N305GT

Part: SKIN — DENTED (BS 498-502) · airframe 47,097 hrs · 39,420 cycles

DURING ROUTINE MAINTENANCE AT THE COOPESA MAINTENANCE FACILITY IN SAN JOSE, COSTA RICA (SJO), THE FUSELAGE SKIN BETWEEN STA 498 AND STA 502 AND BETWEEN S-21R AND S-25R WAS FOUND TO HAVE 3 EA. DENTS. REPAIRED PER ENGINEERING AUTHORIZATION Nº 72-2020-179 AND DOCUMENTED UNDER JOB: A1J170 NRI 1-35.

Part: SKIN — CRACKED (BS 827-847) · airframe 47,097 hrs · 39,420 cycles

DURING SCHEDULED MAINTENANCE AT COOPESA FACILITY IN SAN JOSE, COSTA RICA (SJO), THE FUSELAGE SKIN BETWEEN STA 827 AND STA 847 AND BETWEEN STGR-1 AND STGR-2L UNDER THE ELT ANTENNA WAS FOUND WITH OIL CANNING AND CRACK DAMAGE. THE DAMAGE WAS REPAIRED PER ENGINEERING AUTHORIZATION Nº 69-2020-270_P1 UNDER JOB: A1J170 NRI 2-28.

Part: SKIN — DENTED (BS 345.5) · airframe 47,097 hrs · 39,420 cycles

DURING MAINTENANCE VISIT, A DENT WAS NOTED ON THE FUSELAGE SKIN AT STA. 345.5, ABOVE STR. 20R. THE DENT WAS OUT OF LIMITS PER 737-400 SRM. THE DAMAGE WAS REPAIRED PER ENGINEERING AUTHORIZATION Nº 20-2020-028 AND DOCUMENTED UNDER JOB: A1J170 NRI 1-32.

Part: WEB — CORRODED (BS 540) · corrosion level 3 · airframe 47,097 hrs · 39,420 cycles

DURING SCHEDULED MAINTENANCE AT THE COOPESA MAINTENANCE FACILITY IN SAN JOSE, COSTA RICA (SJO), THE WING CENTER SECTION FRONT SPAR WEB AT BS 540.00 AND LBL 8 WAS FOUND TO HAVE CORROSION DAMAGE. WAS REPAIRED PER ENGINEERING AUTHORIZATION Nº 32-2020-118 AND DOCUMENTED UNDER JOB: A1J170 NRI 1-41.

Part: SKIN — DENTED (BS 301) · airframe 47,097 hrs · 39,420 cycles

DURING ROUTINE MAINTENANCE AT MAINTENANCE FACILITY, THE LOWER FUSELAGE EXTERNAL SKIN JUST BELOW THE SERVICE DOOR, AT BS 301.5, BETWEEN STR-17 R AND STR-18 R WAS FOUND TO HAVE A SHALLOW DENT.

Part: KEELBEAM — CORRODED (BS 630-646) · corrosion level 2 · airframe 47,097 hrs · 39,420 cycles

DURING ROUTINE MAINTENANCE AT THE COOPESA MAINTENANCE FACILITY IN SAN JOSE, COSTA RICA (SJO), THE KEEL BEAM STRAP BETWEEN STA 630 AND STA 646 WAS FOUND TO HAVE CORROSION. WAS REPAIRED PER ENGINEERING AUTHORIZATION Nº 72-2020-181 UNDER JOB: A1J170 NRI 1-61.

Part: CONTROL PANEL — FAILED (COCKPIT) · airframe 60,130 hrs · 35,218 cycles

AIRCRAFT GROUNDED. MCP, AUTOPILOT AND FLIGHT DIRECTOR FAILED IN FLIGHT ON CLIMB OUT. REPLACED MCP IAW AMM 22-11-34. OPS CK NORMAL. (LP 71462 ITEM 2) REF LP 71462 ITEM #1 - AUTOPILOT FAIL INFLIGH . CHANGE FCC B PRECAUTIONARY PER MX CTL. R & R FCC B REF AMM 22-11-33. SYS OPS CKS GOOD PER AMM 22-11-33 / 501. A/C REMAINS CAT III A. (LP 71463) LIGHTNING STRIKE INSP DUE FROM LP 71462 ITEM 2. CREW REPORTED POSSIBLE LIGHTNING STRIKE. PERFORMED SATISFACTORY CONDITIONAL INSPECTION PER AMM 05-51-27. NO AIRCRAFT OR SYSTEM DAMAGE NOTED.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

DURING THE STRUCTURE INSPECTION, IT WAS FOUND AT LOWER FUSELAGE SKIN WITH CORROSION AT BS 648 BETWEEN STRINGER 28R AND 28L, DME2 ANTENNA AREA. THE DAMAGED AREA WAS REPAIRED PER INSTRUCTIONS PROVIDED ON SR 4-4392840368 AND APPROVED UNDER FAA FORM 8100-9 PROVIDED.

Part: SKIN — DENTED (ZONE 400) · airframe 45,283 hrs · 38,394 cycles

DURING THE STRUCTURE INSPECTION, IT WAS FOUND AT ENGINE NR 1 NOSE COWL LIP SKIN WITH DENS AT 8 O'CLOCK AND 11 O'CLOCK POSITION. THE DAMAGED AREAS WERE REPAIRED IAW SRM 54-10-01 FIGURE 201 REPAIR 1 DETAIL II.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

DURING THE STRUCTURE INSPECTION, IT WAS FOUND AT AFT CARGO COMPARTMENT FRAME WITH CORROSION AT BS 727F BETWEEN STRINGER 26R AND 26L. THE DAMAGED PART WAS REPAIRED IAW SRM 53-00-07 FIGURE 202 REPAIR 17 DETAIL IV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

DURING THE STRUCTURE INSPECTION, IT WAS FOUND AT AFT CARGO COMPARTMENT FLOOR SUPPORT ZEE WITH CORROSION FROM BS 727 TO BS 947, STRINGER 26L. THE DAMAGED PART WAS REPAIRED IAW SRM 53-60-53 FIGURE 201 REPAIR 4 FROM ZEE FROM BS 787 TO BS 947 AT STR 26L, THE OTHER SECTION OF THE ZEE WAS FOUND WITHIN ALLOWABLE DAMAGE IAW SRM 51-10-02 PARAG. 14A AND 53-60-53 AD1 FIGURE 101 DETAIL V.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME SUPPORT CLIP WITH CRACK AT BS 787 STR-26L. THE MENTIONED PART WAS REPLACED BY A NEW ONE AS PER SRM 51-10-02 PARAG 8.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

UPPPER FUSELAGE CARGO CABIN STR-8AR, BETWEEN BS 332.1 AND BS 344 INTERCOSTAL T-CHORD CRACKED. THE MENTIONED T-CHORD WAS REPLACED IAW AIR EO3753A37 DATED MAR 01, 2017, PART 1 STEP 4 AND 5 AND SB 737-53A1108 REV. 7 DATED JULY 07, 2017 PART 4 STEP 5 AND 6.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME WITH CORROSION AT BS 787 BETWEEN STR-26L AND 27L. FRAME SECTION WAS REPLACED BY NEW ONE AS PER SRM 51-10-02 PARG. 8.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FLOOR SUPPOR ANGLE WITH CORROSION AT BS 947.5 BETWEEN STR-26L AND 26R. THE DAMAGED PART WAS REPLACED IAW SRM 51-10-02 PARAG 8.

Part: FRAME — CRACKED (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

MAIN CARGO COMPARTMENT BS 616 WL 201 RBL 64 FRAME WITH CRACK. PERFORMED REPAIR FRAME AT BS 616 WL 201 RBL64 IAW SB 737-53A1254 SECTION 3B6 PART 6 FIG. 20, 21 AND 22 REV. 2 FEB 22, 2012

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT CLIP WITH CORROSION AT BS 787 STR-27R. THE MENTIONED CLIP WAS REPLACED AS PER SRM 51-10-02 PARAG. 8.

Part: SUPPORT FITTING — CORRODED (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME SUPPORT CLIP WITH CORROSION AT BS 807, STR-27R, THE MENTIONES CLIP WAS REPLACED BY A NEW ONE AS PER SRM 51-10-02 PARAG 8

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARMENT WEB WITH CORROSION FROM BS 794 AND BS 847 AT SCUFF PLATE AREA. THE MENTIONES WEB WAS REPLACED BY A NEW ONE AS PER SRM 51-10-02 PARG. 8

Part: BULKHEAD — CANNING (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

LOWER FUSELAGE BS 1016 AFT PRESSURE BULKHEAD WEB, FROM THE AFT SIDE OF BULHEAD AT LEVEL OF STR-8L WEB WITH OIL CANNING. THE WEB WAS REPAIRED AS PER SRM 53-80-08 FIG. 203 REPAIR 12.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME ATTACH CLIP WITH CORROSION AT BS 787 STR-26R. THE MNETIONED CLIP WAS REPLACED AS PER SRM 51-10-02 PARAG. 8.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME SUPPORT ANGLE WITH CORROSION AT BS 807 ON STR-27L. THE SUPPORT ANGLE WAS REPLACED IAW SRM 51-10-02 PARG. 8

Part: DOOR SILL — CRACKED (FUSELAGE) · airframe 45,283 hrs · 38,394 cycles

UPPER FUSELAGE CARGO CABIN BS 294.5, STR-17R, LOWER MAIL SILL WEB CRACKED. THE MENTIONED PART WAS REPLACED IAW EO3753A008 REV. 1 DATED 17 SEP 2018 AND SB 737-53A1241 R1 DATED NOV 06, 2013.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,283 hrs · 38,394 cycles

AFT CARGO COMPARTMENT FRAME WITH CORROSION AT BS 807 BETWEEN STR-25L AND 27R. THE MENTIONED FRAME WAS REPAIRED AS PER SRM 53-00-07 FIG. 202 REPAIR 17 DETAIL V.

Part: STRINGER CLIP — CRACKED (BS 360) · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION, FOUND THE STRINGER CLIP AT BS 360, STRINGER 10L, CRACKED. THE STRINGER CLIP WAS REPLACED IAW SRM 51-10-02, PARAGRAPH 8.

Part: FITTING — CORRODED (STRINGER 27L) · corrosion level 2 · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION IN THE FWD CARGO BAY AREA, FOUND AT BS 540, THE STRINGER 27L WITH THE END FITTING CORRODED. THE DAMAGED END FITTING WAS REPLACED IAW SRM 51-10-02, PARAGRAPH 8.

Part: ATTACH ANGLE — CRACKED (BS 348) · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION, FOUND BS 348.2, STRINGER 15L, AN INTERNAL ATTACH ANGLE FOUND CRACKED. THE ATTACH ANGLE WAS REPLACED IAW SB 737-53A1240, WORK INSTRUCTIONS, PART 4, PARAGRAPH C, REV. 1 AND EAM 3553020-4, SECTION 3.

Part: FRAME — CRACKED (BS 500F) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT CARGO CABIN, THE BS 500F FRAME WEB WAS FOUND WITH CRACK BETWEEN STR 8L AND STR 9L, SPECIFICALLY AT AC SUPPORT ATTACH BRACKET. MENTIONED DAMAGE WAS REPAIRED IAW SB737-53-1216 PART III FIGURE 8.

Part: WEB — CORRODED (LT MLG WW) · corrosion level 2 · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION AT THE LT MAIN WHEEL WELL, FOUND SIDE WEB CORRODED, BS 695 - 706, STRINGER 18AL. THE WEB WAS REPLACED IAW SRM 51-10-02, PARAGRAPH 8, DRAWINGS 69-78163, AND 65-46877.

Part: FITTING — DAMAGED (BS 927) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT THE UPPER FUSELAGE MAIN CARGO CABIN, IT WAS FOUND AT BS 927 STR 17RH, THE FRAME ATTACH FITTING WITH FASTENER HOLE WITH BROKEN SCREW. THE AFFECTED FRAME ATTACH FITTING WAS REPAIRED AS PER AEI E.O.5332 AND APPROVED UNDER FAA 8110-3 FORM PROVIDED BY AEI.

Part: FRAME — CORRODED (BS 520) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT AIR CONDITION DISTRIBUTION BAY, IT WAS REPORTED AT BS 520 THE FRAME SECTION BETWEEN STRINGERS 27L AND 28L CORRODED. THE DAMAGED FRAME SECTION WAS REPAIRED IAW SRM 53-00-07, FIGURE 201 REPAIR 5.

Part: FRAME — CRACKED (BS 348.2) · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION, FOUND THE BS 348.2FRAME CRACKED AT STRINGER 15L, THE FRAME SECTION WAS REPLACED IAW SB 737-53A1240, WORK INSTRUCTIONS PART 4A, REV 1, AND EAM 3553020-4, SECTION 1.

Part: SHEAR WEB — CRACKED (BS 348) · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION, FOUND BS 348.2, BETWEEN STRINGERS 16L AND 17L SHEAR WEB CRACKED. THE SHEAR WEB WAS REPLACED IAW SB737-53A1240, WORK INSTRUCTIONS, PART 4, PARAGRAPH F, REV 1, AND EAM3353020-4, SECTION 6.

Part: FRAME — CRACKED (BS 500A) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT CARGO CABIN, THE BS 500A FRAME WEB WAS FOUND WITH CRACK BETWEEN STRINGERS 8R AND 9R, SPECIFICALLY AT AC SUPPORT ATTACH BRACKET. REPAIRED IAW SB737-53-1216, PART III, FIGURE 8.

Part: CHANNEL — CORRODED (BS 986-1006) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT THE LOWER FUSELAGE WATER WASTE PANEL AREA, FOUND THE INNER SIDE CHANNEL CORRODED BETWEEN BS 986 - 1006, STRINGERS 25 - 26R. THE CHANNEL WAS REPLACED IAW SRM 51-10-02, PARAGRAPH 8, AND DRAWING 65-55843.

Part: FRAME — CRACKED (BS 727B) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT CARGO CABIN, THE BS 727B FRAME WEB WAS FOUND WITH CRACK BETWEEN STRINGERS 8R AND 9R, SPECIFICALLY AT AC SUPPORT ATTACH BRACKET. THE DAMAGE WAS REPAIRED IAW SB737-53-1216, PART III, FIGURE 8.

Part: BEAM — CRACKED (BS 178) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION, FOUND AT BS 178 RBL 71.1 WBL 226 - 231 THE VERTICAL BEAM WEB CRACKED, THE BEAM WAS REPAIRED IAW SRM 53-10-08, FIG 201, REPAIR 12, DETAIL V.

Part: FRAME — CRACKED (BS 727B) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION AT CARGO CABIN, THE BS 727B FRAME WEB WAS FOUND WITH CRACK BETWEEN STRINGERS 8L AND 9L. THE DAMAGE WAS REPAIRED IAW SB737-53-1216, PART III, FIGURE 8.

Part: SPAR WEB — DAMAGED (RT WING) · airframe 43,510 hrs · 37,257 cycles

DURING A STRUCTURAL INSPECTION AT THE RT WING REAR SPAR WEB, FOUND TWO FASTENER HOLES ELONGATED AT RSS 206.11 AND RSS 273. THE ELONGATED FASTENER HOLES WERE REPAIRED IAW S/R 3-3949229341, AND EO COO-EO-2017-3990-R01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,510 hrs · 37,257 cycles

DURING THE INSPECTION ACCOMPLISHMENT PER EAM3353009-1 REV NR 3 RELATED WITH AD2016-11-04, IT WAS FOUND AT THE LOWER FUSELAGE FWD CARGO COMPARTMENT. STA500G, BETWEEN STR20R AND STR21R FRAME WITH CRACK AT THE 0.500 INCH DIAMETER HOLE. THE AFFECTED FRAME BS 500G WAS REPAIRED IAW SRM 53-00-07 REPAIR 20, AS IS STATED ON SB737-53A1279 REV. 2.

Part: FRAME — DAMAGED (BS 907) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION, BS 907 FRAME, STRINGER 17L AND 17R, FOUND SEVERAL FASTENER HOLES DAMAGED, THE FRAME AND ATTACHING PARTS WERE REPAIRED IAW EO 5136.

Part: FRAME — CRACKED (BS 178 BULKHEAD) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION OF THE UPPER FWD FUSELAGE IT WAS FOUND AT BS 178 WL 207 THE BULKHEAD LH SIDE CHORD WITH CRACK. THE AFFECTED CHORD HAS BEEN REPLACED IN ACCORDANCE WITH SB 737-53A1208

Part: SKIN — CANNING (BS 1006) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION OF THE UPPER REAR FUSELAGE IT WAS FOUND THE FUSELAGE SKIN WITH AN OIL CAN AT BS 1006 3 INCH BELOW STRG 16L. THE AFFECTED SKIN AREA HAS BEEN REPAIRED IAW SRM 53-80-01, REPAIR 6.

Part: SKIN — CRACKED (RT WING) · airframe 43,510 hrs · 37,257 cycles

DURING INSPECTION, THERE WERE FIVE CRACKS FOUND IN THE UPPER SKIN, T/E AREA BETWEEN RSS 238 AND 267, THE RT WING UPPER SKIN WAS REPAIRED IAW SRM 57-20-01, REPAIR 7.

Part: SKIN — CRACKED (LT WING) · airframe 43,510 hrs · 37,257 cycles

DURING INSPECTION, OF THE LT REAR SPAR UPPER CHORD, THERE WERE FOUND THREE CRACKS AT UPPER SKIN T/E AREA, THE AFFECTED LT WING UPPER SKIN AREA WAS REPAIRED.

Part: SPAR — CRACKED (LT WING) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION THE LT WING REAR SPAR UPPER CHORD WAS FOUND CRACKED AT RSS 223, THE AFFECTED SPAR SECTION WAS REPAIRED IAW SRM 57-20-10, REPAIR 4.

Part: SPAR — CRACKED (RT WING) · airframe 43,510 hrs · 37,257 cycles

DURING THE STRUCTURAL INSPECTION, THE RT WING REAR SPAR WEB AND UPPER CHORD WERE FOUND WITH A CRACK AT RSS 224. THE AFFECTED WEB AND UPPER CHORD SECTIONS WERE REPAIRED IAW SRM 57-20-10, REPAIRS 4 AND 6.