N407YK

Part: BLOWOUT PANEL — BLOWN (ZONE 100) · airframe 62,289 hrs · 41,847 cycles

AT 37000 FT IN CRUISE, CABIN ALTITUDE CLIMBED RAPIDLY AND EXCEEDED 20,000 FEET. FOLLOWED QRH, CABIN WAS NOT CONTROLLABLE IN MAN AC W/ VALVE CLOSED INDICATION. AIRCRAFT RETURNED TO PAOM. PERFORMED CABIN DEPRESSURIZATION CONDITIONAL INSPECTION IAW AMM 05-51-081 FOUND LOWER AFT CARGO COMPT BLOW OUT PANEL BLOWN OUT. NO OTHER FAULTS FOUND, PERFORMED CABIN PRESSURE LEAK TEST IAW AMM 05-51-91 NO FAULTS FOUND.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

RH WING L/E LOWER ACCESS PANEL EDGE INSTALL CONDITION NOT FLAT , AFTER PANEL REMOVE FOUND FRONT SPAR LOWER CHORD CORROSION AT FSS.644.

Part: PRESSURE BLKHD — CRACKED (BS 685 LBL54) · airframe 61,937 hrs · 41,552 cycles

W/W PRESURE BLUCKHEAD CRACK ABOUT 1.125" STA 685+18 LBL54, IN MAIN CABIN UNDER FLOOR.

Part: ATTACH ANGLE — CRACKED (BS 348 S16L) · airframe 61,937 hrs · 41,552 cycles

AN ATTACHMENT CLIP CRACK ON MAIN ENTRY DOOR STOP INTERCOSTAL, BS348.2, S-16L.

Part: ANGLE — CRACKED (MAIN DOOR) · airframe 61,937 hrs · 41,552 cycles

MAIN ENTRY DOOR LOW AFT CORNER SCUFF PLATE ANGLE CRACK. 1EA.

Part: FRAME — CRACKED (BS 380 S20-21L) · airframe 61,937 hrs · 41,552 cycles

DO HFEC INSP. FOUND FRAME INTEGRAL INBOARD CHORD CRACKED ABOUT 0.2" IN LENGTH AT BS 380 BETWEEN S-20L AND S-21L AS MARKED.

Part: FRAME — DAMAGED (BS 500D S21L) · airframe 61,937 hrs · 41,552 cycles

DO HFEC INSP. FOUND FRAME STANDOFF/TOOLING HOLE EDGE CRACKED ABOUT 0.2" IN LENGTH AT BS 500D S-21L AS MARKED

Part: SKIN — BULGED (BS 1104 S6L) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

BULGED (3.0" X 3.0") AT LH SIDE FUSELAGE EXTERNAL SKIN AT STA 1104, S-6L.

Part: SUPPORT ANGLE — CORRODED (LT WING) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

LH WING T/E UPPER PANEL SUPPORT ANGLE WAS CORRODED , WBL 185.

Part: SUPPORT ANGLE — CRACKED (LT WING) · airframe 61,927 hrs · 41,552 cycles

LH WING T/E UPPER PANEL SUPPORT ANGLE WAS CRACKED , WBL 84.24.

Part: BEAM — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 61,927 hrs · 41,552 cycles

CORROSION(3.0" X 3.0") AT LH HORIZONTAL STABILIZER TRAILING EDGE BEAM UPPER SURFACE AT STAB STA 168.

Part: STRAP — CORRODED (THRUST REVERSER) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

CORROSION ON NO.2 ENG LH THRUST REVERSER AFT COWL PANEL FRAME-STRAP AT 7 O'CLOCK POSITION.

Part: ANGLE — CRACKED (RT NACELLE) · airframe 61,937 hrs · 41,552 cycles

TWO EA "L" ANGLES CRACK ON RH NACELLE NAC.STA.278.52 AT WBL.192 AND WBL.204

Part: SEAT TRACK — CRACKED (COCKPIT) · airframe 61,937 hrs · 41,552 cycles

PILOT SIDE SEAT TRACK CRACK ON FWD I.B STOP STUD AREA.

Part: PLUG — CORRODED (LT WINDOW) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

CORROSION AT LH WINDOWS PLUG PANE , BETWEEN STA907 AND STA927 (L:2",W:0.5")

Part: SEAL — CORRODED (LT OVERWING) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

LH AFT OVERWING EMER EXIT HATCH LOW PORTION CORROSION AROUND DOOR SEAL AREA..

Part: PANEL — BULGED (THRUST REVERSER) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

BULGE ON NO.1 ENG LH THRUST REVERSER UPPER BIFURCATION PANEL AT NAC STA 256

Part: SUPPORT — CORRODED (RT MLG DOOR) · corrosion level 2 · airframe 61,937 hrs · 41,552 cycles

RH MLG CENTER DOOR UPPER SHOCK STRUT DOOR SUPPORT LINK CORRODED.

Part: WARNING MESSAGE — ACTIVATED (TAKE OFF) · airframe 61,711 hrs · 41,099 cycles

TO CONFIG WARNING ANNUNCIATED ON TAKEOFF. CYCLED SPEEDBRAKE HANDLE AND TAKEOFF WARNING TEST GOOD OK IAW AMM 32-09-00.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 60,953 hrs · 39,475 cycles

CRACK INDICATION FOUND AT STR 10R AT BS 500L -1 7/8" AND BS 500L + 1 6/8" TOTAL CRACK LENGTH 3 5/8". REPAIRED CRACK ON STR 10R PER SRM 53-00-01 REPAIR 30 FIG 201, ASSOCIATED WORKSHEETS AND IAW EO 5323-077 REV 1R

Part: HINGE PIN — CRACKED (ZONE 300) · airframe 58,996 hrs · 38,658 cycles

DURING INSPECTION OF PINS PER SB 737-55A1077 INSTRUCTIONS, IT WAS FOUND THE P/N 69-73120-1 LH OUTER HINGE PIN CRACKED AT ITS TAPERED SHANK AREA. THE DAMAGED PIN HAS BEEN REPLACED AND A DAMAGE REPORT WAS SENT TO BOEING.

Part: NONE — CRACKED (ZONE 200) · airframe 58,996 hrs · 38,658 cycles

DURING HFEC INSPECTION OF THE AFFECTED AREA PER SB737-53A1204 REV 2 INSTRUCTIONS THAT IS RELATED WITH AD2018-04-06, IT WAS FOUND AT BS 360 STR 9L LEVEL THE ATTACHMENT CLIP CRACKED. THE AFFECTED CLIP WAS REPLACED IAW ASAP E.O. # 5322-024 REV-IR, SUPPORTED BY FAA FORM 8110-3 AND AMOC APPROVAL TO AD2018-04-06.

Part: SKIN — CORRODED (ZONE 600) · airframe 58,996 hrs · 38,658 cycles

DURING STRUCTURAL INSPECTION IT WAS FOUND AT RH WING UPPER SKIN EXTERNAL SURFACE CORRODED AT SEVERAL PLACES, BETWEEN FRONT SPAR AND STR 13 AND BETWEEN WBL 77 AND WBL 133. THE DAMAGED AREAS WERE REPAIRED IAW ASGS EO # 2022-0406 REV IR AND SUPPORTED BY FAA FORM 8110-3.

Part: NONE — CRACKED (ZONE 100) · airframe 58,996 hrs · 38,658 cycles

DURING HFEC INSPECTION OF FRAMES, IAW AD2016-11-04 AND SB737-53A1279 INSTRUCTIONS, IT WAS FOUND AT FWD CARGO COMPT. BS 500E BETWEEN STR 20R-22R THE FRAME WEB WITH WIRE PENETRATION HOLE AND STANDOFF/TOOLING HOLES WITH CRACK. THE REPAIR WAS CARRIED OUT UNDER AEI E.O. #17799 REV-IR INSTRUCTIONS WITH FAA FORM 8110-3 APPROVAL AND AMOC TO AD2016-11-04.

Part: NONE — CRACKED (ZONE 100) · airframe 58,996 hrs · 38,658 cycles

DURING AN OPEN-HOLE HFEC INSPECTION OF FRAME WEB TOOLING HOLES, AND INSULATION ATTACHMENT HOLES ON THE LEFT AND RIGHT SIDE IAW BOEING SB 737-53A1362 IR (SEPT 20, 2018), PART 12, FIGURES 73, 74, 79 AND 80. (REF:AD 2019-15-07 (H): TABLE 11) IT WAS FOUND AT BS 967 THE FRAME WEB WITH TOOLING HOLE CRACKED BETWEEN S-24R AND S-25R. THE DAMAGED FRAME TOOLING HOLE WAS REPAIRED IAW AEI E.O. #17575 REV IR SUPPORTED BY FAA FORM 8110-3 AND AMOC APPROVAL TO AD 2019-15-07.

Part: KEELBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 58,996 hrs · 38,658 cycles

DURING THE STRUCTURAL INSPECTION, IT WAS FOUND ON FWD CARGO COMPT. BETWEEN BS 500G AND BS 520, (S-28L LEVEL) THE KEEL BEAM LOWER FLANGES CORRODED. THE REPAIR WAS CARRIED OUT UNDER ASAP E.O. #5322-020 REV-IR A INSTRUCTIONS WITH FAA FORM 8110-3 APPROVAL.