N8676A
Registered owner: UMB BANK NA TRUSTEE, UT (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
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
230 reports on file, 2016-07-05 – 2026-08-19.
Part: WIRE — DETACHED (ZONE 200) · airframe 35,680 hrs · 17,805 cycles
L1 DOOR OUTSIDE EMERGENCY LIGHT INOPERATIVE. FOUND WIRE W3142-0151-16 REMOVED FROM GROUND BLOCK GD3876. RE-PINNED WIRE TO GROUND BLOCK AND OPS CHECK OF EMERGENCY LIGHT L731 IS GOOD IAW WDM 33-51-12, SWPM 20-90-11, AND AMM 33-51-00-710-801.
Part: HANDLE — LOOSE (ZONE 800) · airframe 35,680 hrs · 17,805 cycles
ASSIST HANDLE ON G1 GALLEY LOOSE. SECURED ASSIST HANDLE ON G1 GALLEY IAW AMM 25-31-11-400-801 SUBTASK 25-31-11-410-016.
Part: SKIN — DELAMINATED (ZONE 500 FLAP) · airframe 35,680 hrs · 17,805 cycles
FOUND LEFT OTBD AFT FLAP DELAMINATED. REMOVED AND REPLACED LT OTBD AFT FLAP IAW AMM 27-51-22-401.
Part: HANDLE — UNSECURE (ZONE 800) · airframe 35,680 hrs · 17,805 cycles
R2 DOOR AIRFRAME SIDE ASSIST HANDLE NEEDS SECURED. SECURED ASSIST HANDLE AT R2 DOOR AIRFRAME SIDE IAW AMM 25-21-25-420-801.
Part: LAMP — INOPERATIVE (ZONE 200) · airframe 35,680 hrs · 17,805 cycles
L2 EXTERNAL EMERGENCY LIGHT IS INOPERATIVE. REPLACED THE LAMPS, OP CHECKED L2 DOOR EXTERNAL EMERGENCY LIGHT IAW AMM 33-51-04-960-801. EMERGENCY LIGHT. OPS CHECKED GOOD.
Part: HANDLE — UNSECURE (ZONE 800) · airframe 35,680 hrs · 17,805 cycles
L1 DOOR ASSIST HANDLE NEEDS SECURED. SECURED ASSIST HANDLE AT L1 DOOR IAW AMM 52-11-31-400-802 SUBTASK 52-11-31-020-011.
Part: HANDLE — UNSECURE (ZONE 800) · airframe 35,680 hrs · 17,805 cycles
L2 DOOR AIRFRAME SIDE ASSIST HANDLE NEEDS SECURED SECURED ASSIST HANDLE ON AIRFRAME SIDE AT L2 DOOR IAW AMM 25-21-25-420-801 SUBTASK 25-21-25-420-004 SECURED ASSIST HANDLE ON AIRFRAME SIDE AT L2 DOOR IAW AMM 25-21-25-420-801 SUBTASK 25-21-25-420-004.
Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 35,680 hrs · 17,805 cycles
FOUND RT OTBD AFT FLAP DELAMINATED. REMOVED AND REPLACED RT OTBD AFT FLAP IAW AMM 27-51-22.
Part: LENS — DAMAGED (ZONE 200) · airframe 35,680 hrs · 17,805 cycles
FORWARD L1 DOOR EXIT LENS REQUIRES REPLACEMENT. REMOVED AND REPLACED THE FWD L1 DOOR EXIT LIGHT LENS IAW AMM 33-51-01-960-801.
Part: LAMP — INOPERATIVE (ZONE 200) · airframe 35,680 hrs · 17,805 cycles
L1 DOOR EXTERNAL EMERGENCY LIGHT IS INOPERATIVE. REPLACED THE LAMPS, OPS CHECKED L1 DOOR EXTERNAL EMERGENCY LIGHT IAW AMM 33-51-04-960-801. OPS CHECKED GOOD.
Part: RELAY — FAILED (ZONE 300) · airframe 33,550 hrs · 16,703 cycles
ELECTRIC STAB TRIM FAIL DURING CLIMB OUT, AUTOPILOT WAS NOT ENGAGED. NEITHER CAP OR FO ELECTRIC STAB TRIM WAS OPERATIONAL. MANUAL TRIM OPERATED NORMALLY. R & R R64 STAB TRIM CONTROL RELAY IAW WDM 27-41-12. NO DEFECTS NOTED.
Earlier reports · 2016–2025 · 219 reports
2025
Part: COVER — LOOSE (ZONE 800) · airframe 33,345 hrs · 16,609 cycles
FWD SERVICE DOOR EXIT COVER (LOWER) CAME OFF. SECURED FWD SERVICE DOOR EXIT COVER IAW MM 33-51-01
Part: TRIM MOTOR — INOPERATIVE (ZONE) · airframe 33,287 hrs · 16,579 cycles
CREW REPORTS STAB TRIM INOPERATIVE, WORKS WITH AUTOPILOT. R & R STABILIZER TRIM MOTOR IAW AMM 27-41-71. TESTED GOOD IAW AMM 27-41-71-700-801.
Part: BULB — INOPERATIVE (ZONE 200) · airframe 32,867 hrs · 16,363 cycles
EXTERIOR EMERGENCY LIGHT, AFT OF L2 DOOR NO ILLUMINATION DURING EMERGENCY LIGHT OPS CHK. PLACED THE BULB IAW MM 33-51-00.
Part: BATTERY — INOPERATIVE (ZONE 200) · airframe 32,435 hrs · 16,132 cycles
LH EMERGENCY. EXIT LIGHTS INOPERATIVE. R & R EMERGENCY LIGHT BATTERY AT LT 12CBA POSITION.
Part: SENSOR — FAULTY (ZONE 100) · airframe 31,661 hrs · 15,714 cycles
LE FLAP TRANSIT LIGHT CAME ON WHEN FLAPS 15 SELECTED AND STAYED ON <[01]. R&R #4 LEADING EDGE FLAP PROXIMITY SENSOR REF AMM 27-88-11. OPS CHECK GOOD.
2024
Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 29,980 hrs · 14,805 cycles
FORWARD ENTRY DOOR SLIDE EMERGENCY LIGHT INOP<[01] RE LAMPED FORWARD ENTRY DOOR SLIDE EMERGENCY LIGHT;OPS CHECKS GOOD PER MM 33-51-04;[02] RE LAMPED FORWARD ENTRY DOOR SLIDE EMERGENCY LIGHT;OPS CHECKS GOOD PER MM 33-51-04. ADDED SELECT REFERENCE.;[03] VERIFIED
Part: MEGAPHONE — BROKEN (ZONE 200) · airframe 29,980 hrs · 14,805 cycles
FORWARD CABIN MEGAPHONE HANDLE IS BROKEN AWAY FROM HORN.<[01] REPLACED FWD CABIN MEGAPHONE IN REFERENCE TO AMM 25-64-00.;[02] ROBERT WALESA (TECHNICIAN); 19-DEC-2024 18:57 UTC<BR>REPLACED FWD CABIN MEGAPHONE IN REFERENCE TO AMM 25-64-00.
Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 29,980 hrs · 14,805 cycles
RIGHT OVER WING EXIT EMERGENCY LIGHTS INOP<[01] REMOVED AND REPLACED RIGHT OVER WING EMERGENCY LIGHT BATTERY PACK;ROW 13R PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00;[02] INSPECTED WORK PERFORMED
Part: CHANNEL — CRACKED (ZONE 200) · airframe 29,980 hrs · 14,805 cycles
FLOORBOARD SUPPORT CHANNEL CRACKED AT I/B ATTACH POINT AT APPROXIMATELY STA. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT LBL 24.82.<[01] REMOVED DAMAGE FLOOR BOARD SUPPORT (BREAK ASSY-PNL) AT ST. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT LBL 24.82 IAW SRM 51-40-02.;[02] LOCATED AND DRILLED NEW FLOOR BOARD SUPPORT ( BREAK ASSY-PNL) IAW SRM 51-40-05.;[03] C/W INSPECTION OF C/A #1 AND #2;[04] OK TO INSTALL GIVEN;[05] INSTALLED NEW FLOOR BOARD SUPPORT (BREAK ASSY-PNL);AT STA. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT LBL 24.82 IAW SRM 51-40-02.;[06] C/W INSPECTION OF C/A #5
Part: CHANNEL — CRACKED (ZONE 200) · airframe 29,980 hrs · 14,805 cycles
FLOORBOARD SUPPORT CHANNEL CRACKED AT I/B ATTACH POINT AT APPROXIMATELY STA. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT RBL 24.82.<[01] REMOVED DAMAGE FLOOR BOARD SUPPORT (BREAK ASSY-PNL) AT ST. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT RBL 24.82 IAW SRM 51-40-02.;[02] LOCATED AND DRILLED NEW FLOOR BOARD SUPPORT ( BREAK ASSY-PNL) IAW SRM 51-40-05.;[03] C/W INSPECTION OF C/A #1 AND #2;[04] OK TO INSTALL GIVEN;[05] INSTALLED NEW; REMOVED AND REPLACED FLOOR BOARD SUPPORT (BREAK ASSY-PNL);AT STA. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT RBL 24.82;[06] INSTALLED NEW; REMOVED AND REPLACED FLOOR BOARD SUPPORT (BREAK ASSY-PNL);AT STA. 540 BETWEEN FLOOR BEAM AT LBL 0.07 TO SEAT TRACK FLOOR BEAM AT RBL 24.82 IAW SRM 51-40-02.;[07] C/W INSPECTION OF C/A #5 AND #6
Part: ATTACH BRACKET — CRACKED (ZONE 500) · airframe 29,980 hrs · 14,805 cycles
DEFLECTION RIB ATTACH BRACKET IS CRACKED<[01] REMOVED DAMAGED BRACKET PER SRM 51-40-02.;[02] REMOVED AND REPLACED DEFLECTION RIB ATTACH CLIP PER SRM 51-40-02.;[03] 2. THOMAS BAUER (TECHNICIAN); 07-DEC-2024 21:25 UTC<BR>REMOVED AND REPLACED DEFLECTION RIB ATTACH CLIP PER SRM 51-40-02
Part: BRACKET — CRACKED (ZONE 400) · airframe 29,980 hrs · 14,805 cycles
PANEL 414 FAN COWL ASSY. #1 ENGINE INBOARD: OIL DOOR WIND DEFLECTOR BRACKET IS CRACKED. MARKED. PANEL 414 FAN COWL ASSY. #1 ENGINE INBOARD: OIL DOOR WIND DEFLECTOR BRACKET IS CRACKED. MARKED.<[01] #1 ENGINE I/B (R/H) FAN COWL WAS REPLACED ON TASK CARD TTG8Q00S5H1Q (LINE#55); NO FURTHER ACTION REQUIRED;[02] C/W INSPECTION
Part: MOUNT BRACKET — CRACKED (ZONE 500) · airframe 29,980 hrs · 14,805 cycles
PANEL 551FB HAS A CRACKED MOUNTING ANGLE. REMOVED AND REPLACED MOUNTING BRACKET PER SRM 51-40-02. INSPECTED WORK PERFORMED. REMOVED AND REPLACED MOUNTING BRACKET PER SRM 51-40-02.
Part: FLOOR PANEL — DELAMINATED (ZN 200 FUS TOP) · airframe 29,980 hrs · 14,805 cycles
CENTER CABIN FLOOR PANEL 241 KF DELAMINATED<[01] REMOVED AND REPLACED WITH NEW SERVICEABLE FLOOR PANEL 241KF PER AMM 53-21-00.;[02] COMPLIED WITH CORRECTIVE ACTION #1.
Part: FLOOR PANEL — DELAMINATED (ZN 200 FUS TOP) · airframe 29,980 hrs · 14,805 cycles
CENTER CABIN FLOOR PANEL 241 GF DELAMINATED<[01] REMOVED AND REPLACED WITH NEW SERVICEABLE FLOOR PANEL IAW AMM 53-21-00.;[02] C/W INSPECTION
Part: FLOOR PANEL — DELAMINATED (ZN 200 FUS TOP) · airframe 29,980 hrs · 14,805 cycles
CENTER CABIN FLOOR PANEL 241 RF DELAMINATED<[01] REMOVED AND REPLACED FLOOR PANEL PER AMM 53-21-00-400-801.;[02] COMPLIED WITH CORRECTIVE ACTION#1.
Part: ATTACH ANGLE — CRACKED (ZONE 600) · airframe 29,980 hrs · 14,805 cycles
RW DEFLECTION CONTROL RIB; INBOARD AFT ATTACH ANGLE CRACKED RW DEFLECTION CONTROL RIB INBOARD AFT ATTACH ANGLE CRACKED<[01] REMOVED AND REPLACED INBOARD AFT ATTACH ANGLE PER SRM 51-40-02.;[02] VERIFIED REPLACEMENT OF THE INBOARD AFT ATTACH ANGLE BRACKET PER SRM 51-40-02.
Part: ANGLE — CRACKED (ZONE 500) · airframe 29,980 hrs · 14,805 cycles
L/H WING DEFLECTION RIB; UPPER PANEL; CENTER COVE RIB ANGLE CRACKED(BACKSIDE).<[01] REMOVED CRACKED ANGLE PER SRM 51-40-02.;[02] REMOVED AND REPLACED INBD.DEFLECTION RIB CENTER COVE ATTACH ANGLE PER SRM 51-40-02.;[03] THOMAS BAUER (TECHNICIAN); 08-DEC-2024 01:39 UTC<BR>REMOVED AND REPLACED INBD.DEFLECTION RIB CENTER COVE ATTACH ANGLE PER SRM 51-40-02.
Part: ATTACH ANGLE — CRACKED (ZONE 600) · airframe 29,980 hrs · 14,805 cycles
RW TE COVE; FIRST RIB INBOARD OF THE DEFLECTION CONTROL RIB (ORSS 275); UPPER INBOARD SIDE OF THE RIB ATTACH ANGLE IS CRACKED RW TE COVE FIRST RIB INBOARD OF THE DEFLECTION CONTROL RIB (ORSS 275) UPPER INBOARD SIDE OF THE RIB ATTACH ANGLE IS CRACKED<[01] REMOVED AND REPLACED CRACKED ATTACH ANGLE PER SRM 51-40-02.;[02] VERIFIED THE REPLACEMENT OF THE ATTACHED ANGLE BRACKET PER SRM 51-40-02.
Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 29,980 hrs · 14,805 cycles
PANEL 661BB HAS SEVERAL FASTENER HOLES DAMAGED ; PULLED SURFACE & CRACKING.<[01] FILLED DAMAGED HOLES; APPLIED PRE-PREG REPAIR PLIES AND COOKED REPAIR PER SRM 51-70-05-2R-9.;[02] ENTERED IN ERROR;[03] REPAIRED DAMAGED FASTENER HOLES PER SRM 51-70-05-2R-9.;[04] VERIFIED REPAIR OF HOLES PER SRM 51-70-05-2R-9.;[05] OK TO RESIN SEAL REPAIR PER SRM 51-70-08-0G-0;[06] OK TO APPLY RESIN CA# 5;[07] APPLIED RESIN SEAL AND DECORATIVE FINISH PER SRM 51-70-08-0G-0;[08] INSPECTED APPLIED RESIN SEAL AND DECORATIVE FINISH PER SRM 51-70-08-0G-0
Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 29,980 hrs · 14,805 cycles
R/H A/C BAY AFT WALL STA 663 AND APPROX. RBL 8 VAPOR BARRIER ATTACH ANGLE IS CRACKED AT RIVET HOLE IN VERTICAL FLANGE.<[01] CUT AND REMOVED DAMAGED SECTION OF ATTACH ANGLE IAW SRM 57-10-10-2R-5;[02] COMPLIED WITH SURFACE INSPECTION OF CUTOUT AND HOLE PROBE INSPECTION PER NDT MANUAL PART6 51-00-00 PROCEDURE 16 AND 23. NO DEFECTS NOTED;[03] FABRICATED PARTS IAW SRM 57-10-10-2R-5;[04] VERIFIED FABRICATED REPAIR PARTS IAW SRM 57-10-10-2R-5; OK TO INSTALL.;[05] REPAIRED IAW SRM 57-10-10-2R-5 AND EA# M-24-157-02340;[06] EDIT MEASUREMENTS;[07] C/W INSPECTION;[08] C/W INSPECTION
Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 29,980 hrs · 14,805 cycles
L/H A/C BAY AFT WALL STA 663 AND APPROX. LBL 8 VAPOR BARRIER ATTACH ANGLE IS CRACKED AT RIVET HOLE IN VERTICAL FLANGE.<[01] CUT AND REMOVED DAMAGED SECTION OF ATTACH ANGLE IAW SRM 57-10-10-2R-5;[02] COMPLIED WITH SURFACE INSPECTION OF CUTOUT AND HOLE PROBE INSPECTION PER NDT MANUAL PART6 51-00-00 PROCEDURE 16 AND 23. NO DEFECTS NOTED;[03] FABRICATED PARTS IAW SRM 57-10-10-2R-5;[04] VERIFIED FABRICATED REPAIR PARTS IAW SRM 57-10-10-2R-5; OK TO INSTALL.;[05] REPAIRED IAW SRM 55-10-10-2R-2 AND EA# M-24-157-02340;[06] C/W INSPECTION;[07] C/W INSPECTION
Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 27,339 hrs · 13,373 cycles
CEILING EMRGCY LTS INOP @ ROW 18;21 DEF<[01] R/R EMRGCY LT BATT PACK @ ROW 20 DEF PER AMM 33-51-06. LIGHT OPS - OK.
2023
Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
FWD CABIN EMERGENCY LIGHTS BATTERY PACK AT STA 565L IS INOP<[01] REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK AT STA 565L PER MM 33-51-06.EMERGENCY LIGHTS OPS CHECKED GOOD PER MM 33-51-06;[02] INSPECTED AS REQUIRED
Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
FWD CABIN EMERGENCY LIGHT BATTERY PACK AT STA 565R IS INOP<[01] REMOVED AND REPLACE EMERGENCY LIGHT BATTERY PACK AT STA 565R PER MM 33-51-06.EMERGENCY LIGHTS OPS CHECKED GOOD PER MM 33-51-06;[02] INSPECTED AS REQUIRED
Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
AFT GALLEY R/H EMERGENCY LIGHT BATTERY PACK INOP<[01] REMOVED AND REPLACED EMAERGENCY LIGHT BATTERY PACK AT STA 952R PER MM 33-51-06;[02] AFT GALLEY EMERGENCY LIGHTS OPS CHECKED GOOD PER MM 33-51-06;[03] INSPECTED AS REQUIRED
Part: TRACK — CRACKED (ZN 300 STABILIZE) · airframe 26,986 hrs · 13,173 cycles
R/H HORIZONTAL STAB UPPER AFT BLADE SEAL FWD TRACK IS CRACKED.<[01] INSTALLED R/H HORIZONTAL STAB UPPER AFT BLADE SEAL FWD TRACK PER SRM 51-40-02;[02] VERIFIED INSTALLATION OF NEW R/H HORIZONTAL STAB UPPER AFT BLADE SEAL FWD TRACK PER SRM 51-40-02
Part: STRINGER — INCORRECT (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
BS 727 INNER CHORD AT STRINGER 18A RIGHT SIDE GAP IS 0.045' AT THE UPPER AND 0.040' AT THE BOTTOM<[01] REPAIRED PER EO-5311-E-14625-NG ON FAULT #TTG8Q00Q4Z2Z.;[02] VERIFIED ALL WORK STEPS COMPLETED ON EO-5311-E-14625-NG
Part: STRINGER — INCORRECT (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
BS 727 INNER CHORD AT STRINGER 18A LEFT SIDE GAP IS 0.018'<[01] REPAIRED PER EO-5311-E-14577-NG.;[02] REPAIRED PER EO-5311-E-14577-NG ON FAULT #TTG8Q00Q4Y4H.;[03] INSPECTED AS REQUIRED
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
FWD CARGO RH TRANSITION ANGLE HAS CORROSION FROM STA. 500E TO 500F.<[01] BLENDED AREAS; REMOVED .010' MATERIAL; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] REMOVED DAMAGE FROM STA. 500D+10 TO 500F+10 PER SRM 53-00-53-2R-5. FABRICATED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA EA M-22-153-01550.;[03] RII INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2;[04] RII OK TO INSTALL REPAIR PARTS.;[05] REMOVED DAMAGE FROM STA. 500D+10 TO 500F+10 PER SRM 53-00-53-2R-5. FABRICATED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA EA M-22-153-01550. INSTALLED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA M-22-153-01550.;[06] C/W INSPECTION.;[07] REMOVED DAMAGE FROM STA. 500D+10 TO 500F+10 PER SRM 53-00-53-2R-5. FABRICATED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA EA M-22-153-01550. INSTALLED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA M-22-153-01550.;[08] RII; COMPLIED WITH INSPECTION; REMOVED DAMAGE FROM STA. 500D+10 TO 500F+10 PER SRM 53-00-53-2R-5. FABRICATED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA EA M-22-153-01550. INSTALLED REPAIR PARTS PER SRM 53-00-53-2R-5 AND EA M-22-153-01550.
Part: PLATE — LOOSE (ZN 800 DOOR) · airframe 26,986 hrs · 13,173 cycles
AFT SERVICE DOOR INTERNAL HANDLE CAMPLATE LOOSE.<[01] SECURED CAMPLATE PER M/M REF 52-41-11;[02] C/W INSPECTION.
Part: FASTENER — LOOSE (ZN 800 DOOR) · airframe 26,986 hrs · 13,173 cycles
FORWARD ENTRY DOOR ESCAPE SLIDE RIGHT HAND GIRT BAR BRACKET LOOSE.<[01] R/R FASTENER IAW SRM 51-40-02.;[02] C/W INSPECTION.
Part: NUT — INOPERATIVE (ZN 800 DOOR) · airframe 26,986 hrs · 13,173 cycles
FORWARD ENTRY DOOR ESCAPE SLIDE FORWARD MOUNT BARREL NUT BAD.<[01] REPLACED BARREL NUT PER SOPM 20-50-01.;[02] C/W INSPECTION.
Part: LINER — TORN (R1 DOOR) · airframe 26,986 hrs · 13,173 cycles
FWD SERVICE DOOR (R-1) LINER TEDLAR COVERING TORN IN 2 AREAS. (SLIDE MOUNT FASTENER AND HANDLE AREAS MARKED)<[01] REMOVED AND REPLACED LINER PER M/M REF 52-41-31;[02] NEW DOOR LINER TO BE INSTALLED ON FAULT TTG8R007M6VR.
Part: FLOOR PANEL — DELAMINATED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
FOLLOWING FWD WET AREA FLOOR BOARDS HAVE DENTS/DELAMINATION; 231CF; 231BF; 231AF; 222DF; 222CF; 221GF; 221FF; 221EF; 221CF; AND 221DF.<[01] REPLACED FLOOR PANEL 231AF ON TTG8Q00P6GLG.<BR>REPLACED FLOOR PANEL 231BF ON TTG8Q00P6GLE.<BR>REPLACED FLOOR PANEL 231CF ON TTG8Q00P6GLC.;[02] CORRECTION TO C/A #1 -<BR>NEW FLOOR PANEL 231AF INSTALLED ON TTG8Q00P6GLG.<BR>NEW FLOOR PANEL 231BF INSTALLED ON TTG8Q00P6GLE.<BR>NEW FLOOR PANEL 231CF INSTALLED ON TTG8Q00P6GLC;[03] COMPLIED WITH CORRECTIVE ACTION #1 AND #2.;[04] NEW FLOOR PANEL 222DF INSTALLED ON TTG8Q00P6GLN<BR>NEW FLOOR PANEL 222CF INSTALLED ON TTG8Q00P6GLQ<BR>NEW FLOOR PANEL 221GF INSTALLED ON TTG8Q00P6GLS<BR>NEW FLOOR PANEL 221FF INSTALLED ON TTG8Q00P6GLU<BR>NEW FLOOR PANEL 221EF INSTALLED ON TTG8Q00P6GLW<BR>NEW FLOOR PANEL 221CF INSTALLED ON TTG8Q00P6GM0<BR>NEW FLOOR PANEL 221DF INSTALLED ON TTG8Q00P6GLY;[05] VERIFIED PANELS CLOSED. SIGN OFF FOR CORRECTIVE ACTION #4 ONLY.
Part: FLOOR PANEL — DELAMINATED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
221BF AND 221AF FWD WET AREA FLOOR BOARDS HAVE DENTS/DELAMINATION.<[01] NEW FLOOR PANEL 221BF INSTALLED ON TTG8Q00P6GMR<BR>NEW FLOOR PANEL 221AF INSTALLED ON TTG8Q00P6GM4;[02] NEW FLOOR PANEL 221BF INSTALLED ON TTG8Q00P6GM2<BR>NEW FLOOR PANEL 221AF INSTALLED ON TTG8Q00P6GM4;[03] VERIFIED PANELS CLOSED SIGN OFF CORRECTIVE ACTION # 2.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+2 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+1.25 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+13 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+2 RBL 21 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED REF TTG8Q00Q22PQ.;[03] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[04] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2 AND #3
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+6 RBL 20 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .005IN MATERIAL; REMAINING THICKNESS OF .035 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED REF TTG8Q00Q22PQ.;[03] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[04] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2 AND #3
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+3 RBL 21 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE FOUND TO BE OUT OF LIMITS PER SRM 53-00-52-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE 727B+15.5 RBL 20 WL 156. MRKD<[01] PART REPLACED OUT TO LIMITS PLEASE SEE TTG8Q00Q22PQ FOR CORRECTIVE ACTION;[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+19 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+9 RBL 21 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED REF TTG8Q00Q22PQ.;[03] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[04] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2 AND #3
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+2 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+14.5 LBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+15.5 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+16.25 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727E+9 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+18.75 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+18.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 757.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+6.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+13 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED REF (TTG8Q00Q22QW).;[02] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[03] C/W INSPECTION OF C.A. STEP 2 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+16 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+13 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+18 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+14 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+14.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+6 RBL 21 WL 156. MRKD<[01] REMOVED CORROSION ON AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE AT STA 727G +6? RBL 21. ORIGINAL THICKNESS IS 0.040?. MAX MATERIAL REMOVED 0.007. MAX ALLOWED 0.004. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] R/H TRANSITION ANGLE FROM STA 727 +4? TO STATION 767 TO BE REPLACED ON TTG8Q00Q22PQ;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 779 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+20 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+14.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT RIVET HEAD STA 727G RBL 21 WL 156. MRKD<[01] REMOVED CORROSION FROM AFT CARGO R/H TRANSITION ANGLE ATTACH FASTENER HOLE AT STA 727G RBL 21. ORIGINAL THICKNESS IS 0.040?. MAX MATERIAL REMOVED 0.006?. MAX ALLOWED 0.004. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] R/H TRANSITION ANGLE FROM STA 727 +4? TO STA 767 TO BE REPLACED ON TTG8Q00Q22PQ;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+16 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 797.5 LBL 21 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+7.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 792.5 LBL 20 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 765.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 769 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 779.75 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 801.5 LBL 21 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: PANEL — CRACKED (ZN 300 STABILIZE) · airframe 26,986 hrs · 13,173 cycles
PANEL 343FB HAS CRACKING AT FASTENER HOLE(MARKED)<[01] REMOVED DAMAGE FROM FASTENER HOLE ON PANEL 343FB IAW SRM 51-70-05-2R-9;[02] VERIFIED DAMAGE REMOVED FROM FASTENER HOLE ON PANEL 343FB IAW SRM 51-70-05-2R-9.;[03] REPAIRED DAMAGED FASTENER HOLE ON PANEL 343FB IAW AMM 51-70-05-2R-9;[04] INSPECTED C/A 3. REPAIRED DAMAGED FASTENER HOLE ON PANEL 343FB IAW AMM 51-70-05-2R-9;[05] RESTORED FINISH TO REPAIRED AREA ON PANEL 343FB PER M.M. 51-21-99;[06] INSPECTED AS REQUIRED. CORRECTED ACTION #5
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 753.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 752.25 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 749.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+10.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+8.75 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 770.5 LBL 21 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 777.5 LBL 21 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 783.25 LBL 20 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+6 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+20 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE 727B+12 RBL 20 WL 156. MRKD<[01] PART REPLACED OUT TO LIMITS PLEASE SEE TTG8Q00Q22PQ FOR CORRECTIVE ACTION;[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+2 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+9 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+20 RBL 21 WL 156. MRKD<[01] REMOVED CORROSION FROM AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE STA 727F +20? RBL 21. ORIGINAL THICKNESS IS 0.040?. MAX MATERIAL REMOVED 0.007?. MAX ALLOWED 0.004?. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2;[02] R/H TRANSITION ANGLE FROM STA 727 +4? TO STA 767 TO BE REPLACED ON TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+16 RBL 21 WL 156. MRKD<[01] REMOVED CORROSION FROM AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE STATION 727F +16? RBL 21. ORIGINAL THICKNESS IS 0.040?. MAX MATERIAL REMOVED 0.006?. MAX ALLOWED IS 0.004?. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53?1A-2;[02] R/H TRANSITION ANGLE FROM STA 727 +4? TO STA 767 TO BE REPLACED ON TTG8Q00Q22PQ;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+6 RBL 21 WL 156. MRKD<[01] REMOVED CORROSION FROM AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE STA 727F +6 RBL 21. ORIGINAL THICKNESS IS 0.040?. MAX MATERIAL REMOVED 0.005?; MAX ALLOWED 0.004?. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2;[02] R/H TRANSITION ANGLE FROM STATION 727 +4? TO STATION 767 TO BE REPLACED ON TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+9 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727E+20 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 749 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+16 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 761.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 775 LBL 20 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+21.25 LBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 776.5 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 783 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 785.5 LBL 21 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+8.75 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+3 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727D+7.5 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+15.75 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+10.25 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727E+16 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+2.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+18 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+1.75 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+6 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+13 RBL 20 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727E+13 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+13 RBL 21 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 783 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 771 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 775 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 766 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ;[03] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9
Part: FLOORBEAM — CORRODED (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
FLOOR BEAM BS947 CORRODED UNDER AND AROUND LAV MOUNT RBL50.5<[01] REMOVED CORROSION ON TOP OF UPPER CHORD OF FLOOR BEAM STA 947.5 RBL 50.5 (REMOVED 0.039? OF .180? MATERIAL) FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1.;[02] INSPECTION C/W REMOVED CORROSION ON TOP OF UPPER CHORD OF FLOOR BEAM STA 947.5 RBL 50.5 (REMOVED 0.039? OF .180? MATERIAL) FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1.;[03] C/W FALLOW UP INSPECTION OF REPAIR AREA; FALLOWING DAMAGE REMOVAL.;[04] BLENDED DAMAGED AREA ON TOP OF UPPER CHORD OF FLOOR BEAM STA 947.5 RBL 51 IAW SRM 53-70-51-2R-8 ALTERNATIVE 3.;[05] VERIFIED DAMAGE BLEND OUT (CA #4).;[06] ACCOMPLISHED HFEC HOLE PROBE AND SURFACE INSPECTION OF REPAIR AREA PER NDT PART 6 51-00-00 PROC. 16 AND 51-00-00 PROC. 23 NO DEFECTS NOTED;[07] REMOVED ADDITIONAL .002' IAW SRM 51-10-02.;[08] FLAP PEENED BLENDED AREA IAW SOPM 20-10-03.;[09] FABRICATED SHIM AND LOCATED/DRILLED FASTENER HOLES IAW SRM 51-40-05.;[10] C/W C/A #7;8;9;[11] REPAIRED IAW SRM 53-70-51-2R-8.;[12] C/W INSPECTION.;[13] C/W INSPECTION.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+7.5 RBL 20 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE FOUND TO BE OUT OF LIMITS PER SRM 53-00-52-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+20 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+10.25 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+10.25 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+10 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+18 LBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+20 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 789.5 LBL 21 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+16 RBL 21 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+16 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+20 RBL 21 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 882.5 RBL 20 WL 164. MRKD<[01] REMOVED SURFACE CORROSION AT AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE AT STA 882.5 RBL 20 WL 164.;[02] REMOVED SURFACE CORROSION AT AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE AT STA 882.5 RBL 20 WL 164 PER SRM 53-00-53-1A-2;[03] ALODINED AND PRIMED DISCREPANT AREA IAW SRM 51-20-01 AND SOPM 20-41-02;[04] REMOVED SURFACE CORROSION AT AFT CARGO R/H TRANSITION ANGLE AT N/P HOLE AT STA 882.5 RBL 20 WL 164; PART WAS DETERMINED TO BE WITHIN LIMITS PER SRM 53-00-53-1A-2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+19.75 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+14.25 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+5.75 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+19 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+16.5 RBL 20 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .006IN MATERIAL; REMAINING THICKNESS OF .034 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+9 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 781.5 LBL 21 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 755.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+1 RBL 20 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE FOUND TO BE OUT OF LIMITS PER SRM 53-00-52-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+5.25 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+19.5 LBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE 727D+1 LBL 20 WL 156. MRKD<[01] OKAY TO INSTALL NEW TRANSITION ANGLE PER SRM 51-40-02;[02] OK TO INSTALL NEW TRANSITION ANGLE L/H STA.727-849;[03] INSTALLED NEW TRANSITION ANGLE L/H STA. 727-849 IAW SRM 51-40-02;[04] INSTALLED NEW TRANSITION ANGLE L/H STA. 727-849 IAW SRM 51-40-02;[05] INSPECTED INSTALLED NEW TRANSITION ANGLE L/H STA. 727-849
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+2.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+18.75 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+6 LBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 793.5 LBL 21 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+18.5 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727J+12 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+5.5 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+13 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+19.75 RBL 20 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+13 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+9.5 RBL 20 WL 156. MRKD<[01] .040IN ORIGINAL THICKNESS; REMOVED .005IN MATERIAL; REMAINING THICKNESS OF .035 IN. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED REF TTG8Q00Q22PQ.;[03] THIS TRANSITION ANGLE WAS REMOVED AND REPLACED PER SRM 51-40-02 REF TTG8Q00Q22PQ.;[04] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 #2 AND #3
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 770.5 LBL 20 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 786 RBL 20 WL 156. MRKD<[01] REMOVED R/H TRANSITION ANGLE IAW SRM 51-40-02 <BR>LOCATED AND DRILLED NEW R/H TRANSITION ANGLE IAW SRM 51-40-10;[02] INSTALLED NUTPLATES PER SRM 51-40-02;[03] REMOVED R/H SHIELD PER SRM 51-40-02 <BR>LOCATED AND DRILLED SHIELD PER SRM 51-40-10<BR>INSTALLED NUTPLATES ON NEW SHIELD PER SRM 51-40-02;[04] VERIFIED C/A # 3 : . STEVEN POULIN (TECHNICIAN); 09-DEC-2023 07:02 UTC<BR>REMOVED R/H SHIELD PER SRM 51-40-02<BR>LOCATED AND DRILLED SHIELD PER SRM 51-40-10<BR>INSTALLED NUTPLATES ON NEW SHIELD PER SRM 51-40-02;[05] GRANTED : OK TO INSTALL;[06] INSTALLED R/H SHIELD IAW SRM 51-40-02;[07] INSTALLED R/H SHIELD IAW SRM 51-40-02;[08] VERIFIED C/A # 7 : STEVEN POULIN (TECHNICIAN); 09-DEC-2023 10:30 UTC<BR>INSTALLED R/H SHIELD IAW SRM 51-40-02
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+18 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW)
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727H+20 LBL 21 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 789 LBL 20 WL 159. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+3 RBL 20 WL 156. MRKD<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE FOUND TO BE OUT OF LIMITS PER SRM 53-00-52-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ;[02] INSPECTION COMPLETE ON CORRECTIVE ACTION #1 FOR: BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. TRANSITION ANGLE TO BE REPLACED ON FAULT #TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 775 LBL 21 WL 157. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
FORWARD CARGO RIGHT TRANSITION ANGLE HAS CORROSION AT BS 500F TO 500G.<[01] BLENDED AREAS; REMOVED .010' MATERIAL; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-2R-5.;[02] DAMAGE REMOVED FROM STA. 500D+10 TO 500F+10 . REPAIR TO BE ACCOMPLISHED ON NR# TTG8Q00Q4FZS.;[03] INSPECTED AS REQUIRED. CORRECTIVE ACTION #1 AND #2. VERIFIED REPAIR ACCOMPLISHED ON TTG8Q00Q4FZS
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727D+6 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 786.75 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 773.25 RBL 20 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9.;[02] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q24G9
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+13 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 727I+12.25 LBL 20 WL 156. MRKD<[01] THIS TRANSITION ANGLE IS REMOVED AND REPLACED PER SRM 51-40-02 REF (TTG8Q00Q22QW);[02] C/W INSPECTION OF C.A. STEP 1 (AMT MICHAEL PETERSON) OF THE REPLACED TRANSITION ANGLE PER SRM 51-40-02.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO R/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE AT STA 759.5 RBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22PQ.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727F+6 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,986 hrs · 13,173 cycles
AFT CARGO L/H TRANSITION ANGLE HAS CORROSION AT N/P HOLE STA 727G+9 LBL 21 WL 156. MRKD<[01] REPAIR ACCOMPLISHED ON CARD TTG8Q00Q22QW.
Part: SUPPORT — CORRODED (ZN 200 FUS TOP) · airframe 26,986 hrs · 13,173 cycles
AFT LAV MOUNT SUPPORT STRUCTURE CORRODED @ RBL50 BS949<[01] MEASURED DAMAGE AND FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1.;[02] DRILLED UP REPLACEMENT INTERCOSTAL PER SRM 51-40-05. COUNTERSUNK APPLICABLE HOLES PER SRM 51-40-08.;[03] R/R INTERCOSTAL IAW SRM 51-40-02.;[04] C/W INSPECTION.
Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,444 hrs · 12,853 cycles
LH AFT OVERWING EMER. EXIT LIGHT & ROWS 16-22 EMER.CEILING LIGHTS INOP<[01] R&R M1670 BATTERY PACK & CHARGER PER AMM 33-51-06 OPS CHECK GOOD
Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,316 hrs · 12,775 cycles
AFT ENTRY DOOR AND GALLEY EMERGENCY LIGHTS INOP<[01] REMOVED AND REPLACED AFT GALLEY ENTRY DOOR EMERGENCY LIGHT BATTERY PER AMM 33-52-06. OPS CHECK GOOD
Part: SEAL — CRACKED (ZN 300 STABILIZE) · airframe 25,388 hrs · 12,244 cycles
TAIL - R/H FWD UPPER HORIZONTAL SLIDING SEAL CRACKED.<[01] R&R R/H FWD UPPER HORIZONTAL STAB SLIDING SEAL REF AMM 53-31-31.
Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 24,701 hrs · 11,857 cycles
EMERGENCY EXIT ROW LIGHT ABOVE DOOR ON CAPTAINS SIDE OUT.<[01] PERFORMED OPS CHECK OF OVERWING EXIT LIGHT ASSY. IAW AMM 33-21-00; NO DEFECTS NOTED. LIGHT OPS CHECKS GOOD.
Part: GIRT BAR — OUT OF ADJUST (ZN 900 LAV/GALLE) · airframe 24,216 hrs · 11,599 cycles
FWD SERVICE DOOR GIRT BAR STUCK<[01] FOUND FWD SERVICE DOOR ESCAPE SLIDE GIRT BAR NOT INSTALLED PROPERLY IN HOOKS. PROPERLY INSTALLED GIRT BAR IN HOOKS PER M.M. CH. 25-66-00
2022
Part: SLIDE — OUT OF POSITION (FWD ENTRY DOOR) · airframe 22,602 hrs · 10,684 cycles
FA DISARM FRONT ENTRY DOOR ;AS STARTING TO OPEN ;BAR LOWERED AND CAUGHT TO PULL OUT SLIDE / [01] REMOVED AND REPLACED FWD ENTRY DOOR SLIDE REF MT 725-61-06 (76286)
Part: LIGHT — CRACKED · airframe 21,371 hrs · 9,996 cycles
FWD GALLEY FLOOR EMERGENCY LIGHT LENS CRACKED / [01] REPLACED LIGHT LENS REFERENCE AMM 33-51-14
2021
Part: BAFFLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO FLOOR STRUCTURE; BAFFLE /INTERCOSTAL BETWEEN STATION 747-767 RBL 22;WL 155 HAS AREAS OF CORROSION ON UPPER SURFACES. DOT 234/12 ; / [01] REMOVED CORROSIONIAW B737 SRM 51-10-02-0G-0.; [02] EVALUATED MATERIAL LOSS. ORIGINAS T< .032; REMAINING; .024; LOSS OF .008. OUT OF LIMITS IAW B737 SRM 53-00-53-1A-2.AAR TOOL # 32351; CAL DUE 12/10/22.; [03] REMOVED BAFFLE IAW B737 SRM 51-40-02-0G-0.; [04] INSPECTION CW STEPS 1-3; [05] RECEIVED NEW BAFFLE P/N 146A7505-8; A TAG #WN12212. IAW BOEING DWG # 146A7502. REV. B.; [06] LOCATED AND DRILLED BAFFLE IAW B737 SRM 51-40-05-0G-0.; [07] INSPECTION CW STEPS 5;6<BR><BR>OK TO INSTALL; [08] INSTALLED BAFFLE IAW B737 SRM 51-40-02-0G-0.; [09] ALL STEPS COMPLETE 1-9 FOR BAFFLE REPLACEMENT; [10] INSPECTION CW. AUDIT CW
Part: SCUFF PLATE — CRACKED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO DOOR CUTOUT; AFT CORNER SCUFF PLATE IS CRACKED ; / [01] AFT CARGO DOOR CUT OUT AFT CORNER SCUFF PLATE GOT REPAIRED IN BACK SHOP ON WO:43041-1600-0003.NEED OK TO INSTALL AFT CORNER SCUFF PLATE.; [02] VERIFIED STEP 1. OK TO INSTALL; [03] INSTALLED AFT CARGO DOOR CUT OUT AFT CORNER SCUFF PLATE IAW AMM 53-11-02-420-801 AND SRM 51-40-02-0G-0.; [04] TOOL NUMBER:24544 DUE 4/15/22.; [05] VERIFIED STEP 3 AND 4.
Part: WEB — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO THRESHOLD WEB HAS AREAS OF CORROSION AT FASTENER HOLE NUT PLATES; UPPER AND LOWER SURFACES. STATION 807-814 WL 156 AND RBL 25. ; / [01] REMOVED 3EA NUT PLATES TO FOM IAW B-737 SRM 51-40-02.; [02] DAMAGE REMOVED IAW B-737 SRM 51-10-02-0G-0. 10X MAG LENS DETECT NO FURTHER DAMAGE.; [03] UT IAW B737 NDT PART 4; 51-00-00 PROC 2. ORIG .045'; LOSS .007'; REMAINING .038'. TOOL#40084; DUE 11AUG22; [04] ORIGINAL 0.045; LOSS 0.007; REMAINING 0.038. WEB WAS FOUND OUT OF LIMITS IAW B-737 SRM 53-60-15-1A-1 FIG. 103 DETAIL D.; [05] REMOVED AFT CARGO DOOR FWD AND AFT CORNER SCUFF PLATES AND CENTER SCUFF PLATE IAW B737 SRM 51-40-02-0G-0<BR><BR>REMOVED AFT CARGO DOOR LOWER SILL WEB IAW B737 SRM 51-40-02-0G-0; [06] LOCATED AND DRILLED FASTENER & NUTPLATE HOLES IN NEW WEB IAW SRM 51-4-02.; [07] COUNTERSUNK FASTENER HOLES IN NEW WEB IAW SRM 51-40-08.; [08] APPLIED CIC TO LOWER SURFACE OF NEW WEB IAW AMM 51-21-91.; [09] INSPECTION CW STEPS 6;7 AND 8; [10] INSTALLED NUTPLATES IAW SRM 51-40-02.; [11] OK TO INSTALL NEW WEB; 146A8123U25. A TAG # WN6549.; [12] INSPECTION CW STEPS 10-11<BR><BR>OK TO INSTALL NEW PART; [13] REMOVED CORROSION IAW SRM 51-10-02. ORIGINAL MATERIAL THICKNESS IS .045' WITH A LOSS OF .007'. REMAINING THICKNESS OF .038' IS OUT OF LIMITS IAW SRM 53-60-15-1A-1. REMOVED WEB IAW SRM 51-40-02 & INSTALLED NEW WEB IAW BOEING DWG. # 146A8120 ID:0041 REV.A. & SRM 51-40-02.; [14] RII C/W; [15] VERIFIED STEP 13.<BR><BR>INSP C/W<BR>AUDIT C/W
Part: STRIP — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
DOT#71-186 FWD CARGO COMPARTMENT #2 RH FWD CAP STRIP CORRODED ; / [01] DAMAGE REMOVED IAW B-737 SRM 51-40-02. 10X MAG LENS DETECT NO FURTHER DAMAGE.; [02] HFEC IAW B737 NDT PART 6; 51-00-00 PROC 23. NO DEFECTS NOTED. TOOL#36303; DUE 13APR22; [03] REPLACED DAMAGED PART WITH NEW CAP STRIP IAW B-DRAWING 453A1600 REV -.; [04] REPLACED DAMAGED PART WITH NEW CAP STRIP IAW B-DRAWING 453A1600 REV -. A-TAG WN1585; [05] VERIFIED ALL STEPS COMPLETE; [06] BOEING DWG 453A1600 SHT 140 REV- EFFECTIVITY VERIFIED LINE#5706 P/N 453A1611-31; [07] VERIFIED COMPLETE
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
A113-04 AFT CARGO COMPARTMENT PANEL 140BF I/B AND O/B EDGES ARE CORRODED. ; / [01] EVALUATED FLOOR PANEL 140BF AND FOUND TO BE OUT OF LIMITS. CORROSION EXCEEDS MORE THAN 20' IN LENGTH IAW SRM 53-00-53-1A.; [02] MATERIAL VERIFIED FOR NEW FLOOR PANEL. 2024-T3; .071' A-TAG A104325 IAW AMM 25-52-01-201.; [03] VERIFIED STEP 2;3; [04] FABRICATED NEW FLOOR PANEL IAW AMM 25-52-01-201.; [05] VERIFIED STEP 4. OK TO TREAT AND PRIME; [06] APPLIED ALODINE; AND PRIMED BOTTOM SURFACE OF PANEL IAW AMM 25-52-01-201.; [07] FOUND CORROSION ON FLOOR PANEL 140BF TO EXCEED 20' IN LENGTH. THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A. FABRICATED NEW PANEL IAW AMM 25-52-01-201.; [08] VERIFIED STEPS 6;7
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
DOT#66-186 FWD CARGO COMPARTMENT FLOOR PANEL 120CF CORRODED ; / [01] FLOOR PANEL 120CF REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A. LENGTH OF CORRODED AREA MORETHAN 20'.; [02] VERIFIED MATERIAL TO BE A-TAG# A106979; P/N 2024-T3 IAW AMM 25-52-01-201-801.; [03] FABRICATED FLOOR PNL 120CF IAW AMM 25-52-01-201-801.; [04] INSPECTION CW STEPS 1-3; [05] OK TO TREAT AND PRIME; [06] TREATED & PRIMED FLOOR PANEL 120CF IAW AMM 51-21-72-370-804; [07] TREAT AND PRIME C/W; [08] COMPLETE<BR>AUDIT C/W
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
A113-02 AFT CARGO COMPARTMENT PANEL 140DF; I/B AND O/B EDGES ARE CORRODED. ; / [01] CORROSION DAMAGE TO PANEL 140DF EXCEEDS THE 20 INCH MAX ALLOWABLE AREA AND FOUND TO BE OUT OF LIMITS IAW B-737 SRM 53-00-53-1A-1 FIG. 102.; [02] MATERIAL VERIFIED AS 0.071' 2024-T3 IAW B-737 AMM 25-52-01-839-010. A-TAG A104322; [03] VERIFIED STEP 1;2; [04] FABRICATION STARTED ON PANEL 140DF IAW B-737 AMM25-52-01-201-801. TASK NOT COMPLETE.; [05] FABRICATED PANEL 140DF IAW B-737 AMM 25-52-01-201-801.; [06] VERIFIED STEP 5. OK TO TREAT AND PRIME; [07] TREATED AND PRIMED FLOOR PANEL 140DF IAW B-737 B-SOPM 20-43-03 & 20-41-02.; [08] C/W; [09] VERIFIED STEP 7;8. C/W
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
A113-05 AFT CARGO COMPARTMENT PANEL 140CF I/B AND O/B EDGES ARE CORRODED. ; / [01] CORROSION DAMAGE TO PANEL 140CF EXCEEDS THE 20 INCH MAX ALLOWABLE AREA AND FOUND TO BE OUT OF LIMITS IAW B-737 SRM 53-00-53-1A-1 FIG. 102. FABRICATION STARTED ON PANEL 140CF IAW SRM 25-52-01-201-801/ TASK NOT COMPLETE. COMPLETED FABRICATION OF PANEL 140CF IAW SRM 25-52-01-201-801. APPLIED ALODINE AND PRIMED IAW AMM 25-52-01-201. FOUND CORROSION TO EXCEED 20' IN LENGTH; THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A. FABRICATED NEW PANEL IAW AMM 25-52-01-201.
Part: STRIP — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
DOT#70-186 FWD CARGO COMPARTMENT #3 RH FWD CAP STRIP CORRODED ; / [01] FWD CARGO COMPARTMENT #4 LH CAP STRIP IS CORRODED; NOT THE #3 RH SIDE. REPLACED #4 CAP STRIP AND VERIFIED P/N 453A1611-16 A-TAG WN5426. IAW IPC 25-52-10-03 ITEM 365; [02] VERIFIED STEP 1.; [03] OK TO INSTALL CAP STRIP.; [04] INSTALLED NEW #4 L/H CAP STRIP I/A/W B737 AMM 25-52-10-400-801; [05] VERIFIED STEP 4
Part: PANEL — CORRODED (AFT CARGO BAY) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT PANEL 140EF I/B AND O/B EDGES ARE CORRODED. DAMAGE EXCEEDS THE 20' INCH MAX ALLOWABLE LIMIT AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIG. 102. FABRICATED NEW PANEL IAW AMM 25-52-01-201. FOUND CARGO PANEL CORROSION TO EXCEED 20' IN LENGTH. THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A. FABRICATED NEW PANEL IAW AMM 25-52-01-201.
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
A113-01 AFT CARGO COMPARTMENT FLOOR PANEL 140AF; EDGES ARE CORRODED. ; / [01] CORROSION DAMAGE TO PANEL 140AF EXCEEDS THE 20 INCH MAX ALLOWABLE AREA AND FOUND TO BE OUT OF LIMITS IAW B-737 SRM 53-00-53-1A-1 FIG. 102.; [02] EVALUATED FLOOR PANEL 140AF AND FOUND CORROSION TO EXCEED 20' IN LENGTH. THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A.; [03] MATERIAL VERIFIED FOR NEW FLOOR PANEL. 2024-T3; 071'; A-TAG A106982 IAW AMM 25-52-01-201.; [04] VERIFIED STEP 1;2;3; [05] FABRICATED NEW CARGO FLOOR PANEL IAW AMM 25-52-01-201.; [06] VERIFIED STEP 5; [07] OK TO TREAT AND PRIME; [08] ALODINED AND PRIMED PANEL IAW AMM 25-52-01-201.; [09] FOUND CORROSION TO EXCEED 20' IN LENGTH; THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A. FABRICATED NEW PANEL IAW AMM 25-52-01-201.; [10] VERIFIED STEP 8;9<BR>C/W
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
DOT#67-186 FWD CARGO COMPARTMENT FLOOR PANEL 120DF CORRODED ; / [01] PANEL 120DF CORRODED BEYOND LIMITS.; [02] INSPECTION VERIFIED CORROSION BEYOND 20 INCH LIMITS AND MATERIAL FOR FABRICATION; [03] FABRICATED NEW FLOOR PANEL 120DF FROM .071-2024-T3-A TAG# A104322 IAW AMM 25-52-01-201-801.; [04] INSPECTION CW STEP 3; [05] TREATED & PRIMED PANEL 120DF IAW AMM 51-00-58-201.; [06] VERIFIED ITEM 5<BR><BR>AUDIT C/W
Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
DOT#68-186 FWD CARGO COMPARTMENT FLOOR PANEL 120AF CORRODED ; / [01] REMOVED CORROSION.PANEL 120AF IS OUT OF LIMITS DUE TO BLEND AREA EXCEEDING 20 INCHES IN LENGTH. IAW B737 SRM 53-00-53-1A-1. FIGURE 102.; [02] MATERIAL FOR PANEL VERIFIED AS 2024-T3. .071. IAW B737 AMM 25-52-01-201-801. A TAG# A104324.; [03] VERIFIED ITEMS 1 AND 2; [04] FABRICATED PANEL 120AF IAW B737 AMM 25-52-01-201-801.; [05] VERIFIED ITEM 4<BR><BR>OK TO TREAT AND PRIME; [06] TREATED AND PRIMED LOWER SURFACE OF PANEL 120AF IAW B737 AMM 51-21-41-370-801; AND 51-21-72-370-804. PLACED PANEL ON RACK.; [07] VERIFIED ITEM 6; [08] AUDIT C/W
Part: ANGLE — CORRODED (FUSELAG) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-09) FWD CARGO COMPARTMENT STA 500F+15 LBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION AT FWD CARGO STA. 500F+15 LBL 24 Z ANGLE AND PERFORMED 10X MAGNETIC GLASS I/A/W SRM 53-00-53-1A-2; [02] VERIFIED MATERIAL LOSS LOSS OF .007 ORIGINAL.040 REMAINING .033 IS OUT OF LIMITS I/A/W SRM 53-00-53-1A-2 AAR TOOL 29270 DUE 12-09-22; [03] INSPECTION CW STEP 2; [04] Z-ANGLE WAS OUT OF LIMITS; AND NEW Z-ANGLE WAS FABRICATED AND INSTALLED FROM BS 500F + 10' TO BS 500I ON CARD TTG8Q009V7VB; [05] AUDIT C/W
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-010) FWD CARGO COMPARTMENT STA 500E+15 LBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION AT FWD CARGO STA 500E+15 LBL 24 Z ANGLE AND PERFORMED 10X MAGNIFYING GLASS I/A/W SRM 53-00-53-1A-2; [02] VERIFIED MATERIAL LOSS LOSS OF .007 ORIGINAL.040 REMAINING .033 IS OUT OF LIMITS I/A/W SRM 53-00-53-1A-2; [03] INSPECTION VERIFIED STEP 2; [04] Z-ANGLE WAS OUT OF LIMITS; AND NEW Z-ANGLE WAS FABRICATED AND INSTALLED FROM BS 500F + 10' TO BS 500I ON CARD TTG8Q009V7VB; [05] AUDIT C/W
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-02) FWD CARGO COMPARTMENT STA 500A TO 500I RBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION. MATERIAL REMOVED = .009. MATERIAL REMAINING =.031. ZEE ANGLE FOUND TO BE OUT OF LIMITS.<BR>DEPTH GAUGE 21461. CAL DATE 8/11/22.; [02] REMOVED Z-ANGLE FROM STA 500A-500I R/H SIDE IAW SRM 51-40-02.; [03] VERIFIED MATERIAL TO BE A-TAG #A67394 P/N BAC1496-444 AND IAW SRM 53-00-53-5R.; [04] FABRICATED Z-ANGLE IAW SRM 51-4-05 AND SRM 53-00-53-5R.; [05] FABRICATED Z-ANGLE IAW SRM 51-40-05-0G-0; AND SRM 53-00-53-2R-5 REPAIR 5; [06] VERIFIED ITEMS 1 THROUGH 5<BR><BR>OK TO TREAT AND PRIME; [07] TREATED AND PRIMED Z-ANGLE IAW SRM 53-00-53-2R-5.; [08] VERIFIED ITEM 7; [09] OK TO INSTALL ZEE ANGLE REPAIR PARTS; [10] INSTALLED R/H Z-ANGLE ON FED CARGO FROM STA 500A-500I IAW SRM 53-00-53-2R-5 AND BOEING DWG #143A7500 TY:DWG; ID:001; REV:-.; [11] VERIFIED ITEM 10<BR><BR>NUTPLATES STILL REQUIRE FORCE TEST; [12] TESTED GLUED NUTPLATE IAW SRM 51-40-10-2R-0; TABLE 202.<BR>AAR TOOL# 41801 DUE: 03/08/22; [13] REPAIR AND INSTALLATION OF RH Z-ANGLE IN FWD CARGO COMPARTMENT IS COMPLETE; ALL STEPS 1-13 COMPLETE; [14] RII C/W; [15] VERIFIED STEP 12 AND 13.<BR>INSP C/W<BR>AUDIT C/W
Part: NUT PLATE — CORRODED (AFT CARGO BAY) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT STA 767 +5' BETWEEN RBL 20 AND LBL 20 WL 155 FLOOR TRANSITION NUTPLATE STRIP IS CORRODED TOP SIDE 7 EA AREAS AS MARKED ; / [01] REMOVED CORROSION; AND MEASURED MATERIAL LOSS. ORIGINAL .070'; REMOVED .021'; ALLOWABLE .007'. FOUND TO BE OUT OF LIMITS I/A/W B737 SRM 53-00-53-1A-2<BR>TOOLING# 29270 DUE 12/09/22; [02] VERIFIED STEP 1.; [03] VERIFIED NEW TRANSITION STRIP FOR STA 767+5; LBL20-RBL20 AS 146A9401-4ATSMRO A TAG # A108694.; [04] VERIFIED STEP 3<BR><BR>ALL TASKS COMPLETE<BR>AUDIT COMPLETE
Part: BRACKET — CRACKED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT STA 867 LBL 11 LOWER SUPPORT BRACKET FOR LAV TANK BULKHEAD PNL FRAME STRUCTURE IS CRACKED AS MARKED ; / [01] REMOVED CRACKED BRACKET AT STA 867 L/H SIDE AFT CARGO IAW SRM 51-40-02-0G-0; [02] VERIFIED NEW ANGLE BRACKET AS P/N 149A8109-114 [A] TAGA105630 IAW BOEING DWG 149A8109 REV: B; [03] INSPECTION CW STEP 2; [04] LOCATED AND DRILLED ALL FASTENER HOLES IN NEW AFT CARGO BRACKET STA 867 L/H SIDE IAW SRM 51-40-05-0G-0 ALSO BOEING DWG 149A8109 REV:B; [05] INSPECTION CW STEP 4<BR><BR>OK TO INSTALL; [06] INSTALLED NEW BRACKET AT STA 867 L/H SIDE AFT PIT IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 149A8109 REV:B; [07] NEW BRACKET COMPLETED INSTALLED IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 149A8109 REV:B; [08] VERIFIED ITEMS 6 AND 7<BR><BR>AUDIT C/W
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-011) FWD CARGO COMPARTMENT STA 500D+10 LBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION AT FWD CARGO STA 500D+10 LBL 24 Z ANGLE AND PERFORMED 10X MAGNIFYING GLASS I/A/W SRM 53-00-53-1A-2; [02] VERIFIED MATERIAL LOSS LOSS OF .006 ORIGINAL .040 REMAINING .034 IS OUT OF LIMITS I/A/W SRM 53-00-53-1A-2 AAR TOOL 29270 DUE 12-09-22; [03] INSPECTION VERIFIED STEP 2; [04] Z-ANGLE WAS OUT OF LIMITS; AND NEW Z-ANGLE WAS FABRICATED AND INSTALLED FROM BS 500F + 10' TO BS 500I ON CARD TTG8Q009V7VB; [05] AUDIT C/W
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-08) FWD CARGO COMPARTMENT STA 500G+15 LBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION AT FWD CARGO STA 500G+15 LBL24 Z ANGLE AND PERFORMED 10X MAGNIFYING GLASS I/A/W SRM 53-00-53-1A-2; [02] VERIFIED MATERIAL LOSS LOSS OF .006 ORIGINAL.040 REMAINING .034 IS OUT OF LIMITS I/A/W SRM 53-00-53-1A-2 AAR TOOL 29270 DUE 12-09-22; [03] INSPECTION VERIFIED STEP 2; [04] VERIFIED NEW Z ANGLE AND SPLICE SIDEPLATE P/N BAC1496-444-7075-T6 A TAG #A67392 FROM STA 500D TO 500I I/A/W SRM 53-00-53-2R-5 REPAIR 5; [05] VERIFIED ITEM 4; [06] STARTED FABRICATE NEW Z ANGLE I/A/W SRM 53-00-53-1A-2; [07] FABRICATED NEW Z ANGLE AND SPLICE SIDEPLATE I/A/W SRM 53-00-53-2R-5 REPAIR 5 FROM 500D TO 500L; [08] VERIFIED ITEMS 6 AND 7<BR><BR>OK TO TREAT AND PRIME; [09] ALODINED AND PRIMED NEW Z ANGLE AND SPLICE SIDEPLATE I/A/W AMM 51-21-41-370-803 AND 51-21-72-370-804; [10] INSPECTION CW STEP 9; [11] OK TO INSTALL ZEE ANGLE REPAIR PARTS; [12] INSTALLED ZEE ANGLE AND REPAIR PARTS I/A/W SRM51-40-02-0G-0 AND 53-00-53-2R-5 REPAIR 5; [13] INSTALLED ALL GLUE ON NUTPLACES ON NEW ZEE ANGLE AND REPAIR PARTS I/A/W SRM 51-40-10-2R-0 A TAG A99876 AND PERFORMED NUTPLATE PUSHOFF STRENGTH TEST I/A/W SRM 51-40-10-2R-0. AAR TOOL 41801 DUE 03-08-22 OPS CHECK GOOD; [14] ALL STEPS 1-14 COMPLETE FOR REPAIR; [15] VERIFIED ITEMS 12 THROUGH 14<BR><BR>AUDIT C/W
Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-03) FWD CARGO COMPARTMENT STA 500I RBL 24 TO LBL 24; LOWER BULKHEAD SUPPORT ANGLE IS CORRODED. ; / [01] ORIGINAL T=.071 REMAINING T=.062 MATERIAL LOSS=.009 LWR BKHD SUPPORT ANGLE DETERMINED TO BE OUT OF LIMITS. DEPTH GAUGE #21461 CAL DATE 8/11/22.; [02] UPDATED TO STEP 1; ORIGINAL T .071' REMAINING T .062' LOSS .009' WITHIN LIMITS IAW SRM 53-30-08-1A-1. MAXIMUM LOSS OF MATERIAL IS .024' DEPTH GAUGE #21461 CAL DATE 8/11/22.; [03] UPDATE TO STEP 2. TO MUCH CORROSION AROUND FASTENER HOLES. LOSS IS .030' AROUND FASTENER HOLES OUT OF LIMITS. IAW SRM 53-030-08-1A-1. REPLACING PART 143A9485Y35; [04] REMOVED LOWER BULKHEAD SUPPORT ANGLE IAW SRM 51-40-02-0G-0; [05] NEW RAIL ASSEMBLY VERIFIED AS P/N 143A9485-35 WN11677 IAW IPC 53-11-01-42; [06] VERIFIED STEPS 1-5; [07] INSTALLED NEW LOWER RAIL ASSEMBLY IAW SRM 51-40-02-0G-0 AND IPC 53-11-01-42; [08] VERIFIED STEP 7 OK TO CIC; [09] APPLIED CIC TO NEW RAIL AREA IAW AMM 51-21-91-620-802; [10] VERIFIED STEP 9<BR>C/W
Part: SHIELD — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT BETWEEN STA 767 AND 787; RBL 21 TO RBL 22.50 AND WL 155; FWD FLOOR SHIELD IS CORRODED IN 10 EA AREAS AS MARKED ; / [01] REMOVED CORROSION FROM SHIELD IAW SRM 51-10-02. ORIGINAL MATERIAL THICKNESS IS .063' WITH A LOSS OF .032'. REMAINING THICKNESS OF .031 IS OUT OF LIMITS IAW SRM 53-00-53-1A-2. TOOL ID # AAR29270; CALIBRATION DUE ON 12/09/2022.; [02] REMOVED SHIELD AT STA 767-787; RBL21-RBL25; IAW SRM 51-40-02.; [03] VERIFIED ITEMS 1 AND 2; [04] LOCATED/DRILLED FASTENER HOLES IAW SRM 51-40-05 & COUNTERSUNK HOLES IAW SRM 51-40-08.; [05] APPLIED CIC TO LOWER SURFACE IAW AMM 51-21-91.; [06] OK TO INSTALL NEW SHIELD 146A8127U12ATSMRO A TAG # WN11956.; [07] INSPECTION CW STEPS 4;5 AND 6<BR><BR>OK TO INSTALL; [08] INSTALLED SHIELD AT STA 767-787; RBL21-RBL25; IAW SRM 51-40-02 & BOEING DWG. # 146A0081 ID:0028 REV.A.; [09] PART INFO ONLY: BLIND RIVET CR3243-6-03 A TAG # A48743 & BLIND RIVET BACR15FP5F4R A TAG # A6441.; [10] REMOVED CORROSION FROM SHIELD AT STA 767-787; RBL21-RBL25; IAW SRM 51-10-02. ORIGINAL MATERIAL THICKNESS IS .063' WITH A LOSS OF .032'. REMAINING THICKNESS OF .031' IS OUT OF LIMITS IAW SRM 53-00-53-1A-2. REMOVED AND REPLACED SHIELD IAW SRM 51-40-02 & BOEING DWG. # 1R6A0081 ID:0028 REV.A.; [11] INSPECTION CW STEPS 8;9 AND 10; [12] RII REQUIREMENTS CW; [13] AUDIT CW; [14] AUDIT CW
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT BILGE AREA L/H Z ANGLE BETWEEN STA 727E AND 807; LBL 21; WL 155 IS CORRODED TOP AND BOTTOM SKIN SURFACES AS MARKED ; / [01] REMOVED CORROSION IN MULTIPLE AREAS. ORIGINAL .040'; REMOVED .011'; ALLOWABLE .004'. FOUND TO BE OUT OF LIMITS FROM STA 727E +10 - STA 800 I/A/W B737 SRM 53-00-53-1A-2 ALLOWABLE DAMAGE 2.; [02] VERIFIED STEP 1; [03] REMOVED FASTENERS IN REPAIR AREA CUT Z-ANGLE AND REMOVED IAW SRM 51-40-02-0G-0 ALSO SR. 53-00-53-2R-5 REPAIR 5; [04] VERIFIED NEW REPAIR MATERIAL FOR L/H Z-ANGLE REPLACEMENT AS P/N BAC1496-444 7075-T6 [A] TAG A93218; A93224 IAW SRM53-00-53-2R-5 REPAIR 5 TABLE 201; [05] INSPECTION CW STEPS 3-4; [06] STARTED FABRICATING NEW SECTIONS OF L/H SIDE Z-ANGLES IN AFT PIT IAW SRM 53-00-53-2R-5 REPAIR 5; [07] VERIFIED STEP 6.; [08] COMPLETED FABRICATING NEW L/H SIDE Z-ANGLE FOR AFT PIT STA 727ETO STA 847 IAW SRM 53-00-53-2R-5 REPAIR 5 STEPD;E;F;G;H. NEED OK TO TREAT AND PRIME; [09] INSPECTION CW STEP 8<BR><BR>OK TO TREAT AND PRIME; [10] ALODINED AND PRIMED NEW L/H SIDE Z-ANGLE PARTS AND OEM CUT EDGE OF Z-ANGLE IAW SRM 53-00-53-2R-5 REPAIR 5 STEP - 4 I;J; [11] INSPECTION CW STEP 10<BR><BR>OK TO CIC; [12] APPLED CIC TO LOWER SURFACE OF ZEE ANGLE IAW B737 AMM 51-21-91-620-802.; [13] OK TO INSTALL; [14] INSTALLED ZEE ANGLEIAW B737 SRM 53-00-53-2R-5 REPAIR 5.; [15] VERIFIED STEP 14; [16] APPLIEDCIC TO UPPER SURFACE OF ZEE ANGLE IAW B737 AMM 51-21-91-620-802.; [17] REPAIR COMPLETE ALL STEPS 1-17 C/W
Part: ANGLE — CORRODED (FWD CARGO BAY) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-013) FWD CARGO COMPARTMENT STA 500B+2 LBL 24; Z ANGLE IS CORRODED. REMOVED CORROSIONS' AT FWD CARGO STA 500B+2 LBL 24 Z ANGLE AND PERFORMED 10X MAG GLASS IAW SRM 53-00-53-1A-2. VERIFIED MATERIAL LOSS LOSS OF .003 ORG .040 REMAINING .037 IS WITHIN LIMITS IAW SRM 53-00-53-1A-2. ALODINED AND PRIMED BLENDED AREA IAW AMM 51-21-41-370-803 AND 51-21-72-370-801.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-07) FWD CARGO COMPARTMENT STA 500H+15 LBL 24; Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION AT FWD CARGO STA 500H+15 LBL24 Z ANGLE AND PERFORMED 10X MAGNETIC GLASS I/A/W SRM 53-00-53-1A-2; [02] VERIFIED MATERIAL. LOSS LOSS OF .007 ORIGINAL IS .040 REMAINING .033 IS OUT OF LIMITS I/A/W SRM 53-00-53-1A-2 AAR TOOL 29270 DUE 12-09-22; [03] INSPECTION VERIFIED STEP 2; [04] Z-ANGLE WAS OUT OF LIMITS; AND NEW Z-ANGLE WAS FABRICATED AND INSTALLED FROM BS 500F + 10' TO BS 500I ON CARD TTG8Q009V7VB; [05] AUDIT C/W
Part: NONE — CRACKED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
(DOT 67-04) FWD CARGO COMPARTMENT STA 500G LBL 24; INTERCOSTAL SUPPORT ANGLE IS CRACKED. ; / [01] REMOVED INTERCOSTAL CLIP AT STA. 500G; LBL24; IAW SRM 51-40-02.; [02] VERIFIED NEW CLIP; 143A7502U159; IAW BOEING DWG 143A7505 REV. -. A TAG # A66315.; [03] LOCATED/DRILLED NEW CLIP IAW SRM 51-40-05. OK TO INSTALL; [04] REMOVED CRACKED CLIP AT STA. 500G; LBL24; AND INSTALLED NEW CLIP; 143A7502U159; IAW SRM 51-40-02 AND BOEING DWG 143A7505.; [05] VERIFIED ITEMS 1 THROUGH 4; [06] OK TO INSTALL CLIP (OUT OF SEQUENCE); [07] AUDIT C/W
Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
AFT CARGO COMPARTMENT BILGE AREA R/H Z ANGLE BETWEEN STA 727H AND 767 ; RBL 21 AND WL 155 IS CORRODED TOP AND BOTTOM SKIN SURFACES IN SEVERAL AREAS AS MARKED ; / [01] REMOVED CORROSION; AND MEASURED DAMAGE. ORIGINAL .040'; REMOVED .015'; ALLOWABLE .004. FOUND TO BE OUT OF LIMITS FROM STA 727H +5 TO STA 767 I/A/W B737 SRM 53-00-53-1A-2 ALLOWABLE DAMAGE 2. <BR>TOOL# 32351 DUE: 12-10-22; [19] INSTALLED ZEE ANGLE IAW B737 SRM 53-00-52-2R-5; REPAIR 5.; [20] INSPECTION CW STEP 19; [21] OK TO CIC; [22] APPLIED CIC TO ZEE ANGLE IAW B737 AMM 51-21-91-620-802.; [23] INSPECTION CW STEP 22; [24] AUDIT CW
Part: FAIRING — DELAMINATED (#1 ENG) · airframe 20,537 hrs · 9,518 cycles
#1 ENGINE O/B MID STRUT FWD FAIRING PANEL 431BL HAS WEAR/DELAM AT FWD LOWER CORNER. DOT#A193-5 ; / [01] EVALUATED AND FOUND PLIES MISSING AT FWD LWR CORNER EDGEBAND AS MARKED. FOUND TO BE REPAIRABLE IAW SRM 54-50-70-2R-1 TABLE 201 250 DEGREE PRE-PREG AND SRM 51-70-05-2R-10.<BR><BR>CLEANED AND PREPPED IAW SRM 51-70-05-2R-10 STEP 4 A-C.<BR><BR>VERIFIED MATERIAL IAW SRM 51-70-05-2R-0 REPAIR GENERAL TABLE 203. FILM ADHESIVE (A68274); FABRIC (A60941).; [02] BONDED REPAIR IAW SRM 51-70-05-2R-10 STEP 4 D-G. CURED AT 260 DEGREES (AAR21182 EXP 4-30-22). TAP TEST GOOD. <BR><BR>REQUESTING OK TO APPLY DECORATIVE FINISH; [03] STEP 1 AND 2 OK.. OK TO PAINT; [04] APPLIED DECORATIVE FINISH IAW AMM 51-21-99-300-801 TABLE 701. PAINT (A28552); [05] REPAIRED AND APPLIED DECORATIVE FINISH ON #1 ENGINE MID STRUT FWD FAIRING 431BL AT FWD LWR CORNER IAW SRM 51-70-05-2R-10; SRM 51-70-05-2R-0 REPAIR GENERAL AND AMM 51-21-99-300-801.
Part: SUPPORT — CRACKED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
STA 540 RBL 2 CABIN FLOOR LATERAL SUPPORT IS CRACKED. VIEWED FROM BELOW. ; / [01] REMOVED FLOOR BREAK IAW SRM 51-40-02; [02] REMOVED AND REPLACED FLOOR SUPPORT BREAK AT STA540; RBL2; IAW SRM 51-40-02 & BOEING DWG. # 143A0060 ID:0058 REV.A. 143A5240-36 A TAG # KK803.; [03] INSPECTION CW STEPS 1-2; [04] RII REQUIREMENTS CW. AUDIT CW
Part: SUPPORT — CRACKED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
STA 540 LBL 2 CABIN FLOOR LATERAL SUPPORT IS CRACKED. VIEWED FROM BELOW. ; / [01] REMOVED SUPPORT BREAK IAW SRM 51-40-02; [02] REMOVED AND REPLACED FLOOR SUPPORT BREAK AT STA 540; LBL2; IAW SRM 51-40-02 & BOEING DWG. # 143A0060 ID:0058 REV.A.; [03] 143A5240-35 A TAG # 12055; [04] INSPECTION CW STEPS 1-3; [05] RII REQUIREMENTS CW; [06] AUDIT CW
Part: SUPPORT WEB — CRACKED (L/H WING) · airframe 20,537 hrs · 9,518 cycles
L/H WING FIXED T/E; INBD OF DEFLECTOR CONTROL RIB; PANEL SUPPORT WEB IS CRACKED. A224-10 ; / [01] REMOVED PANEL SUPPORT WEB IAW SRM 51-40-02-0G-0; [02] NSTALLED NEW PANEL SUPPORT WEB IAW SRM 51-40-02-0G-0 AND DWG 115A2511 SHT 2 REV B; [03] VERIFIED C/W
Part: ANGLE — CRACKED (L/H WING) · airframe 20,537 hrs · 9,518 cycles
L/H WING FIXED T/E AT OTBD EDGE OF #6 SPOILER; PANEL SUPPORT IS CRACKED. A224-007 ; / [01] REMOVED PANEL SUPPORT IAW SRM 51-40-02-0G-0; [02] LOCATED & DRILLED NEW ANGLE 115A2156-17 / A TAG # A107452 IAW SRM 51-40-05.; [03] VERIFIED STEP 2; [04] INSTALLED ANGLE IAW SRM 51-40-02 & BOEING DWG # 115A2156 ID:0007 REV.-; [05] REMOVED AND REPLACED PANEL SUPPORT ANGLE AT LEFT WING T/E; O/B OF #6 SPOILER IAW SRM 51-40-02 & BOEING DWG. # 115A2156 ID:0007 REV.-; [06] INSPECTION CW STEPS 4-5; [07] AUDIT CW
Part: FAIRING — DELAMINATED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
FUSELAGE FAIRING 192BL; L/E HAS EROSION WITH DELAM. DOT A034-08 ; / [01] EVALUATED AND FOUND DAMAGE TO EDGE TO BE REPAIRABLE IAW SRM 53-40-70-1A-1 PARAGRAPH 4B(8) AND FIGURE 105. <BR>CLEANED; PREPPED AND APPLIED SEALER RESIN TO AREA; CURED 2 HOURS AT 125 DEGREES IAW SRM 51-70-08-0G-0 PARAGRAPH 3A-F. TOOLING---AAR30347 DUE 4-29-22 (A71242)<BR>NEED OK TO PAINT; [02] STEP 1 OK. OK TO PAINT; [03] RESTORED DECORATIVE FINISH IAW AMM 51-21-99-300-801 PARAGRAPH 2E(6). (A41936); [04] REPAIRED DAMAGE TO L/E OF FAIRING 192BL IAW SRM 53-40-70-1A-1; SRM 51-70-08-0G-0 AND AMM 51-21-99-300-801
Part: FAIRING — DELAMINATED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
UPPER AFT CORNER OF FAIRING 191AL DELAMINATED. ; / [01] EVALUATED AND FOUND EDGE DELAMINATION AND IS REPAIRABLE IAW SRM 53-30-70-2R-1 TABLE 202 AND SRM 51-70-04<BR>CLEANED; PREPPED AND RESIN INJECTION REPAIR IAW SRM 51-70-04-2R-13 REPAIR 13 PARAGRAPH 4A-H. TAP TEST GOOD. TOOLING--AAR30347 DUE 4-29-22 (A74289); [02] REPAIRED DAMAGE TO UPPER AFT CORNER OF FAIRING 191AL IAW SRM 53-30-70-2R-1 AND SRM 51-70-04-2R-13. TAP TEST GOOD
Part: FLOOR PANEL — PULLED (CABIN FLOOR) · airframe 20,537 hrs · 9,518 cycles
CABIN FLOOR PANEL 231FF HAS MISSING CORE AT AFT I/B CORNER ; / [01] EVALUATED AND FOUND CORE MISSING AT AFT I/B CORNER. NO DAMAGE TO COMPOSITE. FOUND TO BE REPAIRABLE IAW SRM 53-00-50-2R-10. TAP TEST GOOD.<BR><BR>APPLIED POTTING COMPOUND IAW SRM 53-00-50-2R-10 STEP 3 A-G AND SRM 53-00-50-2R-0 REPAIR GENERAL STEP 5(P). CURED AT 120 DEGREES OVEN (B0-06 EXP 2-19-22). POTTING COMPOUND (A101798).; [02] REPAIRED CABIN FLOOR PANEL 231FF AT AFT I/B CORNER IAW SRM 53-00-50-2R-10 AND SRM 53-00-50-2R-0 REPAIR GENERAL.
Part: FAIRING — DELAMINATED (FUSELAGE) · airframe 20,537 hrs · 9,518 cycles
FUSELAGE FAIRING 192BR; L/E HAS EROSION WITH DELAM. DOT A034-06 ; / [01] EVALUATED AND FOUND 2 EACH AREAS OF DELAM ON L/E AND BOTH ARE REPAIRABLE IAW SRM 53-40-70-2R-1 TABLE 202 AND SRM 51-70-04<BR>REMOVED DAMAGED PLIES; CLEANED AND PREPPED AREAS FOR REPAIR IAW SRM 51-70-04-2R-1 STEPS 4 A;B;C<BR>VERIFIED REPAIR MATERIALS AS REPAIR PLIES--BMS9-8 STYLE 3K-70P (A03859); BMS9-3TY D CL7 (A37286); REPAIR RESIN--EA9390 (A54377); SEALER RESIN--EC1838 (71242); [02] OK TO BOND; [03] BONDED REPAIR; CURED 3.5 HOURS AT 200 DEGREES IAW SRM 51-70-04-2R-1 STEPS 4 D;E;F. TOOLING AAR30347 DUE 4/29/22; [04] UT IAW B737 NDT PART 4; 51-00-02. NO DEFECTS NOTED. TOOL#40084; DUE 11AUG22; [05] STEP 3 OK. OK TO PAINT; [06] RESTORED DECORATIVE FINISH IAW AMM 51-21-99-300-801 PARAGRAPH 2E(6) (A41936); [07] REPAIRED DAMAGE TO L/E OF FAIRING 192BR IAW SRM 53-40-70-2R-1; SRM 51-70-04-2R-1; NDT PART 4; 51-00-02 AND AMM 51-21-300-801; [08] VERIFIED STEPS 6-7 AND AUDITED
Part: ANGLE — CRACKED (R/H WING) · airframe 20,537 hrs · 9,518 cycles
RIGHT WING; 20' INBOARD OF DEFLECTION CONTROL RIB; ATTACH ANGLE TO PANEL SUPPORT IS CRACKED. A045-003 ; / [01] REMOVED ANGLE IAW SRM 51-40-02.; [02] LOCATED & DRILLED FASTENER HOLES IN NEW ANGLE; 115A2156-18 A TAG # A107454; IAW SRM 51-40-05.; [03] INSTALLED NEW ANGLE IAW SRM 51-40-02.; [04] REMOVED AND REPLACED ANGLE; 20' I/B OF DEFLECTION RIB; FOR RIGHT WING UPPER PANEL SUPPORT IAW SRM 51-40-02 & BOEING DWG. # 115A2156 ID:0007 REV.-; [05] INSPECTION CW STEPS 1-4; [06] AUDIT CW
Part: ANGLE — CRACKED (L/H WING) · airframe 20,537 hrs · 9,518 cycles
L/H WING FIXED T/E; ATTACHED TO INBD SIDE OF DEFLECTOR CONTROL RIB; PANEL SUPPORT L-ANGLE CRACKED. DOT 224-006 ; / [01] REMOVED L-ANGLE IAW SRM 51-40-02-0G-0; [02] INSTALLED NEW L-ANGLE IAW SRM 51-40-02-0G-0 AND IPC 57-42-51-03; [03] VERIFIED STEP 2.
2020
Part: GIRT BAR — OUT OF ADJUST (L2 DOOR SLIDE) · airframe 16,338 hrs · 7,287 cycles
L-2 DOOR SLIDE GIRT TOO LONG; NEEDS REINSTALLED. / REPLACED L-2 DOOR SLIDE GIRT PER TASK CARD 725-61-08AMT 117477INSP P44 43511
Part: PUMP — LOW PRESSURE (HYD SYSTEM) · airframe 15,872 hrs · 7,075 cycles
ON CLIMB OUT PASSING 18;000. ENG 1 A & B SYS HYD LOW PRESSURE PUMP LIGHT ILLUMINATED. CHECKED HYD OIL QTY & PRESSURE, A SYS PRESSURE WAS DROPPING. CONSULTED QRH CHECKLIST 13:4 LOSS OF A SYS. COMPLETED CHECK LIST AND RETURNED TO DEPARTURE. HYD CHECKED BRAKES PRIOR TO APPROACHING GATE. REMOVED AND REPLACED THE NR 1 HYDRAULIC ENGINE DRIVEN PUMP. INSPECTED AND REPLACED THE NR 1 ENGINE CASE DRAIN FILTER IAW AMM 29-11-11. A/C OK FOR SERVICE.
2019
Part: COVER — UNSECURE (EXIT SIGN) · airframe 12,065 hrs · 5,360 cycles
OVERHEAD "EXIT" SIGN MID-CABIN FELL DOWN TO FLOOR. SECURED SIGN (COVER) PER AMM.
2016
Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 1,896 hrs · 842 cycles
L2 DOOR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED THE LAMP IAW AMM.