What was found
CRACK ACCESS PANEL 194GR BODY FAIRING AT LOWER FUSELAGE 2025-340197<[01] REJECT STEP 10. BECAUSE THE REPAIR PLIES INSTALLED DO NOT MEET THE OVERLAP REQUIREMENTS IAW B737-700 SRM 51-70-04-2R-2 REPAIR 2>CURED THE REPAIR PLIES AND PERFORMED POST REPAIR INSPECTION (TAP TEST) ON REPAIRED AREA AND FOUND IN GOOD CONDITIONS IAW B737-700 SRM 51-70-04-2R-2 REPAIR 2 PARAGRAPH 4.I;J AND B737-700 SRM 51-70-04-2R-0 REPAIR GENERAL PARAGRAPH 4.N AND O.(1); B737-700 NDT MANUAL PART1 51-05-01. TOOL USED: HOT BONDER P/N:HCS9200B-AV S/N:18196021 DUE DATE: 22-FEB-26. CURED TIME: 220 MINUTES AT 200 DEGREES FAHRENHEIT.;[03] VERIFIED CORRECTION IN C/A # 2 HUGO TEJADA ( TECHNICIAN). REMOVE AND INSTALL NEW REPAIR PLIES. THE PROCESS IS DOCUMENTED IN PARTIAL WORK STEPS 11 TO 14.<BR> <BR>CURED THE REPAIR PLIES AND PERFORMED POST REPAIR INSPECTION (TAP TEST) ON REPAIRED AREA AND FOUND IN GOOD CONDITIONS IAW B737-700 SRM 51-70-04-2R-2 REPAIR 2 PARAGRAPH 4.I;J AND B737-700 SRM 51-70-04-2R-0 REPAIR GENERAL PARAGRAPH 4.N AND O.(1); B737-700 NDT MANUAL PART1 51-05-01. TOOL USED: HOT BONDER P/N:HCS9200B-AV S/N:18196021 DUE DATE: 22-FEB-26. CURED TIME: 220 MINUTES AT 200 DEGREES FAHRENHEIT.;[04] REPAIRED ACCESS PANEL 194GR BODY FAIRING AT LOWER FUSELAGE IAW B737-700 SRM 51-70-04-2R-2 REPAIR 2. SEE INDIVIDUAL SIGNOFFS BELOW.;[05] REPAIRED ACCESS PANEL 194GR BODY FAIRING AT LOWER FUSELAGE IAW B737-700 SRM 51-70-04-2R-2 REPAIR 2. SEE INDIVIDUAL SIGNOFFS BELOW.