUMP ELECTRIC SOLENOID ASSY REF CMM 29 11 34 PG 727. ALL PARTS VERIFIED BY SEAMC. OP'S CHECK GOOD. NO LEAKS NOTED.
RADAR DISPLAYS RADIAL BANDS EMITTING FROM THE AIRCRAFT SYMBOL IN ALL MODES. REPLACED ANTENNA DRIVE UNIT REF MM 34 43 11. FLAT PLATE REMOVED & RE-INSTALLED REF SAME. OPS NORMAL REF MM 34 43 00. GROUND VERIFICATION GOOD.
ON CLIMB DUCT PRESSURE READINGS WERE: (FL 370 L 42PSI R 21PSI N1 100.6/ 100.6.) (FL 380 L 41PSI R 20PSI N1 101.0/ 101.0) (CRUISE FL 390 L 38PSI R 24PSI N1 89.8/ 89.7) (TOP DESCENT FL 390 L 37PSI R 23PSI N1 88.5 / 88.5.). ACCOMP ENG BLEED AIR SYSTEM HEALTH CHECK REF MM 36 11 00 700 801 AND MM 36 12 00 700 801. PRSOV AND HIGH STAGE REG FAILED. REPLACED PRSOV REF MM 36 11 04 400 801. REPLACED HIGH STAGE REGULATOR REF MM 36 11 07 400 801. PERFORMED BLEED AIR HEALTH CHECK REF MM 36 11 00 700 801 & 36 12 00 700 801. OPS CHECK GOOD.
DURING DEPARTURE WX RADAR DISPLAYED ERRONEOUS RETURNS ON BOTH DISPLAYS IN ALL TILT ANGLES. TEST FUNCTION APPEARED CORRECT. REPLACED WEATHER RADAR TRANSCEIVER PER MM 34 43 41. GROUND VERIFICATION SUCCESSFUL.
AFTER ENGINE START AFTER RECALL THE CONT CAB ZONE TEMP LIGHT CAME ON. IT WENT OUT WITH MASTER CAUTION RESET. GROUNDED YES. BITE OF BOTH ZONE TEMP CONTROLLERS SHOW FLT DECK CABIN SENSOR FAULT. FOUND FILTER IN CONTROL CABIN CLOGGED. CLEANED FILTER & GROUND OPS CHECK GOOD REF AMM 21 61 00 & FIM 21 62 TASK 842. SEAMC ETOPS DESK DAVE NOTIFIED.
AFTER ENGINE NR 1 AND NR 2 ENGINE ELEC HYD PUMP LOW PRESSURE LIGHT WOULD NOT EXTINGUISH. RESET EMDP NR 1 AND EMDP NR 2 PER MM 20 60 01 OPS CHECK GOOD C/W FIM 29 300 810&811. FUNCTION CHECK GOOD. GROUND VERIFICATION SUCCESSFUL SEAMC NOTIFIED.
APU DET INOP LIGHT ILLUMINATED. BITE CHECKED APU DET IAW FIM 26 10 801. FAULTED TAILPIPE LOOP REPLACED IAW MM 26 15 01, OPS CHECKED NORMAL.
APU DURING START UP AUTO SHUTS DOWN. FAULT CODE: 49 94299. REPLACED STARTED GENERATOR BYPASS SWITCH REF MM 49 91 13 400 803. COMPLETED FIM TASKS 49 90 00 810 809 PG 1 THRU 6 STEPS F(3). NO FURTHER MESSAGE.
APU FAULT LIGHT ON APU START LIGHT EXT AFTER 4 MIN. FAULT AGAIN ON 2ND ATTEMPT. REMOVED & REPLACED APU GENERATOR IAW AMM REF 49 41 21 PG BLOCK 401. OPS CHECK NORMAL PER AMM REF 49 11 00, APU OPERATIONAL TEST.
CONTROL CABIN ZONE TEMP LIGHT CAME ON DURING FLIGHT. RESETS ON RECALL OPS NORMAL. REPLACED CONTROL CABIN TEMP CONTROL VALVE.
CONTROL CABIN ZONE TEMP LIGHT ILLUMINATES UPON RECALL EXTINGUISHES UPON RESET. REPLACED FLT DECK TRIM AIR VALVE PER AMM 21 61 21 000 801 AND 21 61 21 400 801 LEAK CHECK GOOD AND PERFORMED BITE PER AMM 21 62 00 810 801, NO FAULTS NOTED.
CONT CAC "ZONE TEMP" ILLUMINATED UPON RECALL FOLLOWS QRH. CLEARS WITH MASTER CAUTION RESET. NR 2 PACK/ZONE TEMP CTRL LOGGED FLT DECK TRIM VALVE. REPLACED CONTROL CABIN TRIM MOD VALVE V143 REF MM 21 61 21. ALL INSTALLATION TESTS NORMAL PER MM 21 61 21. ETOPS SIGNIFICANT SYSTEM GROUND VERIFICATION COMPLETE. SEAMC NOTIFIED.
FMC 1&2 WENT OUT DURING PREFLIGHT AND WILL NOT RE-INITIALIZE. VERIFIED FAULT BOTH FMC 1&2 INOP PULLED CIRCUIT BREAKERS FOR FMC 1&2 MCDU AND COMPUTER RE-RACKED FMC 1&2 COMPUTERS RESET ALL CIRCUIT BREAKERS SYSTEM, OPS CHECK GOOD IAW MM 34 61 00.
HF NR 1 CB POPPED. REPLACED NR 1 HF TRANSCEIVER PER MM 23 11 21 000 801 & 23 11 21 0400 801. OPS CHECK OK PER MM 23 11 00 710 801. NO FAULTS, AIRCRAFT OK FOR SERVICE. ACCOMPLISHED PER HF MM REFERENCE.
THE "FMC DISAGREE" CAME ON TAXIING OUT IN SEA. RAN THE CHECKLIST AND LIGHT WENT OUT, OPS NORMAL.
WX STAB DISPLAYED ON ND. PERFORMED GROUND FUNCTIONAL VERIFICATION TEST PER MM 34 43 00 SYSTEM, OP CHECKS GOOD. NO HISTORY IN THE LAST 60 DAYS.
RIGHT SIDE WINDOW FAILED CIRCUIT BREAKER IS IN. PERFORMED FIM TASK 30 41 00 801, NO FAULTS NOTED. OK FOR SERVICE. SEAMC NOTIFIED, OPS CHECKED NORMAL.
NR 1 ENG SPINNER CONE PAINT PEELING. REMOVED & REPLACED NR 1 ENG FRONT SPINNER CONE REF MM 72 21 01.
CONTROL CABIN ZONE TEMP LIGHT ILLUMINATES ON RECALL. VERIFIED PERF FIM 21 62 TASK 842. NR 2 CONT BIT & PREV FLT TEST SHOWS FLT DECK TRIM VALVE FAULT. VERIFY TEST PASSES. NO CURRENT FAULT. NO HISTORY 90 DAYS. RESET FAULT. OPS CHECK LT PACK GOOD. MCF INFORMED.
PRESSURIZATION AUTO FAIL ALTN LIGHTS ILLUMINATED ON PREFLIGHT. ACCOMP PRESS CONT BITE ON BOTH CONT. ONLY NR 2 FAULT SHOWS FAULT CODE 101. CLEARED FAULT REF FIM 21 31TASK 803. NOW NO CURRENT FAULTS PRESENT. ALL GROUND CHECK'S OK PER SEAMC. A/C OK TO RETURN TO SERVICE.
HF NR 2 RECEIVES ONLY WILL NOT TRANSMIT. DIVERSION TIME 1 HOUR 38 MINUTES. CHANGED NR 2 HF T/R. OPS NORMAL. REF MM 23 11 21.
HF 2 WOULD NOT TRANSMIT OR RECEIVE IN VOICE WHEN KEYING MIC IT WOULD NOT BREAK SQUELCH WITH EITHER CAPT OR F/O. EVENTUALLY HF 2 STARTED WORKING NORMALLY. SUSPECT HF 2 WAS STUCK IN DATA MODE. PERFORMED HF SYS TEST REF AMM 23 11 00 730 801. HF2 OPS CK NORMAL. NO HISTORY LAST 30 DAYS.
RT HORIZONTAL STAB L/E DENTED. CUT OUT DAMAGE, REPAIRED PER SRM 55 10 01.
CONT CAB ZONE TEMP ILLUMINATED ON RECALL. NR 2 TEMP CONTROLLER LOGGED FLT DECK TRIM VALVE FAULT, PERFORMED FIM 21 62 00 810 832, SYSTEM BITES NORMAL. NO CURRENT FAULTS REF BITE 21 62 TASK 801. PER SEAMC GROUND VERIFICATION SUCCESSFUL.
ZONE TEMP LIGHT ILLUMINATED ON RECALL FOR CONT CAB LIGHT EXTINGUISHES ON MASTER CAUTION RESET GROUNDED YES. PERFORMED BITE TEST ON NR 1 AND NR 2 ZTC FOUND FLT DECK SENSOR FLAGGED ON BOTH CONTROLLERS. PERFORMED CLEANING OF SENSOR REF 21-61-10-100-801 REF BITE TEST 21-61-00-700-807-002 AND OPS CKD REF 21-61-00-700-807-002. NO FAULTS LOGGED IN BOTH CONTROLLERS. SYS RETURNED TO NORMAL. MFG NOTIFIED.
FCC DC C/B POPPED. RESET C/B PER MM 20 60 01. PERFORMED DFCS BITE CHECK PER FIM TASK 22 41 00 810 801. NO CURRENT FAULTS NOTED. OPS NORMAL.
FIRST OFFICERS FMC L2 BUTTON REQUIRES A VERY HARD PUSH TO FUNCTION. VERIFIED DEFECT, REMOVED AND REPLACED RT CDU (FMC) REF MM 34 61 00, OPS CHECK NORMAL. PARTS INFO VERIFIED.
MOMENTARY MASTER CAUTION UPON PWR APPLICATION ON T/O ABORTED AT 10KTS. CHECKED WINDOW HEAT & PITOT PROBE HEAT REF MM 30 31 00 & 30 41 00. PSE SHOWS NO FAULTS & FLIGHT RECORDER OPS NORMAL 76352. GRD VERIFICATION CONFIRMED NR 2 ENG. ANTI ICE FAULT14061. REMOVED AND REPLACED TAI VALVE, OPS CHECK FAILED. INSTALLED NEW TAI VALVE REF MM 30 21 11 400 801, OPS CHECK LEAK CHECK GOOD.
IN CRUISE FLIGHT AT 37000 RIGHT DUCT PRESSURE IS 25 PSI LEFT DUCT PRESSURE 44 PSI. RIGHT DUCT PRESSURE VARIES BETWEEN 21 PSI AND 44 PSI. ACCOMPLISHED FIM TASK 36 10 00 810 804 STEP 21F 34G, PERFORMED NR 2 ENG BLEED AIR SYSTEM HEALTH CHECK. FOUND PRECOOLER BAD, FAILED TO OPEN. REMOVED AND REPLACED PRECOOLER VALVE REF AMM 36 12 01. FOUND PRSOV VALVE FAILED TO OPEN AT 10 PSI. REMOVED AND REPLACED PRSOV REF AMM 36 11 04. LEAK CHECKED ALL SENSE LINES, NO LEAKS FOUND. HIGH STAGE VALVE FAILED TO OPEN WITH 10 PSI . REMOVED AND REPLACED HIGH STAGE VALVE REF AMM 36 11 06. RE-PERFORMED FIM TASK 36 10 00, NO FAULTS NOTED. ACCOMPLISHED ENGINE BLEED AIR CROSSOVER OPS TEST, OPS CHECKED GOOD. REF AMM 36 11 00 710 801. ALL PART NUMBERS VERIFIED WITH SEAMC.
HGS/AUTOLAND 30 DAY CHECK UNSUCCESSFUL. ALL SYSTEMS ON HGS AND A/L WORKED NORMALLY EXCEPT ACFT FLARED AND TOUCHED DOWN 55 FEET LT OF CENTERLINE. WINDS WERE CALLED AT 12KTS LT CROSSWIND. GROUNDED YES. CHECKED. NO HISTORY. FFR GP NR 2O SHOWS NO FAULTS "A" OR "B" CHANNEL FOR LAST FLT. DFCS LAND VERIFY BITE GP NR 49 PASSES. HGS SYS TEST PASSES REF MM 34 36 OO. ACFT REMAINS CATIIIA AUTOLAND & HGS QUALIFIED. OPS NORMAL.
OVERSPEED TO ACFT PAST MMO TEMPORARILY FOR 2 SECOND AT TOP OF DESCENT VNAV SPD DID NOT ENGAGE AS IT SHOULD ON THE COMMON VNAV PACKAGE. GROUNDED YES. CAPT REPORTED OVERSPEED OF APPROX 5KTS FOR 2 SEC. OVERSPEED WITHIN LIMITS PER MM 05-51-04 PARA G NO INSP REQ. BOTH FMC'S OPS TEST NORMAL PER MM 34-61-00-710-801 NO DEFECTS NOTED. VERIFICATION FLIGHT SUCCESSFUL.
FMC DISAGREE WARNING ILLUMINATED. GROUNDED YES. COMPLETED THE QRH FMC DISAGREE CHECKLIST ON THE GROUND. OPS NORMAL.
SHORTLY AFTER DESCENT TO FL370 FROM FL390 FOR TURBULENCE THE CABIN PRESSURE BECAME UNSTABLE. CABIN ALT STARTED TO CLB ALONG WITH CABIN RATE VARYING WILDLY FROM 2000' FPM CLB TO APPROX 3000' FPM DESCENT ACCOMPANIED WITH HIGH CABIN DIFF PRESSURE. QRH CONSULTED ALONG WITH QRC TO INITIATE A DESCENT TO LWR ALT. ATC NOTIFIED & DIVERTED TO RENO. NO CB'S WERE FOUND TRIPPED & O2 MASKS NEVER DEPLOYED. ALTN MODE OF ELECTRONIC PRESS. CONTROLLER SEEMED TO STABILIZE THE CABIN PRESSURE DURING DESCENT. GROUNDED YES. LENGTH OF DIVERSION: 35 MINUTES. R&R AFT OUTFLOW VALVE ASSEMBLY REF M/M 21-31-03. OPS CHECKS NORMAL REF M/M TASK 213100 710 801 AND 21-31-00 700 802.
RIGHT ENGINE HAS FUEL LEAK FOUND FUEL TUBE GASKET CONNECTING TO HMU LEAKING. VERIFIED FUEL LEAK DURING IDLE LEAK CHECK. REMOVED & REPLACED GASKET REF MM 73 21 10 400 801 F00 (ITEM 34) FIG 401. IDLE LEAK CHECK GOOD.
DURING LEAK CK OF REPLACEMENT OF NR 2 ENGINE NOTED HMU TO BE LEAKING AT THE TOP SURFACE FITTING/ADJUSTING SCREW CAP JUST AFT OF THE SUPPLY FUEL LINE. LEAK IS COMING FROM THE PARTING LINE BETWEEN HMU AND CAP REPLACED NR 2 ENGINE HMU PER AMM73 21 10 400. OPS AND TESTS CHECK GOOD NO LEAKS.
DURING OPERATIONAL CK OF HYDRAULIC PUMP ON NR 2 ENGINE FOUND THAT HYD PRESS WAS ZERO WITH PUMP SWITCH ON FOUND ENG HYD PUMP CONNECTOR DP1204 WORN. REPLACED MW0312 HARNESS REF IPC 71 51 03 01 AND AMM 71 51 03. OPS NML REF AMM 71 00 00 AND 73 21 00. ENG HYD PUMP TEST NML REF AMM 29 11 11 PRESSURE INDICATION NML WITH SWITCH ON. GROUND VERIFICATION OF ETOPS SIGNIFICANT SYSTEM SUCCESSFUL.
NR 2 ENGINE IDG FREQUENCY AT 390CPS REPLACED NR 2 ENGINE IDG PER AMM 24 11 11 400. OPS CHECK GOOD, IDG ETOPS VERIFIED.
WHILE ACCOMPLISHING OPS CHECK OF NR 2 ENGINE AFTER ENGINE CHANGE NOTED ENGINE DRIVEN PUMP WILL NOT SHUT OFF CLEANED CONNECTOR PER SWPM 20-60-01. OPS CK GOOD. VERIFIED HYD PUMP SHUTS OFF DURING GROUND RUN REF AMM 29-11-11-710-015-002.
JUST PRIOR TO LEVEL OFF AT FL 340 NR 2 ENG BEGAN TO SURGE BETWEEN 80 PERCENT AND RED LINE ON N1 GAGES N1 INDICATION RED BOXED MOMENTARILY TWICE EGT N2 FUEL FLOW WERE SURGING AS WELL. E 1.5 CHECKLIST FOLLOWED AT POWER REDUCTION EVERYTHING SMOOTHED OUT AND ENG RAN AS PER NORMAL WITH ALL GOOD INDICATIONS NOTES IN CLEAR SMOOTH SKYS ENG A/I OFF CENTER FUEL EMPTIED AND PUMPS OFF JUST PRIOR TO SURGING NO EXCESSIVE VIBRATION NOTED. REMOVED AND REPLACED NR 2 ENGINE. VERIFICATION FLIGHT SUCCESSFUL. OPS NORMAL.
SHORT TERM MAINT MESSAGE NR 73 20311 START SWITCH ARINC BUS DATA DISAGREE FOUND ON LEG NR 2 WHILE ACCOMPLISHING TC 7827300 ON NR 1 ENG PERFORMED FIM TASK 73 24 00 810 813 F00 SYSTEM CK'S GOOD, NO HISTORY IN 90 DAYS PER SEAMC ED GROUND VERIFICATION SUCCESSFUL.
PRESSURIZATION ERATIC IN AUTO + 400 FPM SPIKED 200 FPM ON LEVEL OFF OK IN ALTERNATE PERFORMED TASK 21 13 801 CONFIRMED NR 2 CABIN PRESS FAULT. FOUND NO LOGGED FAULTS IN NR 2 PRESS CONTROLLER HISTORY & NO CURRENT FAULTS. RAN PRESSURIZATION GROUND SYS TEST ON NR 1 & 2 CONTROLLER PER MM 21 31 00, NO FAULTS FOUND. SYS OPS CHECKS NORMAL. RESET NR 2 AUTO PRESS CONTROL.
AUTOTHROTTLE LIM ILLUMINATED IN CLIMB FROM 370 390 WITH AUTOTHROTTLES ENGAGED. NORMAL OPS WITH AUTOTHROTTLE OFF (NOTE: 2 KNOB SPLIT WITH AUTOTHROTTLE LIMIT ILLUMINATED AND CLIMBING). TS FAULT CODES FOUND AT CURRENT STATUS TEST WOULD NOT ENGAGE. RESET FCC A BREAKERS AND AT CURRENT STATUS TEST CHECKED GOOD. REPLACED FCC A PER AMM REF TASKS 22 11 33 000 801 400 801 CHECKED GOOD SOFTWARE VERIFIED CORRECT. VERIFIED ENG 1&2 TAT PROBE IND NORMAL. VERIFED NO FAULTS WITH TLA RESOLVER OR AUTOTHROTTLE BRAKE ASSY PER FIM REF 22 31 00 810 812. PERFORMED DFCS LRU INTERFACE TEST FOR FCC BITE GRP NR 35 LAND VERIFY TEST BITE GRP 49 (AMM 22 11 00 201) AND HGS SENSOR TEST FOR FCC AT PER AMMS REF 34 36 00 ALL TESTS PASS.
APU FILTER DELTA P INDICATOR POPPED. 41-91-13 INSPECTION AND LEAK CHECK IAW TASK49-91-13-600-801. REMOVED AND REPLACED OIL FILTER REF MM 49-91-12-000-802. GND VERIFICATION SUCCESSFUL.
NR1 ENGINE OIL QUANTITY READS 13 QUARTS ENG NR1 OIL ADDED: 6 QTS, ENG NR2 OIL ADDED: 5 QTS, APU OIL ADDED : 0.
WX RADAR, SHOWS STROBES AND FILLS DISPLAY WITH A GRAINY RETURN. DISPLAYS APPARENT GROUND RETURNS FROM WELL OVER HORIZON. THE TEST "TEST" IS OK. COULD NOT DUPLICATE MALFUNCTION REPLACED WX RDR R T PRECAUTIONARY PER MM 34 43 41 FUNCTIONS NML.
UNABLE TO HEAT PASSENGER CABIN TO PASSENGER COMFORT RANGE. TROUBLESHOT AND FOUND NO HEAT LEAVING TRIM AIR PRSOV. VERIFIED PRSOV NOT OPENING AND GOOD POWER AND GROUND. REQUIRES REPLACEMENT. REMOVED AND REPLACED TRIM AIR PRSOV PER MM 21 62 01. GROUND VERIFICATION SUCCESSFUL. SYSTEM OPS NML PER MM 21 62 01.
UNABLE TO ADJUST FWD OR AFT CABIN TEMP USING CONTROL KNOBS. CONT CABIN WORKS NORMAL. POSTIONED TRIM AIR SWITCH TO OFF POSITION ABLE TO CONTROL CABIN TEMPS. TEMP CONTROLLER (ZONE 2): FAULTED THE TRIM AIR MOD VALVE FOR THE FWD PASS CABIN. REMOVED AND REPLACED MOD VALVE PER: M M21 61 21. TEMP CONTROLLER FAULTS CLEARED (CONFIRM FIX).
NR 2 COM RADIO SHOWS FAIL IN ACTIVE AND STANDBY WINDOWS HAPPENED JUST AFTER GRD POWER DIED AND SWITCH TO APU. RE SEATED CONNECTOR NR 2 VHF COMM CONTROL PANEL. OPS CHECK GOOD REF MM 23 12 31. VERIFIED NR 2 VHF COMM CONTROL PANEL DISPLAYED FAIL IN LT AND RT WINDOWS.
NR 1 ENGINE OIL IS AT 13 QTS SERVICED ENGINE OILS NR 1 ADDED 3 QTS, NR 2 ADDED 3.5 QTS APU ADDED 0.
NR 2 ENGINE HAS A HISTORY OF ABOVE NORMAL OIL CONSUMPTION PERFORM MM 71-71-00-200-801 VENTS AND DRAIN INSPECTION, PART POWER ENGINE RUN REQUIRED. ACCOMPLISHED TSR AND AMM 71 71 00. NO LEAKS NOTED.
NR 2 ENG OIL CONSUMTION AT .61 NR 2 ENG OIL CONSUMTION AT ALERT. AIRCRAFT RESTRICTED FROM ETOPS SERVICE UNTIL OIL CONSUMPTION WITHIN LIMITS. INSPECTED INLET EXHAUST AND DRAINS. REF MM 71 71 00 PG 602, NO SIGNS OF LEAKAGE. OIL CONSUMPTION RATE IS NOW .20 BELOW ETOPS MAX CONSUMPTION RATE OF .60 ACFT IS NOW ETOPS CERTIFIED.
NR 1 ENGINE OIL CONSUMPTION AT .62 PER SEAMC. AIRCRAFT RESTRICTED FROM ETOPS SERVICE UNTIL EXCESSIVE OIL CONSUMPTION IS CORRECTED. PER SEAMC, AFTER LAST OIL ADD LP 6415958 NR 1 ENG OIL CONSUMPTION IS NOW .12 AC IS NOW ETOPS QUALIFIED.
NR 2 ENGINE OIL CONSUMPTION AT .62 PER SEAMC. AIRCRAFT RESTRICTED FROM ETOPS SERVICE UNTIL EXCESSIVE OIL CONSUMPTION IS CORRECTED. PER SEAMC AFTER LAST OIL ADD LP 6415958 NR 2 ENG OIL CONSUMPTION IS NOW .12 AC IS NOW ETOPS QUALIFIED.
NR 2 ENG EEC ALTERNATOR HAS BURN MARK WITH MISSING MATERIAL. REF LG PG 6415951 FOR BREAKERS PULLED AND MIG 51A'S INSTALLED. ROTABLE PART HAS BEEN VERIFIED. REMOVED ENG NR 2 EEC ALTERNATOR AND INSTALLED NEW SERVICEABLE EEC ALTERNATOR. TEST 3A LEAK CK AND TEST 13 EEC BITE CK. NO LEAKS OR RECENT FAULTS NOTED.
NR 2 ENGINE FUEL FEED HOSE CHAFED AND LEAKING. REMOVED AND INSTALLED NR 2 ENGINE FUEL SUPPLY LINE. WILL REQUIRE TORQUE. TORQUED NR 2 ENG FUEL SUPPLY LINE REF MM 73 11 10 43570. INSP NR 10 HOSE ASSY VERFIED. RAN NR 2 ENG FUEL SUPPLY LINE, LEAK CHECK GOOD. NO LEAKS AT THIS TIME.
ON CLIMBOUT DUCT PRESS SPLIT WITH RT DUCT CYCLING APPROX 60 CYCLES PER MIN. 10 000 N1 91.6 LT DUCT 40 PSI N2 94.7 RT DUCT40 50 PSI. 18 000 N1 96.7 LT DUCT 42 DUCT N2 96.7 RT DUCT 42 45 PSI 39 000 N1 90.7 LT DUCT 40 PSI. N2 93.8 RT DUCT 40 PSI. CYCLING STOPPED APPROX FL230 ACCOMP LEAK CHECK OF BLEED AIR SYS FOUND BELLOWS OF PRSOV LEAKING AND B-NUTS FOR BLEED REG LOOSE. TIGHTENED BLEED REG B-NUTS AND REMOVED AND REPLACED PRSOV 401 406 STEP G STEP 4. NEEDS TO BE ACCOMP ROTABLE PART NUMBER VERIFIED THRU SEAMC M. JACK PRSOV INSTALLED TEST ACCOMP REF MM 36 1104 STEP H, NO LEAKS NOTED. ACCOMP ENG BLEED AIR OPS TEST OPS NORMAL.
PNEUMATIC DUCT PRESSURE SPLIT BETWEEN LEFT AND RIGHT SYSTEMS NOTED DURING CLIMB. REPLACED RIGHTHAND ENGINE PRECOOLER CONTROL VALVE.
OIL LEAK DISCOVERED AT IDG MOUNT SEAL. REPLACED SEAL AND REINSTALLED IDG.
OIL DRIPPING FROM NR 1 ENGINE. OIL APPEARS TO BE COMING FROM AREA OF IDG OR HYDRAULIC PUMP PAD. OPERATED ENGINE AND PERFORMED LEAK CHECK. NO LEAKS NOTED ON 5 MIN ENGINE RUN.
NR 1 IDG OIL SAMPLE ANALYSIS SHOWS HIGH LEVELS OF DIRT CONTAMINATION AND TRACE METAL VALUES. REPLACED NR 1 IDG OIL COOLER. OP AND LEAK CHECK GOOD.
LT CTR BOOST PUMP IS LEAKING. REMOVED IMPELLER. FILLED CTR TANK WITH 14200. HOUSING LEAK CHECK GOOD. REPLACED LT CTR IMPELLER ASSY AND O-RINGS. LEAK AND OP CHECKS GOOD.
FUELING RECEPTACLE IS LEAKING WHILE TRANSFERRING FUEL. REPLACED FUELING RECEPTACLE AND O-RING. LEAK CHECK GOOD.
DURING SERVICE CHECK, FOUND NR 1 ENGINE IDG DELTA P INDICATOR EXTENDED. REPLACED NR 1 IDG FILTERS AND OILS. RESET INDICATOR. RAN NR 1 ENGINE DELTA P INDICATOR RESET GOOD.
MASTER CAUTION ON RECALL. CNTL CABIN ZONE TEMP ILLUMINATED. RESET WITH MASTER CAUTION. RESET FAULT ON NR 2 ZONE TEMP CNTLR. GROUND VERIFICATION TEST PASSED.
WHILE PERFORMING TASKCARD 78131002 FOUND NR 4 BEARING MESSAGE FOR ENGINE NR 1 LEVEL 2. ACCOMPLISHED EA7731 01027. EA REQUIRES MM TASK 77 31 00 970 805 F00 (AAVM DATA DOWNLOAD) WITHIN 25 FLIGHT CYCLES FROM 24FEB08. DOWNLOADED ENGINES 1, 2 NR 4 BEARING DATA AND FORWARDED TO AS POWERPLANT ENG'G MAINT CNTL & AOG ENG'G.
ON GROUND AT GATE WITH FWD CARGO PIT EMPTY THE FWD CARGO FIRE LIGHT & BELL ILLUMINATED SOUNDED. CONDITION RECURS AFTER SILENCING BELL LIGHT. BOTH A&B LOOPS TEST OK. UNABLE TO DUPLICATE DISCREPANCY. CLEANED ALL FWD CARGO PIT SMOKE DETECTORS PRECAUTIONARY. OP CHECKS NORMAL.
APU START ATTEMPT AFTER LANDING. BOTH STARTS UNSUCCESSFUL WITH FAULT LIGHT. TROUBLESHOT PER FIM 49 60 TASK 801. NO CURRENT FAULTS.
APU OIL FILTER DELTA P INDICATOR EXTENDED, REF TASKCARD 78349013. REMOVED AND REPLACED APU OIL FILTER AND RESET DELTA P INDICATOR.
ACARS "NO COMM" WHEN HF NR 2 SELECTED TO DATA. ATTEMPTED SEVERAL TIMES AT ONE HOUR INTERVALS TO RE-ESTABLISH COMM. HF VOICE WORKED NORMAL. NR 1 HF DATA WORKED NORMAL. UNABLE TO VERIFY DISCREPANCY. ACFT ACARS USES HF DATA WHEN OUT OF VHF DATA RANGE. REPLACED NR 2 TRANSCEIVER PRECAUTIONARY.
HR TRANSCEIVER MALFUNCTIONED CAUSING ACARS "NO COMM" ANNUNCIATION. REPLACED TRANSCEIVER. OP CHECKED OK.
LEFT CTR FUEL BOOST PUMP IS LEAKING. REPLACED ALL O-RINGS ON LEFT CTR BOOST PUMP. OP & LEAK CHECKS GOOD.
THE "AUTO FAIL" LIGHT ILLUMINATED WITH PRESS MODE SELECTED IN AUTOMODE. CHECKED PER AMM 21-31-00 CHECKS NORMAL.
PILOT REPORTED OIL LEVELS LOW BOTH ENGINES. NR 1 ENGINE ADDED 4.5QTS NR 2 ENGINE ADDED 5.5 QTS. APU FULL ADDED 0.
LEFT FMC FAILED. COULD NOT DUPLICATE LEFT FMC FAILURE. PERFORMED FMCS SYS TEST IAW MM 34-61-00. OPS NORMAL.
AT TOP OF DESCENT "VTK" FLAG APPEARED ON LEFT EFIS DISPLAY. BOTH FMC DISPLAYS DEFAULTED TO THE "MENU" PAGE. THREW FMC SWITCH TO "BOTH ON RIGHT" MESSAGE NOTE OF "SINGLE FMC OPS" FOLLOWED BY "DUAL FMC OPS RESTORED". RETURNED FMC SWITCH TO "NORMAL". OPS NORMAL. BOTH LT & RT FMC COMPUTERS LOGGED "L FMC FAILED". DEFERRED MAINTENANCE. LT FMC ON MEL PENDING ENGINEERING EVALUATION. REMOVED AND REPLACED LEFT FMC PER AMM REF 34 61 02
RIGHT AT TOP OF DESCENT "VTK" FLAG APPEARED ON LEFT EFIS DISPLAY. BOTH FMC'S DEFAULTED TO THE "MENU" PAGE. THREW FMC SWITCH TO "BOTH ON RIGHT". MESSAGE NOTE OF "SINGLE FMC OPS" FOLLOWED BY "DUAL FMC OPS RESTORED". RETURNED FMC SWITCH TO "NML" AND ALL FMC EFIS HAD NORMAL DISPLAYS. REPLACED LEFT FMC PER 34-61-02. OP CHECKS GOOD. REFERENCE PREVIOUSLY SUBMITTED SDR ASAA0752390.
CONTROL CABIN `ZONE TEMP` LIGHT CAME ON DURING RECALL. GOES OUT ON RESET. REPLACED CONTROL CABIN TRIM AIR MODULATION VALVE. OP AND BITE CHECKS OK.
WHILE TROUBLESHOOTING NR 2 IDENTIFICATION PLUG FOUND NR 1 IDENTIFICATION PLUG CONFIGURED WRONG. REPINNED ID PLUG PER 73 21 61 PG 501. EEC OPERATES NORMALLY.
AUTO THROTTLES OPERATING IN "A T LIM" MODE DURING CRUISE. ENGINE BITE SHOWS FAULTS 73 10772 9 (PS3 SIGNAL OUT OF RANGE) AND 73 11282 (EEC CHANNEL NOT ENERGIZED WITH ALTERNATOR VOLTAGE). REPLACED NR 2 EEC. EEC INSTALLATION TEST AT SYSTEM TESTS NORMAL.
F/O'S "MAP" FLAG NO "VSPDS" "ALT DIS" FLAG. SWITCHED FMC BOTH TO LEFT, 1 MINUTE LATER BACK TO FMC NORMAL. ALL MODES NORMAL. UPON ARRIVAL @ ACFT BOTH IRS SWITCHED OFF. REALIGNED BOTH IRS'S. ALL DISPLAYS NORMAL. NO HISTORY. ACFT REQUIRES ETOPS VERIFICATION FLIGHT. VERIFICATION FLIGHT SATISFACTORY.
MASTER CAUTION ON RECALL FOR ZONE TEMP CABIN. NR 2 FLT DECK TRIM VALVE FAULTED ON BITE TEST. REPLACED NR 2 CONTROL CABIN TRIM AIR VALVE. OPS NORMAL.
APU AUTO SHUTDOWN AT GATE. REPLACED APU ECU IAW MM 49-61-12.