N75436
Registered owner: UNITED AIRLINES INC, IL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| United Air Lines | Operator | 2019-06-09 – 2019-06-09 | Operator named in NTSB report |
| UNITED AIRLINES INC | Operator | 2019-06-09 – 2019-06-09 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
INSPECTING THE FASTENER HOLES ON LEFT WING INBD L/E, UPPER SPAR ATTACH, ON N/R 5000-0108, EA 5720-02922, FOUND 2 EXISTING HOLES OF 0.250" DIAMETER WITH CRACKS IN SKIN ONLY. ACCOMPLISHED REPAIR OF LTT WING INBD LEADING EDGE SKIN IAW SRM 57-41-01-2R-8.
EA 5510-01843 REV 1 OP 002 LEFT HORIZONTAL STAB RIB 2, STAB STA 101.90 HAS A CRACK ON THE LOWER TRANSITIONAL RADIOUS CONTINUING TO THE OPPOSITE SIDE ALONG THE CHEM MIL. REF AAR N/R 99952380 ACCOMPLISHED REPAIR OF LEFT HORIZONTAL STAB NO 2 RIB AS PER SRM 55-10-09-2R-4,
CORROSION AND SMALL HOLE AT LOWER FUSELAGE SKIN AROUND BS 965 B. ACCOMPLISHED REPAIR OF LOWER FUSELAGE SKIN BETWEEN STA 947.5 AND 967 AT STR 27L-27R AS PER SRM 53-00-01-2R-3 AND ECRA 5370-01202,
RIGHT HORIZONTAL STAB RIB 7, 3RD STIFFINER BACK HAS A CRACK OA BASE,IB SIDE. ACCOMPLISHED REPAIR OF RT HORIZONTAL STAB NR 7 RIB AT NR 3 STIFFENER IAW SRM 55-10-09-2R-4,
CRACK AT UPPER L/1 DOOR FRAME LOWER CORNER STA. 312 STR 5-6L. ACCOMPLISHED REPAIR OF FUSESALGE FRAME AT STA 312 AT STR 5L AND 6L AS PER SRM 53-10-07-2R-1, PENDING ESFR ENTRY, DIP REQUIRED AS PER TABLE 202,INSPECTION THRESHOLD 50,000 FLIGHT CYCLES OR 12,000 FLIGHT CYCLES AFTER REPAIR INSTALLATION, WHICHEVER COMES LATER, INSPECTION INTERVAL OF 12,000 FLIGHT CYCLES FOR HFEC.
MAIN CABIN AFT WET AREA,CORROSION AROUND SCREW HOLES ON FLOORBEAM AT STA 947.5,BETWEEN LBL-10 AND RBL-10. ACCOMPLISHED REPAIR AT STA 947.5 FLOOR BEAM IN REF WITH B737 -900 ER SRM 53-00-51-2R-1, AAR ESR 20-12933 AND ECRA 5370-01199, PENDING ESFR ENTRY, NO DIP REQUIRED.
CRACK FOUND AT RIGHT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 120.30, 26" FROM FRONT SPAR, I/B ROW. CRACK LENGTH:1" REF. AAR N/R:99951969 INSTALLED NEW REPAIR DOUBLER ON RT HORIZONTAL STABILIZER LOWER SKIN AND 2EA REPAIR FILLERS AT STAB STA 120.30 PER SRM 55-10-01- -2R-11,PENDING ESFR ENTRY, DIP REQUIRED AS PER TABLE 204, INSPECTION THRESHOLD 56,000 TOTAL FLIGHT CYCLES WITH 9,000FLIGHT ADD EMP:V939559 CYCLE INTERVALS FOR DVI AND LFEC.
[EA 5510-01843]- CRACK FOUND AT LEFT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 157.10 , 23" FROM FRONT SPAR , I/B ROW. CRACK LENGTH: 1.5". REF AAR N/R 99951973 ACCOMPLISHED REPAIR ON LEFT HORIZONTAL STABILIZER LOWER SKIN, AT STA: 157.10, 23.0" FROM FRONT SPAR, I/B OF RIB, ASPER REF. B737 SRM 55-10-01-2R-11 AND SRM 51-40-02-0G-0 WORK ACCOMPLISHED BY V901438 ESFR ENTERED. INSP C/W ACCOMPLISHED INTERIM REPAIR ON LEFT HORIZONTAL STAB. LOWER SKIN, AT STA 157.10, 23.0" FROM FRONT SPAR, I/B OF RIB, AS PER SRM 55-10-01-2R-11 AND SRM 51-40-02-0G-0.
L1 DOOR INNER CHORD CRACKED AT STA 312. REMOVED AND REPLACED L1 DOOR INNER CHORD AS PER SRM 51-40-02-0G-0 AND DWG 141A8110,
CRACKED UPPER INTERCOSTAL STRAP AT FWD CABIN STA. 380 BL 0. REMOVED AND REPLACED UPPER INTERCOSTAL STRAP AT STA 380-400 BL 0 AS PER SRM 51-10-02-0G-0 AND DWG 143A5400. REMOVED AND REPLACED UPPER INTERCOSTAL STRAP AT STA 380-400 BL 0 AS PER SRM 51-10-02-0G-0 AND DWG 143A5400.
DENT FOUND AT APPROXIMATELY BS 951 THE 5 OCLOCK POSITION. JUST AFT OF WATER SERVICING PANEL. AFT CARGO RH SIDEWALL PANEL # 142VW REMOVED FOE ACCESS, REF AMM 25-52-06-400-801, DRW T29-0620-1-0069. REMOVED AFT CARGO FLOOR PANEL #140DF REF:AMM 25-52-10-400-801, DRW T29-0620-1-0043. AFT CARGO COMPARTMENT WASTE TANK ENCLOSURE PANELS 141SW, 141QW REMOVED FOR ACCESS REF AMM 25-52-20-400-801, DRW T29-0620-1-0021. REMOVED INSULATION BLANKETS FOR ACCESS FROM STA. 927 TO STA. 947 AND STR-22R TO STR-24L REF AMM 25-52-10. FOUND DENT LOCATION AT STA. 928.5 TO STA 946.5 AND BETWEEN STR 25R AD STR 26R. REMOVED EXTERNAL DOUBLER AT STA. 951. REMOVED INTERCOSTAL BETWEEN STR. 25-26. BETWEEN STA. 928.5-951. PER SRM 51-40-02. MATCH DRILLED ALL REPAIR FASTENER HOLES INTO NEW SPLICE DOUBLER. TRIMMED TO SIZE. PER ECRA 5330-06581. PERFORM HFEC HOLE PROBE INSPECTION AT ALL REMOVED FASTENER LOCATIONS IAW NDT MANUAL PART 6 51-00-00, PROCEDURE 16. PER ECRA 5330-06581 STEP B(1)(C). PERFORMED HFEC HOLE PROBE INSPECTION AT ALL REMOVED FAVERIFIED,REPAIRED DAMAGE IAW EC/RA 5330-06581 REV A.
EMERGENCY LIGHTING SYSTEM OPERATIONAL CHECK {B737-33-3-0235} - ROW 8ABC, 27DEF AND AFT OVHD EMER LIGHTS INOP REMOVED AND REPLACED ROW 8ABC 27DEF AND AFT OVHD EMERGRNCY LIGHT BULBS WITH SERVICABLE REF AMM 33-51-03-960-801 OPS CHECK OK
WATER TRUCK BACKED INTO AIRCRAFT AND CAUSED DAMAGE. DENT TOTAL GOUGE LENGTH IS 2.4 INCHES. BOTH DENTS ARE FOUND TO BE OUT OF LIMITS PER SRM 53-00-01-1A-5 LOWER DENT IS 9.910 FROM REPAIR ACCOMPLISHED ON ECRA 5330-06581 LOCATION OF DAMAGE IS ON LH SIDE OF AIRCRAFT BELLY FWD OF WASTE EVALUATED DAMAGE LOCATED STA 799.5 ABOVE AND BELOW STR 25 UPPER PERFORMED DVI OF UNDERLYING STRUCTURE NO DEFECT NOTED SERVICE ACCESS DOOR. SEE ATTACHED PICTURES. DENT MEASURES 3.0 X 2.0 X 0.053. A/Y OF 37 AND SMALL GOUGE AT BOTTOM OF DENT 0.004 DEEP , LOWER DENT MEASURES 3.7 X 3.050 X 0.150 A/Y 20 WITH A 0.004 DEEP GOUGE RUNNING VERTICALLY THROUGH LOCKED FOR MAINTENANCE FERRY FOUND. PER STEP 4. VISUALLY INSPECT ALL OPEN FASTENERS HOLES COMMON TO REPAIR AREA NO DAMAGE NOTED, PER STEP 8. ALL STEPS PERFORMED PER AVO: 436-24-11-12-01. PERFORMED HFEC OF CUT OUT REF 737 PART 6 51-00-00 PROC VERIFIED MATERIAL ID PER AVO #436-24-11-12-01. 23,PERFORMED HFEC HOLE PROBE INSPECTION REF 737 PART 6 51-00-00 PROCEDURE 16, PERFORMED HFEC COUNTERSINK INSPECTION REF 737 53-00-00 PROCEDURE 4. NO CRACKS NOTED. . CUTOUT DAMAGED AREA PER SRM 51-10-02. MAPPED CUTOUT AND SENT TO PERFORM SURFACE HFEC OF TRIM EDGE OF CUTTOUT. PER NDT MANUAL. PERFORM OPEN HOLE HFEC OF REMOVED EXISTING FASTENERS PER NDT PERFORM AN HFEC COUNTERSINK INSPECTON OF INITIAL REMOVED CORRECTION TO PREVIOUS INPECTION. REFERENCE FOR HFEC COUNTERSINK REMOVED ALL FASTENERS WITHIN REPAIR AREA STEP 5.
FLAPS 1 NORMAL INDICATIO FLAPS 2 SLIGHT SPLIT OF NEEDLES LANDED FLAPS 1 REF AMM TASK 27-51-00-740-801 NO EXSISTING FAULTS FOUND DURING FSEU BITE CHECK. NO PREV FAULTS FOUND WHEN LOOKING AT PREV FAULTS MENU ON THE FSEU. RAN FLAPS FULL TRAVEL 0-40 TWICE. FSEU FINAL TEST SHOWS NO FAULTS. NO HISTORY ON AIRCRAFT. FIM TASK 27-51 TASK 840 ALSO REVEALS NO FAULTS
CHECK (VISUAL) CARGO COMPARTMENT FIRE BOTTLE DISCHARGE SQUIB EXPIRATION DATE TAG FOR EXPIRATION DATE. {MULT-26-3-0021} - INBORD SQUIB PLACARD INDICATES EXPIRATION 2023 PARTS NEEDED MF PARTS# 446616 CORRECTION IPC 26-23-01-22A ITEM 20 REMOVE THE LINING AT THE AFT END OF THE FORWARD CARGO COMPARTMENT TO GET ACCESS TO FIRE BOTTLE. L/H FIRE BOTTLE HAS INBORD SQUIB EXPIRED. NEEDS TO BE REPLACE SQUIB IS BEEN REMOVE AND TEMPORARY INSTALL BY HAND TO COVER PORT, ON TILL NEW PART SHOWS UP. VERIFIED REMOVAL AND REPLACEMENT OF CARGO BOTTLE FWD SQUIBB REF AMM 26-23-02-000-801 VERIFIED REMOVAL AND REPLACEMENT OF CARGO BOTTLE FWD SQUIBB REF AMM 26-23-02-000-801 RMVD/RPLD NBR 1 CARGO FIRE BOTTLE FWD SQUIB IAW AMM TASK 26-23-02-000-801 AND TASK 26-23-02-400-801. OPS CKS GOOD.
PER FLIGHT CREW , ONCE AT CRUISE ALL LIGHTS ON CENTER PEDESTAL STARTED TO FLASH WITH A FUME SMELL. ALL COMM HEADS, NAV HEADS, CARGO FIRE HEADS, WERE FLASHING EXCEPT FOR SELCAL AND FLT DK DOOR LIGHTS. DISCONNECTED CONNECTOR FROM STAB TRIM OVERRIDE PANEL ALL RADIO PANELS AND NAV PANELS AND CARGO FIRE DETECTION PANEL DISPLAYS AND INDICATIONS RETURNED TO NORMAL. INSPECTED FWD AND AFT E&E COMPARTMENTS NO FLUIDS FOUND.INSPECTED WIRING IN P8 AFT PEDESTAL AND AVIONICS COMPTS..REF LOG PAGES 5987908, 5993049, 5998176, 5993047, 5993109. PERFORMED CONDITIONAL INSPECTION REF AMM 05-51-26-800-801-C1.REF SWPM 20-60-03. REF LOG PAGE 5987108 NEED TO REPLACE #3 RTP. PANEL, RADIO TU OFF 29-2320-9-0002 4546 ON 29-2320-9-0002 0216 PANEL, RADIO TU OFF 29-2320-9-0002 4546 ON 0000 REMOVED AND REPLACED OBSERVERS RTP,OP CHECK NORMAL.REF AMM 23-12-41-400-801. PARTS USED: 29-2320-9-0002,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1536721 SN OFF 4546. COMM MANAGEMENT UNIT WILL NOT TEST OR POWER UP. UNIT, COMM MGMT OFF 76-2337-9-9001 3756 ON 76-2337-9-9001 4488 UNIT, COMM MGMT OFF 76-2337-9-9001 3756 ON 0000 R&R COMM MANAGEMENT UNIT REF AMM 23-27-33-020-801, 23-27-33-420-801, 23-27-00-800-801, 23-27-33-700-802, 23-27-35-700-801. CAPT'S NAV PANEL REQUIRES REPLACEMENT DUE TO COFFEE SPILL AND PANEL FLASHING. PANEL, CONTROL,
32607201 CREW ADVISED VIA ACRAS (SEE ATTACHED PHOTOS) CREW FOLLOWED QRH LANDING GEAR COMMANDED UP, NOSE GEAR, LEFT GEAR AND RIGHT GEAR REF FIM 32-30 TASK 815. VISUALLY INSPECTED MANUAL EXT DOOR REMOVED AND REPLACED MANUAL EXT SWITCH PER AMM 32-34-11. THAT INSTRUCTED TO OPEN/CLOSE MANUAL GEAR EXTENSION ACCESS DOOR GREEN AND RED LIGHTS ARE ON SWITCH, DOOR AND SWITCH APPEAR NORMAL. CLICK IS HEARD AND FELT ADJUSTMENT OF SWITCH PERFORMED PER AMM 32-34-00. FINAL OPS CHECK AND GEAR RETRACTED NORMALLY. PRIOR TO DOOR BEING CLOSED ALL THE WAY. HAS PREVIOUS HISTORY. STILL REQUIRED. PARTS USED: 29-3234-3-0010,QTY :1 ADD EMP:U354047 PREFORMED MANUAL EXTENSION AND NORMAL GEAR RETACT AND EXTENSION IAW AMM 32-34-00-730-801 AND 32-32-00-710-801 NO DEFECTS NOTED AT THIS TIME ADD EMP:U075381
RH HORIZONTAL STAB LOWER SKIN CRACKED 1" IN LENGTH AT APPROX STA 129.50 I/B OF THE 7TH DRAIN HOLE 17" FROM L.E.M REF BY AIRB ORNE/PEMCO NR.13619.0325 ACCOMPLISHED CUTOUT OF CRACK ON R/H HORIZ STAB LOWER SKIN @ APPR TO VERIFY ENDS OF 1.85"L CRACK & TO VERIFY CRACK CONTAINMENT AFT OX STA 129.5 & 17" FROM L/E FABRICATED & INSTALLED REPAIR DOUBLE ER CUT-OUT COMPLETE ACCOMPLISHED IAW B737 NTM PART B, 51-00-00 P R IAW B737 SRM 55-10-01-2R-11 REPAI. APPLIED TOP COAT REPAIR ARE ROCEDURE 23. COMPLETED BY V924341, INSP BY Q809, ENTERED BY V928 A IAW B737 AMM 51-21-73-370-803. HFEC SURFACE SCAN OF LOWER SKIN 371. RE-INSP BY Q878
RH HORIZONTAL STAB LOWER SKIN CRACKED 1" IN LENGTH AT APPROX STA 129.50 I/B OF THE 7TH DRAIN HOLE 17" FROM L.E.M REF BY AIRB ORNE/PEMCO NR.13619.0325 ACCOMPLISHED CUTOUT OF CRACK ON R/H HORIZ STAB LOWER SKIN @ APPR TO VERIFY ENDS OF 1.85"L CRACK & TO VERIFY CRACK CONTAINMENT AFT OX STA 129.5 & 17" FROM L/E FABRICATED & INSTALLED REPAIR DOUBLE ER CUT-OUT COMPLETE ACCOMPLISHED IAW B737 NTM PART B, 51-00-00 P R IAW B737 SRM 55-10-01-2R-11 REPAI. APPLIED TOP COAT REPAIR ARE ROCEDURE 23. COMPLETED BY V924341, INSP BY Q809, ENTERED BY V928 A IAW B737 AMM 51-21-73-370-803. HFEC SURFACE SCAN OF LOWER SKIN 371. RE-INSP BY Q878
FUSELAGE SKIN DAMAGE BS 1030 - 1045, S13-14L, ACCOMPLISHED CUTOUT DAMAGED AREA IAW STEP 6 OF AVO10288. PERFORMED HFEC PER AVO 10288 STEP 7 NO INDICATION OF CRACKS. PT PERFORMED HFEC PER AVO 10288 STEP 9, NO CRACKS. PERFORMED HFEC HOLE PROBE IAW AVO 10288 STEP 11, NO CRACKS. PERFORMED HFEC COUNTER SINK IAW AVO 10288 STEP 12, NO INDICATIONS, PERFORM HFEC OF AREA CUTOUT STEP7 OF AVO10288. PERFORMED HFEC HOLE PROBE INSP PER AVO10288 REV B, STEP 11. PERFORMED HFEC COUNTERSINK INSP PER AVO10288 REV B, STEP 12. NO CRACK INDICATIONS WERE NOTED. ACCOMPLISHED .040 INSURANCE CUT IN REF TO AVO10288 REV B STEP 7A FOR STRINGER REPAIR IAW AVO10288 REV B, STEP 5A.
FUSELAGE SKIN DAMAGED BS 1006 - 1016, S13-14L. CUTOUT DAMAGED AREA REF STEP 6 OF AVO10287. PERFORMED HFEC PER AVO 10287 STEP 7, NO INDICATION OF CRACKS (PT PERFORMED HFEC PER AVO 10287, STEP 9. NO INDICATION OF CRACKS (PT 6 HFEC COUNTER SINK PER AVO 10287 STEP 12. NO INDICATION. HFEC HOLE PROBE PER AVO 10288 STEP 11. ULTRASONIC THICKNESS CK OF BLEND OUT STEP 10, FOUND NO OTHER AT THIS 6 51-00-00 PROCEDURE 23, 51-00-00 PROCEDURE 23, OF CRACKS PT 6 53-30-00 PROCEDURE 4, CRACKS LOWEST VALUE WAS .079 AT E2 AND E9 LOCATIONS ON DRAWING 10287 LOWEST VALUE WAS .079 AT E2 AND E9 LOCATIONS ON DRAWING. BLENDED OUT DAMAGES REF STEP 8 OF AVO10287, STRIPPED PAINT TO ACCOMPLISH SCRIBE LINE INSPECTIONS IAW AVO10287 REV A,
PDA 2 REFERENCE ORIGINAL LOG PAGE 8887088, LEFT MAIN LANDING FIXED DOOR MISSING ATTACH HARDWARE AT AFT LOWER ATTACH POINT. REMOVED LEFT CENTER AND INNER MAIN LANDING GEAR DOORS (FLYING 32-13-11-000-802. PLACED DOORS IN EWR CDL HOLD AT HANGAR 54 REMOVED. DOORS) AS PER AMM TASK 32-13-11/401 OR AMM TASK STORES. REQUESTING CDL FOR LEFT MAIN GEAR CENTER AND INNER DOORS
FIRE WARN LIGHT ON DASH ILLUMINATED ON TAKEOFF ROLL NO OTHER LTS ILLUMINATED CODE : 84 ON THE BITE TEST...AFTER DISCONNECTED WHEEL WHEEL FIRE DETECTOR, WARNING LIGHT EXTINGUISHED.SUSPECTED FIRE DETECTION LOOP ON KNEEL BEAM BAD.FURTHER TROUBLESHOOTING INDICATED LOOP M270 AT FAULT REF WDM26-12-11-5. REPLACED LOOP M270 IAW AMM26-18-02. CONFIRMED WHEEL WELL FIRE DET SYS ACTIVATED AND TESTS NORMAL. WHEEL WELL FIRE DET SYS OK FOR SVC, REMOVED DEFER STICKER. PER LP 8788539 : WHEEL WELL FIRE LT ILLUMINATED ON CLIMB OUT. LIGHT EXTINGUISHED AFTER APPROX 5 MIN.WHEEL WELL FIRE LT ILLUMINATED ON CLIMB OUT. LIGHT EXTINGUISHED AFTER APPROX 5 MIN.DEACTIVATED THE WHEEL WELL FIRE DETECTION SYSTEM AND VERIFY BRAKES ARE COOL TO THE TOUCH BEFORE ENGINE START IN REFERENCE WITH MEL 2604B.THIS ITEM CORRECTED PER LOG PG 8789135
SEAT MOUNTED EMERGENCY EXIT LIGHT AT ROW 22ABC DAMAGED. REMOVED AND REPLACED WHITE LIGHT ASSY REF MM 33-51-11. OPS CK OK. VERIFIED IDT REQUIREMENTS
PDA 3 AERODYNAMIC SEAL MISSING ON RIGHT WING AFT TRAILING EDGE FLAP O/B TRACK. ADDED PHOTO. REQUEST CDL. DISPATCH DESK: 82 NAME: KEITH DATE: 18-JUL-21- NEEDS SEAL C/W CDL. FURTHER DETAILS AWAITED.
LANDING GEAR LEVER DOES NOT MOVE TO THE UP POSITION IN FLIGHT, I S FREE TO MOVE TO THE UP POSITION WHEN THE LOCK OVERRIDE IS USED INFORMATIO ONLY - CREW STATED THAT THEY DID NOT ATTEMPT TO CHECK THE ALTERNATE GEAR EXTENSION DOOR. MM CHECKED DOOR AND FOUND DOOR PROPERLY CLOSED AND SECURE. CONTROLLER AND MANAGER FOR SIGNOFF. LOCKED BY TOMC MANAGER. WILL NEED CONCURRENCE FROM TOMC UNLOCKED FOR UPDATE THAT GSBV IS NOT CLOSED AND AIRCRAFT IS IN THE AIR. PSEU REPORTED FAULT CODE 31-51001 GSBV FAULT. INDICATING REF FIM 32-61-00-810-825. LOCKED FOR TOMC APPOVAL. UNLOCK FOR UPDATE REPLACED GROUND SPOILER INTERLOCK PROXIMITY SENSOR REF FIM 32-61-00-810-825 AND AMM 27-62-61. SENSOR STILL NEEDS FUNTIONAL TEST REF AMM 27-62-61-400-806. LOCK FOR TOMC APPROVAL 27-62-00-820-811 UP TO ITEM D (2) (H) ACP GROUND SPOILER INTERLOCK VALVE ADJUSTMENT REF AMM UNLOCK ACP GROUND SPOILER INTERLOCK VALVE ADJUSTMENT REF AMM 27-62-00-820-811. NEEDS THE GROUND SPOILER INTERLOCK VALVE FUNCTIONAL TEST REF AMM27-62-61-400-808 ACCOMPLISHED GRD SPOILER INTERLOCK VLV FUNCTIONAL TEST - RIGGING METHOD REF MM27-62-61-400-808, OPS CHECKED GOOD. ACCOMPLISHED GRD SPOILER INTERLOCK VLV PROXIMITY SENSOR FUNCTIONAL TEST REF MM27-62-61-400-806, OPS CHECKED GOOD. REMOVED RIG PIN S/B-3 FROM INTERLOCK VALVE YOKE. ACCOMPLISHED 2 EACH SUCCESSFUL GEAR SWINGS WITH NORMAL INDICATIONS.
RH FWD OVERWING EMERGENCY LIGHT KAPUT. REPLACED CORRESPONDING BATTERY CHARGER AND BATTERY PER AMM 33-51-06, OPS NORMAL ADD EMP:94595
REF F/C N/R 9720302 AND EA 5510-01843 R/H STAB INSPAR LOWER SKIN CRACKED AT STA 101.9 ABOUT 21" FROM FRONT SPAR R/H HORIZONTAL STAB LOWER INSPAR SKIN AT STA 101.90 HAS BEEN REP AIRED IAW ECRA 5511-01089 AN SRM 55-10-01 REP 11 INSP THRESHOLD AT 56000 TOTAL FLT CYCS FOLLOWED BY REPEAT INSPS AT EACH SUBSEQUENT 9000 CYCS PER STEP 5.A TABLE 204 ACCOMPLISH A PERMANENT REPAIR ON OR BEFORE 29 2022 PLANNING TO CONTACT ENGINEERING AFTER 29 NOV 2021 BUT BEFORE 29 DEC 2021 FOR THE PERMANENT REPAIR TOMC APPROVED DIP REF EC/RA 5511-01089 PART 1 STEP 3, ACCOMPLISH A PERMANENT REPAIR ON OR BEFORE 29 JAN 2022.PLANNING TO CONTACT ENGINEERING AFTER 29 NOV 2021 BUT BEFORE 29 DEC 2021 FOR THE PERMANENT REPAIR.? NOTE TO PLANNING: THIS ECRA IS BEING EVALUATED FOR DAMAGE TOLERANCE UNDER 14CFR 26.43(D) AND WILL LIKELY BE MADE PERMANENT WITH REPEAT INSPECTIONS. TOMC-APPROVAL FROM SC1ELBYC COMMENT REVIEWED AND APPROVED. QC REVIEW QC REVIEW INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.
REF EA 5510-01843 REV H L/H HORIZONTAL STABILIZER LOWER IN-SPAR SKIN HAS CRACK AT STA 175.50 11 INCHES FROM FWD SPAR. REF FLEET CYCLE NON-ROUTINE 9720279. REPAIRED L/H HORIZONTAL STAB. LOWER IN-SPAR SKIN CRACK AT STA. 175.50 11 INCHES FROM FWD SPAR PER SRM 55-10-01 REPAIR 11. SEE FLEET CYCLE LOG PG. 9720270 FOR ALL WORK PERFORMED. INITIATE DIP PER SRM 55-10-01 STEP 5.A. TABLE 204 AS REQUIRED "ACCOMPLISH INITIAL INSPECTION ON OR BEFORE 50,000 TOTAL FLIGHT CYCLES. ACCOMPLISH REPETITIVE INSPECTIONS AT INTERVALS NOT TO EXCEED 9,000 FLIGHT CYCLES." PER SRM 55-10-01 PG 223 TABLE 204, INSP THRESHOLD STARTS AT 56,000 TOTAL FLIGHT CYCLES. RE-INSP AT INTERVALS OF 9,000 FLIGHT CYCLES. TOMC APPROVED. SRM 55-10-01 REPAIR 11, PG 223, STEP 5, A.
R/H CENTER WING REAR SPAR VERTICAL PRESSURE WEB HAS APPROX 25" CRACK AT RBL42 R/H VERTICAL PRESS WEB HAS BEEN REPAIRED IAW SRM 57-10-10 REP 3 ALT 2 INSP THRESHOLD AT 56000 FLT CYCS AFTER REPAIR FOLLOWED BYREPEAT INSPS AT EACH SUBSEQUENT 36000 FLT CYCS PER TABLE 205 R/H VERTICAL PRESS WEB HAS BEEN REPAIRED IAW SRM 57-10-10 REP 3 ALT 2 INSP THRESHOLD AT 56000 FLT CYCS AFTER REPAIR FOLLOWED BYREPEAT INSPS AT EACH SUBSEQUENT 36000 FLT CYCS.
FUSELAGE FRAME CRACKED STA.867 BETWEEN S-27L AND S-27R MATERIAL VERIFIED FOR -1 REPAIR J AS .080 7075-0 CLAD PO 8852031 PER AVO ESC190613-0436-1 STEP 4. ED PART PER AVO ESC190613-0436-1. STEPS 4 AND 6. FABRICATED -1 REPAIR J. PERFORMED FLOURESCENT PEN. INSP. ON FORM VERIFIED PO#8852031 AND METAL .80-7175-0 C/W FPI IAW SOPM 20-20- 2 ON FORMED AREA. NO DEFECTS NOTED. CW ITEM #6 FPI PER AVO ESC190613-0436-1. COMPLETED STEPS 1, TRIM OUT FRAME WEB,ALSO COMPLETED STEP 3. PER AVO ESC190613-0436-1A STEP A.1B. HFEC INSPECT FRAME WEB TRIM OUT. OF REMOVED FASTENER AND INSULATION STUD HOLES. PER AVO ESC190613-0436-1A STEP A.2 PERFORM HFEC HOLE PROBE INSP. PER CURRENT AVO ESC190613-0436-1A STEP B.1 FABRICATED -1 REPAIR ANGLE FROM CLAD .071 7075-0 PO 5417049317. IR ANGLE AFTER FORMING. PER AVO ESC190613-0436-1A STEP B.1 PERFORM PEN. INSP. OF -1 REPA STEP A.1.B. PERFORMED .040 INSURANCE CUT OF FRAME PER AVO ESC190613-0436-1B PER AVO ESC1903613-0436-1C STEP B.1 FORMED REPAIR ANGLE -1 FROM CLAD .071 7075-0 PO 5417049317. VERRIFED FRAME WEB TRIMOUT PER A.1A, HFEC ACCOMPLISHED PER A.2. NO DAMAGE NOTED,FORMED REPAIR ANGLE-1 FROM CLAD .071 7075-0 PO 5 417049317 STEP B.1., MATERIAL VERIFICATION ACP., FPI ACCOMPLISHE D PER STEP B.2.1 INS CUT PER A.1.B., PER AVO ESC190613-0436-1B. REPAIR ANGLE -1 HEAT TREATED TO -T62 CONDITION AFTER FORMING REFERENCE HEAT TREAT FORM 43-0150 NEED TO PERFORM FPI OF -1 ANGL E PER AVO ESC190613-0436-1C STEP B.1 NOTE. C/W FPI IAW SOPM 20-20-02 PER AVO ESC190615-0436-1C S
FUSELAGE FRAME CRACKED AT STA.887 BETWEEN S-27L AND S-27R. VERIFY MATERIAL FOR THE -1 REPAIR ANGLE 063-7075-0 P.O. 6215711. REF AVO ECS190615-0436-1. ADD EMP:N STEP B.1 ANNEALED CONDITION. REF. AVO ESC 190615-0436-1 FORMED REPIR ANGLE FROM .063 7075-0 MATERIAL, P0#6215711 MATERIAL VERICATION ACP .063 7075-0 MATERIAL, P0#6215711, VERFIED FORMED REPAIR ANGLE PER STEP B.1.A, FPI ACCOMPLISHED PER B.1.NOTE AVO ESC190615-0436-1A COMPLETED STEP 1. AND STEP 2, AND 2.A TRIM OUT CRACK IN WEB REF AVO#ESC190615-0436-1A. ACCOMPLISHED HFEC INSPECTION,REF AVO#190615-0436-1A, STEP 2B NO LIMITING DEFECTS FOUND. ACCOMPLISHED STEPS 3 ,4 AND 5 REF AVO #ESC 190615-0436-1, NO LIM ITING DEFECTS FOUND REPAIR ANGLE -1 HEAT TREATED TO -T62 CONDITION AFTER FORMING REFERENCE HEAT TREAT FORM 43-0150 NEED TO PERFORM FPI OF -1 ANGL E PER AVO ESC190615-0436-1A STEP B.1.A NOTE. C/W FPI IAW SOPM 20-20-02 PER AVO ESC190615-0436-1A STEP B.1.A N OTE NO DEFECTS NOTED C/W STEP FABRICATION B.1A FABRICATED -1 REPAIR ANGLE, AND B.C FABRICATED STRUCTURAL FILLER ,056 7075-T6, PO#823366320. OK TO ALODINE, AND FR PRIME PARTS REF. STEP B1 A+C OF AVO# ESC190615-0436-1A, READY TO INSTALL. ALODINED AND PRIMED -1 REPAIR ANGLE AND -3 FILLER (.056 7075T6) INSPECTION CLEARANCE TO INSTALL -1 REPAIR ANGLE AND -3 FILLER REF. STEP B1 A+C OF AVO# ESC190615-0436-1A, OKAY TO INSTALL. DRILLED REPLACEMENT PARTS:SHEARTIE P/N 146A3010-171, AND CLIPS P/N 146A1310-63, 146A1310-46,146A1310-48, 146A3500-57 (2EA). NEED OK TO INTALL THESE PARTS
FUSELAGE FRAME CRACKED AT STA.847 AT BETWEEN S-27L AND S-27R. FABRICATED -1 REPAIR J. PERFORMED FLOURESCENT PEN. INSP. ON FORM VERIFIED PO#8852031 AND METAL .80-7175-0 C/W FPI IAW SOPM 20-20- 2 ON FORMED AREA. IAW AVO ESC1906120436-1 ITEM #5 NO DEFECTS NOT ED. TRIMMED OUT FRAME WEB CRACK IN REFERENCE TO AVO ESC1906120436-1A 5.A. 36-1A STEPS 5.B AND STEP 7. PERFORMED HFEC INSP. OF FRAME WEB AND CUTOUT PER AVO ESC19061204 PERFORMED HFEC HOLE PROBE INSP. OF REMOVED FASTENERS PER AVO ESC 1906120436-1A STEP 3. ACCOMPLISHED STEPS 3 , 5B AND 7 OF AVO#1906120436-1A ALL HFEC S TEPS ,NO LIMITING DEFECTS FOUND. PERFORMED .040 INSURANCE CUT, STEP 5.B OF AVO ESC1906120436-1A HFEC''S ACCOMPLISHED FOR FRAME WEB (STA 847) PER AVO ESC190612043 6-1A FOR STEP''S 3&5B&7 PER 737 NDT PART 6,51-00-00 #23 & #16. NO DEFECTS NOTED AFTER INSURANCE CUT. MATERIAL VERIFICATION OF -1 REPAIR ANGLE IS CLAD .071 7075-0 PER CURRENT AVO ESC1906120436-1B. STEP B.1A. PO OF-1 .071 CLAD 7075 REPAIR ANGLE IS 5417049317. MATERIAL VERICATION ACP ON STRUCTURAL REPAIR ANGLE PER AVO ESC19 0613-0436-1A NOTE B1. FORMED REPAIR ANGLE -1 PER AVO ESC1906120436-1B STEP B.1.B VERIFIED FORMED REPAIR ANGLE -1 STEP B.1.B., FPI ACCOMPLISHED PE R B.1.NOTE,PER AVO ESC1906120436-1C. REPAIR ANGLE -1 HEAT TREATED TO -T62 CONDITION AFTER FORMING REFERENCE HEAT TREAT FORM 43-0150 N
OVEN SMOKING OR SPARKING 204 OVEN NR 1 PSN 204 SMOKES AND SMELLS OF BURNT FOOD ODOR DISSIPATES WHEN TURNED OFF. REMOVED AND REPLACED OVEN AT POSITION 204 OPS CHECK.
L1 DOOR EXTERIOR EMERGENCY LIGHT INOPERATIVE. REPLACED THE BATTERY PACK. CHECKED OK IAW AMM 33-51-06-960-805.
EMERGENCY EXIT LIGHT AT THE LT WING EMERGENCY EXIT FORWARD AND AFT DOOR AND ROW 20 & 21 ABC DO NOT COME ON. R & R THE BATTERY PACK AT M1694, OPS TESTED GOOD IAW AMM 33-51-06- 960-805.
FLIGHT CONTROL COLUMN HAD AN ABNORMAL VIBRATION AT 10K, 250-310KTS. EXCESSIVE VIBRATION WORSENING WITH AIRSPEED. EMERGENCY DECLARED. INSPECTED AND FOUND THE NR 7 AND 8 RIGHT ELEVATOR ATTACH HINGE BEARING PLATES TO HAVE SOME PLAY. REMOVED AND REPLACED THE ELEVATOR ATTACH HINGE BEARING PLATES IAW AMM 27-31-11. ELEVATOR CHECKED GOOD AT THIS TIME.
OVEN SMOKING. REPLACED THE OVEN AND OPS CHECKED OK.
HFEC CRACK DETECTED, STATION 727B AT RBL 45.5, AFT OTBD SEAT TRACK FASTENER HOLE COMMON TO SPLICE STRAP. IAW EA 5320-02076 OP 4 STEP 4 SEE WIPS FOR DETAILS OF WORK ACCOMPLISHED. TRIMMED OUT CRACKED FLANGE OF SEAT TRACK & INSTALLED REPAIR SPLICES, STRAPS, FILLERS & MODIFIED REPLACEMENT SPLICE STRAP IAW ECRA 5320-02274.
SEAT TRACK STATION 727B RBL 24.75 BOTH FLANGES HAVE TWO HOLES WITH NO EDGE DISTANCE. SEE WIPS FOR DETAILS OF WORK ACCOMPLISHED. TRIMMED OUT CRACKED FLANGE OF SEAT TRACK & INSTALLED REPAIR SPLICES, STRAPS, FILLERS & MODIFIED REPLACEMENT STRAP IAW ECRA 5320-02274.
SEAT TRACK HOLE HAS A CRACK INDICATION STATION 727B AT AFT INBD HOLE LBL 24.75. INSTALLED SPLICE REPAIR AT LBL 24.75 & COMPLIED WITH REQUIREMENTS OF EA 5320-02076 REV B OP 3 & 4. SEE WIP FOR ALL WORK ACCOMPLISHED IAW ECRA 5320-2273.
SEAT TRACK AT STATION 727B LBL 45.50 BOTH FLANGES HAVE TWO HOLES WITH NO EDGE DISTANCE. INSTALLED SPLICE REPAIR AT LBL 45.50 & COMPLIED WITH REQUIREMENTS OF EA 5320-02076 REV B OP 3 & 4. SEE WIP FOR ALL WORK ACCOMPLISHED IAW ECRA 5320-2273.
CP FLOOR LATERAL INTERCOSTAL STATION 259 RBL 10 TO LBL 10 HAS CORROSION. REMOVED DAMAGE, DVI USING 10X MAG TO ENSURE CORROSION HAS BEEN REMOVED. ACCOMPLISHED FLUORESCENT PENETRANT INSPECTION NO CRACKS FOUND. TREATED, PRIMED & REINSTALLED NUTPLATES, COMPLIED WITH STEPS 1-7 OF ECRA 5311-01706.
RIGHT HORIZONTAL STAB STATION 157.10 CRACK INDICATION 30.5 FROM FRONT SPAR. REPAIRED RT HORIZONTAL STAB CRACK AT STATION 157.10, 30.5 FROM FRONT SPAR IAW SRM 55-10-01 REPAIR 11.
RIGHT HORIZONTAL STAB LOWER SKIN SHOWS CRACK INDICATION AT STAB STATION 101.9 & 28 INCHES FROM SPAR. REPAIRED CRACK ON RT HORIZONTAL STAB LOWER IN SPAR STATION 101.9, 28 INCHES FROM FRONT SPAR & APPLIED TOPCOAT FINISH IAW SRM 55-10-01 REPAIR 11.
LEFT HORIZONTAL STAB CRACK ON LOWER SKIN AT STATION 129.5,26 INCHES FROM FRONT SPAR. REPAIRED LT HORIZONTAL LOWER SKIN AT STATION 129.5 & APPLIED TOPCOAT FINISH IAW SRM 55-10-01 REPAIR 11.
EMERGENCY EXIT SIGN LENS AT R2 DOOR MISSING. MISSING LENS REPLACED. FOUND UNSHIELDED WIRES (3EA) BROKEN INSIDE ASSY. REPAIRED WIRES IN REF WITH SWP 20-10-13 PARA 4 P52 OPERATIONS NML.