RYAN AIR, INC.

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by RYAN AIR INC (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by RYAN AIR INC (per NTSB report)

Operated by Ryan Air (per NTSB report)

Operated by Ryan Air (per NTSB report)

FOUND A CRACK IN STIFFENER ON THE LH WING FALSE SPAR AT W.S. 4900. THE CRACKED STIFFENER WAS R&R WITH NEW, FABRICATED STIFFENER MADE FROM 2024-T3 ALUMINUM .032" THICK, THE PRE-EXISTING SPACER HAD NO DAMAGE AND WAS REUSED. THE NEW STIFFENER WAS PRIMED WITH SUPER KOROPON BAC452 DESOTO PRIMER AND INSTALLED USING CR3213 BLIND FASTENERS, AND HLI 8PB HI-LOKS OF VARYING LENGTHS. ALL WORK PERFORMED WAS ACCOMPLISHED IRW CASA TL NO. 27 AND CASA SRM SECTION II, AND WAS DETERMINED TO BE AIRWORTHY. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AC MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

RH INBOARD FLAP, OUTBOARD PYLON BOTH FLAP HINGE PLATES CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGS (PIN: 212-13202-24-1 AND 212-13202-24-2) AND NEW SKIN (PIN: 212-13202-05-2). ALL PARTS AND BARE SURFACES PRIMED WITH SUPER KOROPON EPOXY PRIMER PRIOR TO INSTALLATION. INSTALLED NEW SKIN AND FITTINGS USING MS20470E RIVETS AND NASI 669 FASTENERS. TOP COATED SURFACES WITH IMRON ELITE BC TO MATCH COMPANY PAINT SCHEME. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION 2 FIG. 2.39 AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

RH INNER FLAP, OUTBOARD PYLON, OUTBOARD SKIN CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGS (PIN: 212-13202-24-1 AND 212-13202-24-2) AND NEW SKIN (PIN: 212-13202-05-2). ALL PARTS AND BARE SURFACES PRIMED WITH SUPER KOROPON EPOXY PRIMER PRIOR TO INSTALLATION. INSTALLED NEW SKIN AND FITTINGS USING MS20470E RIVETS AND NASI 669 FASTENERS. TOP COATED SURFACES WITH IMRON ELITE BC TO MATCH COMPANY PAINT SCHEME. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION 2 FIG. 2.39 AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

LEFT ENGINE OIL TEMPERATURE INCREASED TO REDLINE, PERFORMED PRECAUTIONARY SHUTDOWN. REMOVED AND REPLACED #1 OIL COOLER REF CASA MM 79-20-00 LEAK CHECK GOOD.

FLIGHT CONTROL STUCK FULL LEFT AILERON. REPLACED SHEARED RIVETS FROM AILERON TO AILERON POSITION INDICATING HORN USING MS20470AD RIVETS WITH REFERENCE TO SAAB 340 MM SRM 51-40-21-001 AND 40-30-001B.

RH WING HAS CRACK ON TRAILING EDGE UNDERSIDE ABOVE OUTBOARD FLAP ASSEMBLY AT WS4800 AS MARKED. REPAIRED CRACKED SECTION OF RT FLAP COVE SKIN. REMOVED 75MM X 25MM SECTION FROM INBOARD CRACKED AREA AND 90MM X 25MM SECTION FROM OUTBOARD CRACKED AREA. REMOVED RIVETS AS REQUIRED FROM UPPER FLAP COVE SKIN FOR ACCESS TO REPAIR AREA. FABRICATED FOR OUTER SECTION, FILLER PLATE AND REPAIR PLATE. FABRICATED FOR INBOARD SECTION, FILLER PLATE AND REPAIR PLATE. PLATES AND FILLERS FIT AND DRILLED TO REPAIR AREAS, ALL HOLES DIMPLED TO CLEARANCE REPAIR FROM FLAPS. ALL REPAIR PIECES ACID ETCHED, ALODINED, AND PRIMED WITH EPOXY PRIMER. INSTALLED REPAIR PLATES W/ MS20426AD RIVETS. REINSTALLED TOP COVE SKIN RIVETS PREVIOUSLY REMOVED WITH MS20426AD, AND CR3212 RIVETS AS REQUIRED FROM PREVIOUS INSTALLATION.

RIGHT WING HAS CRACK ON TRAILING EDGE UNDERSIDE ABOVE OUTBOARD FLAP ASSEMBLY AT WS5000 AS MARKED. REPAIRED CRACKED SECTION OF RH FLAP COVE SKIN. SEE 337 DATED 3/20/2026. REMOVED 75MM X 25MM SECTION FROM INBOARD CRACKED AREA AND 90MM X 25MM SECTION FROM OUTBOARD CRACKED AREA. REMOVED RIVETS AS REQUIRED FROM UPPER FLAP COVE SKIN FOR ACCESS TO REPAIR AREA. FABRICATED FOR OUTER SECTION FROM 2024T3 ALUMINUM 90MM X 25MM X 0.025" FILLER PLATE AND 50MM X 160MM X 0.025" REPAIR PLATE. FABRICATED FOR INBOARD SECTION FROM 2024T3 ALUMINUM 75MM X 25MM X 0.025" FILLER PLATE AND 140MM X 50MM X 0.025 REPAIR PLATE. PLATES AND FILLERS FIT AND DRILLED TO REPAIR AREAS, ALL HOLES DIMPLED TO CLEARANCE REPAIR FROM FLAPS. ALL REPAIR PIECES ACID ETCHED, ALODINED, AND PRIMED WITH EPOXY PRIMER. INSTALLED REPAIR PLATES W/ MS20426AD RIVETS. REINSTALLED TOP COVE SKIN RIVETS PREVIOUSLY REMOVED WITH MS20426AD, AND CR3212 RIVETS AS REQUIRED FROM PREVIOUS INSTALLATION. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION II FIG. 2.5 POS. 61 , APPENDIX II FIG. B9, AC43.13-1B 4.57F3 (P:4-19) AND PREVIOUS INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

REPAIR DOUBLER AT LOWER END OF FRAME 19 CRACKED (LH SIDE). REPLACED DOUBLER SEE 337 DATED 3/18/2026. CRACK FOUND AT DOUBLER FOR L/H FRAME 19. R&R WITH 2 DOUBLERS (ONE FWD AND ONE AFT OF FRAME) WITH .032IN 2024 T-3 ALUMINUM IRW CASA 212 SRM SECTION IV FIG 4.28 PAGES OA-02 AND CASA 212 SRM APPENDIX II REPAIRS B14 (PAGES 26-27), B15 (PAGES 28-29) AND B22 (PAGES 44-45). INSTALLED WITH AN470AD4 RIVETS IRW AC-43.13-1 B SECTION 4-57 PAGES 4-14 TO 4-17, USED PRE-EXISTING REPAIR'S RIVET SPACING & SIZE. DOUBLERS WERE ALODINED, PRIMED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR A/C MANUFACTURERS INSPECTION PROGRAM. W&B CHANGE WAS CONSIDERED NEGLIGIBLE.

WEAR MARK ON C CHANNEL SECTION BETWEEN L/H FRAMES 17-20. R&R WITH P/N: 212-23201-03-1 IRW CASA 212 SRM SECTION IV FIGURE 4.28 PAGES 0A-02 & INSTALLED WITH FASTENERS AN470E5, AN470E6, AN426E4, AN426E5, HL18-5, HL18-6, HL70-5, & HL70-6. IRW AC-43.13-1 B SECTION 4-57 PAGES 4-14 TO 4-17 & SECTION 4-57 PARAGRAPH E PAGES 4-19. USED PREVIOUS C-CHANNEL'S EXISTING HOLES FOR RIVET SPACING & SIZE. NEW C-CHANNEL WAS ALODINED, PRIMED, INSTALLED WET WITH PR1425 SEALANT AND PAINTED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR A/C MANUFACTURERS INSPECTION PROGRAM.

RH SIDE FR 6 & FR 11 FLOOR SUPPORT GUSSETS NUT PLATES CORRODED. REPLACED F6/F11 JUNCTION BARS. FOUND 4 FUSELAGE JUNCTION FITTINGS CORRODED ON RH AT FRAME 6 & 11 UNDERFLOOR. FOUND RH WALL SEAT RAIL MIDDLE SECTION CORRODED. F6 & ALL NEW PARTS ACID ETCHED, ALODINED, AND PRIMED W/ 511K011 EPOXY PRIMER. FITTINGS INSTALLED W/ THE FOLLOWING HARDWARE AS REQUIRED: HL18PB PINS, HL65PB PINS, & MS20470AD RIVETS. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, & REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION, CASA 212-200 SRM SECTION 4 FIG 4.17, & AC 43.13-1B SECTION 4-60B (P4-40), 4-57B (P4-16), 4-57E(P4-19). RH WALL SEAT RAIL SECTION. REMOVED SEAT RAIL. FABRICATED NEW SEAT RAIL FROM 206196-1 :2024-T3511 SEAT RAIL STOCK TO SAME DIMENSIONS AS PREVIOUSLY INSTALLED. INSTALLED SEAT RAIL USING CR3242 RIVETS, NAS1670 FASTENERS, & MS20426E RIVETS AS REQUIRED. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, & REPAIR CRITERIA WERE OBTAINED FROM PREVIOUS INSTALLATION. AS WELL AS AC43.13-1B 4.57B (P:4-16) 4.57F (P:4-19). CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT & BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

TWO CRACKS FOUND IN TRAILING EDGE OF LT LOWER INNER FLAP COVE AT APPROXIMATE WS 1800 & 2800. REMOVED 6 1/4 X 2 3/8 SECTION FROM OTBD CRACKED AREA & 4 1/4 X 2 3/8 SECTION FROM INBD CRACKED AREA. REMOVED RIVETS AS REQUIRED FROM UPPER FLAP COVE SKIN FOR ACCESS. FABRICATED FOR OUTER SECTION FILLER PLATE & REPAIR PLATE. FABRICATED FOR INBD SECTION FILLER PLATE AND REPAIR PLATE. PLATES AND FILLERS FIT AND DRILLED TO REPAIR AREAS, ALL HOLES DIMPLED TO CLEARANCE REPAIR FROM FLAPS. ALL REPAIR PIECES ACID ETCHED, ALODINED, AND PRIMED WITH EPOXY PRIMER. INSTALLED REPAIR PLATES. REINSTALLED TOP COVE SKIN RIVETS PREVIOUSLY REMOVED AS REQUIRED FROM PREVIOUS INSTALLATION. TOP COATED & CLEAR COAT TO MATCH.

L F11 REAR UNDER FLOOR FITTING CORRODED BEYOND LIMITS, F11 & F6 UNDERFLOOR FITTING HAVE CORROSION AT NUT PLATES. F6 & F11 JUNCTION BAR FITTINGS FOUND CORRODED. JUNCTION BAR FITTINGS. REMOVED ALL JUNCTION BAR FITTINGS FROM F6 & F11. REMOVED CORROSION UNDER & AROUND FITTING TO WEB INTERFACE. FITTED NEW FITTINGS TO WEBS & DRILLED TO EXISTING HOLE PATERNS. ALL NEW PARTS ACID ETCHED, ALODINED, & PRIMED WITH 511K011 EPOXY PRIMER. INSTALLED NEW FITTINGS ON ALL MATING SURFACES, INSTALLED WITH THE FOLLOWING HARDWARE: FITTINGS R & R 212-22406-06-1 RT FWD, FR 6 & LT AFT FR 11, 212-22406-06-2 LT FWD FR 6, & RT AFT FR 11, 212-22406-07-1 LT AFT, FR 6 & RT FWD FR 11, 212-22406-07-2 RT AFT FR 6 & LT FWD FR 11.

F11 CAP CORRODED BETWEEN SEAT RAILS. FL 1 UNDERFLOOR T ANGLE CENTER CAP - REMOVED FRAME 11 CAP SPLICE SECTION. FABRICATED NEW CAP SPLICE SECTION FROM 2024T351 0.125" X 1 5/8" X 1" ALUMINUM TO SAME SIZE, DESIGN, AND HOLE PATERN AS PREVIOUSLY INSTALLED. PARTS WERE ACID ETCHED, ALODINED, AND PRIMED WITH SUPER KOROPON 5111<011 EPOXY PRIMER. INSTALLED SPLICE SECTION USING MS20470E / MS20426E RIVETS AND I-ILI 8 HI-LOCKS.

F12 BUCKLED UNDER FLOOR. F12 UNDERFLOOR T ANGLE CENTER CAP - REMOVED DAMAGED T ANGLE. FABRICATED NEW T ANGLE FROM 2024T3 .085" X 1 5/8" X 1" TO SAME SIZE, DESIGN, AND HOLE PATTERN AS PREVIOUSLY INSTALLED. FABRICATED REPAIR DOUBLER 4 1/2"X 39 1/2" ALL NEW PARTS ACID ETCHED, ALODINED, AND PRIMED WITH 511K011 EPOXY PRIMER. INSTALLED T ANGLE AND DOUBLER USING MS20470AD RIVETS. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION, CASA 212-200 SRM SECTION 4 FIG 4.12, 4.17, APPENDIX II FIG. B19, B22 ILL, AND AC43.13-1 B 4-57B(P4-16), 4-57E(P4-19), SECTION 4-60B (P4-40).

F16 TOP CAP CORRODED AT NUT PLATES. REMOVED FRAME 16 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.100 THICK. ETCHED AND ALODINED THE "T" ANGLE AND PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED THE "T" ANGLE USING MS20470AD-4 AND MS2470AD-5 RIVETS IAW AC43.13-1B, PARA. 4-57.

- F15 WEB SAGGING UNDERFLOOR - REMOVED FRAME15 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.084 THICK, 38.5 INCHES LONG. STRAIGHTENED OUT THE WEB ON FRAME 15. FABRICATED A DOUBLER FROM 2024 T3, 0.032" THICK MEASURING 38.5" LONG X 3 1/4" TALL WITH A 1/4" FLANGE ALONG THE BOTTOM EDGE. ETCHED AND ALODINED THE FABRICATED PARTS AND PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED THE "T" ANGLE AND THE DOUBLER ON THE AFT SIDE OF THE WEB USING MS20470AD-4 AND MS20470AD-5 RIVETS. ALL WORK PERFORMED IAW THE CASA 212 SRM, SECTION IV FIG. 4.16 AND APPENDIX II FIG. B22 AS WELL AS AC43.13-1B, PARA. 4-57. SEE FAA FORM 337 DATED DEC. 8, 2025.

RT INBD. FLAP, THE OUTBD. PYLON AIRFRAME SIDE, BOTH OF THE HINGE PLATES HAVE PITTING CORROSION THAT IS BEYOND LIMITS. DRILLED BOTH HINGE PLATES AND THE INBD. AND OUTBD. PYLON SIDE SKINS OFF. FITTED AND INSTALLED NEW SIDE SKINS P/N 212-13202-05-1 (INBD.) AND P/N 212-13202-05-2 (OUTBD.) USING MS20470AD4 RIVETS AND MS20470E5 RIVETS IAW AC43.13-1B, SECTION 4, PARA. 4-57. INSTALLED 2 NEW HINGE PLATES P/N212-13202-24-1 (INBD.) AND P/N RA-212-13202-24-2 USING MS20470E-5 RIVETS, 2 JO-BOLTS P/N NAS1669-08 AND 3 CHERRYMAX RIVETS P/N CR3523-5, IAW THE CASA C212 STRUCTURAL REPAIR MANUAL SECTION II FIG. 2.24 AND AC43.13-1B CHAPTER 4, PARA 4-57. FORM 337 SUBMITTED, DATED JAN. 12, 2026

RIGHT FUSELAGE STRUT FITTINGS FAILED SID 53-20-07-250. LIFT STRUT FITTINGS. REMOVED FLOOR PANELS 2611127-18, 2611127-22 AND PULLY BRACKET 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-66 RIVETS REMOVED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 261113-6 AND 2611113-5. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.,188", ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5, USING NEW BOLTS,, RIVETS, AND SUBSTITUTED ONE RIVET PIN. APPLIED PS870 B1/2 TO EXTERIOR OPENING EDGES. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-18, 2611127-22, PULLY BRACKET 2612112-2, AND CAP ASSEMBLY 2611011-66. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION AS WELL AS: MM D2078-13 REVISION-42: SRM 51-40-00, TURBOPROP STANDARD PRACTICES MANUAL (REV 4) 20-10-65, AC43.13-1 B: 4-60B.1 (P4-40), AND 4-57E (P4-19).

RIGHT HORIZONTAL STAB TOP SKIN CRACKED JUST OTBD OF AFT ATTACH FITTING HSS 740. REMOVED TOP REAR SKIN FROM STAB ROOT TO WS 1200. ELEVATOR COVE SKIN WAS DE-RIVITED TO WS 1500 FOR ACCESS. FABRICATED NEW SKIN AND PATTER AS ORIGINAL INSTALLATION. ACID ETCHED, ALODINED, & PRIMED. INSTALLED NEW SKIN ON STABILIZER. REINSTALLED ELEVATOR COVE SKIN. AFFECTED AREAS WERE PAINTED.

TOP RUDDER STATIC WICK BASE DAMAGED (MAJOR REPAIR). REPLACED DAMAGED SKIN, SEE FORM 337 DATED 10/27/25 FOR FURTHER DETAIL. INSTALLED NEW STATIC IS CHARGE BASE P/N: 984.78.81.409 AND STATIC WICK UPPER RUDDER STATIC WICK ATTACH HOLES WORN BEYOND REPAIR LIMITS. REMOVED RUDDER FROM ACFT. REMOVED DAMAGED SKIN 555.40.12.075 FOR REPLACEMENT. REMOVED RIB 555.40.12.180 FOR ACESS DURING INSTALATION. FABRICATED NEW SKIN 55.40.12.075. SKIN WAS ACID ETCHED AND ALODINED. SKIN WAS PRIMED. INSTALLED SKIN 5.40.12.075 AND RIB 555.40.12.180. RUDDER BALLANCE WAS CHECKED PER PC12-45 SRM 51-60-03. RUDDER BALANCE FOUND TO BE WITHIN LIMITS AT 1/2 OZ OVERBALANCE.

FOUND CRACK IN RH WING TO FUSELAGE FAIRING AT FRAME F5. (SEE AOT-C212-53-0001 FOR DETAILS). REPAIRED CRACK DAMAGE AND REINFORCED F5 RH BY INSTALLATION OF SB KIT SB212530055K01. SEE 337 DATED 09/25/2025. FOR FURTHER DETAILS.

LH AILERON CENTER HINGE STRUCTURE, A PREVIOUS REPAIR PATCH IS CRACKED. REPAIR WAS ACCOMPLISHED AS FOLLOWS: REMOVED THE PREVIOUS CRACKED REPAIR ANGLE. USING THE ORIGINAL ANGLE AS A PATTERN A NEW ANGLE WAS FABRICATED FROM 301 STAINLESS STEEL 0.040 THICK AND INSTALLED IN THE SAME FASHION AS THE PREVIOUS INSTALLATION USING MS20470E -4 & -5 RIVETS AS THE ORIGINAL INSTALLATION AND IAW THE CASA SRM SECTION II, AND APPENDIX II FIG. 14, TYPE II AND FIG 15 (CRACK IN BEND RADIUS AT END OF FLANGE). THE ANGLE WAS INSTALLED "WET" USING PPG, PS 890 B1/2 ADHESIVE SEALANT. PRIOR TO INSTALLATION THE ANGLE WAS PRIMED WITH DESOTO SUPER KOROPON EPOXY PRIMER. AFTER INSTALLATION THE EXPOSED PORTIONS OF THE ANGLE WERE TOP COATED WITH IMRON POLYURETHANE ENAMEL (RED-EFFECT) WHICH WAS THEN CLEAR COATED WITH IMRON 8460S. W&B NEGLIGIBLE. FAA FORM 337 SUBMITTED, DATED AUG. 13, 2025.

LH FWD FRAME OF THE LOWER RAMP OPENING (P/N 212-23201-03-1) IS BUCKLED BETWEEN FRAME 17+18. REPLACED DAMAGED C CHANNEL 212-23201-03-1 WITH NEW. SEE 337 DATED 08/13/2025 FOR FURTHER INFORMATION. IMPACT DAMAGE FOUND IN C CHANNEL 212-23201-03-1 FWD OF F18. REMOVED C CHANNEL AND INTERCOSTALS AT F18. FABRICATED NEW INTERCOSTALS FOR F18 FROM 2024T3 ALUMINUM 0.032” THICK. ALL NEW PARTS WERE ACID ETCHED , ALODINED AND PRIMED WITH 511K011 SUPER KOROPON BEFORE INSTALLATION. INSTALLED NEW INTERCOSTALS AND C CHANNEL (P/N RA-212-23201-03-1) USING MS20470AD, MS20470E, AND MS20426AD RIVETS AS REQUIRED. C CHANNEL WAS INSTALLED WITH PS890B1/2 ON ALL MATING SURFACES. FIVE RIVETS BETWEEN F17 ANDF18 WERE SUBSTITUTED WITH HL18PB PINS. MATERIALS USED, RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212 SRM SECTION IV FIG. 4.28, AC43.13 1B 4.57E (P4-19), AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURER’S INSPECTION PROGRAM. W&B CONSIDERED NEGLIGIBLE.

"WHEN BLEED AIR IS TURNED ON, SMOKE ENTERS COCKPIT." "INSPECTED, NO SMOKE WAS OBSERVED COMING FROM THE ENGINE COMPARTMENT." CAUSE SUSPECTED TO BE DIRT/DUST IN BLEED AIR HEAT/VENT DISTRIBUTION.

IMPACT DAMAGE FOUND IN C CHANNEL AFT OF F19. REMOVED DAMAGED C CHANNEL AND INTERCOSTALS AT F18 AND F19 THAT WERE MODIFIED TO ACCEPT A PREVIOUS REPAIR TO OLD C CHANNEL. FABRICATED NEW INTERCOSTALS FOR F18 AND F19. ALL NEW PARTS WERE ACID ETCHED, ALODINED AND PRIMED WITH 511K011 SUPER KOROPON BEFORE INSTALLATION. INSTALLED NEW INTERCOSTALS AND C CHANNEL AS REQUIRED. C CHANNEL WAS INSTALLED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT & BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

CORROSION FOUND ON LOWER SURFACE OF LH WING AT W.S. 3450. REMOVED BRACE STRUT AT APPROXIMATE W.S. 3200 AND SPLICE PLATE AT APPROX. W.S. 3060 FOR ACCESS TO REPAIR AREA. REMOVED DAMAGED SKIN, REMOVED SEALANT FROM PREVIOUS INSTALLATION. FABRICATED NEW SKIN FROM 0.063" 2024T3 ALCLAD TO SAME DIMENSIONS AS ORIGINAL INSTALLATION. NEW SKIN WAS ACID ETCHED AND ALODINED, THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED NEW SKIN AND SERVICEABLE SPLICE PLATE WET USING PS890B1/2 SEALANT. USED MS20470E AND MS20426E RIVETS, HL18PB, HL19PB, AND HL62PB PINS AS REQUIRED FOR INSTALLATION. REINSTALLED BRACE STRUT USING HL18PB, HL62PB, AND HL218PB PINS AS REQUIRED. TOP COATED EXTERIOR REPAIR AREA WITH IMRON ELITE RED CORAL EFFECT, BRYCE OBSIDIAN BLACK, AND CLEAR COAT TO MATCH EXISTING PAINT PATTERN. MATERIALS USED, RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION AND C212-200 SRM SECTION 2 FIG. 2.27 AND AC43.13 1B 4.57E. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURER'S INSPECTION PROGRAM. W&B CHANGE CONSIDERED NEGLIGIBLE.

LEFT WING LIFT STRUT ATTACH FITTINGS ON FUSELAGE FOUND CORRODED OR DAMAGED. REMOVED FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKET 2612111-2, 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-67 AND 2611011-44 DE-RIVETED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.188" ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES, USING NEW AN174-30A BOLTS, AN174-32A BOLTS, AN173-6A BOLTS, MS20470AD5 RIVETS, AND SUBSTITUTED ONE RIVET ON THE LH INSTALLATION AND 6 RIVETS ON THE RH INSTALLATION FOR HL18PB 5-4 PINS. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKETS 2612111-2, 2612112-2. ALL WORK DONE IAW C208 MM D2078-13: REVISION - 42, CHAPTER 20-10-10, SRM 51-40-00, AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) MATERIALS USED: RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C208 MM D2078-13: REVISION - 42 CHAPTER 20-10-10, C208 SRM D5132-13: REVISION - 9 CHAPTER 51-40-00, AND FROM AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURES INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

RIGHT WING LIFT STRUT ATTACH FITTINGS ON FUSELAGE FOUND CORRODED OR DAMAGED. REMOVED FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKET 2612111-2, 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-67 AND 2611011-44 DE-RIVETED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.188" ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES, USING NEW AN174-30A BOLTS, AN174-32A BOLTS, AN173-6A BOLTS, MS20470AD5 RIVETS, AND SUBSTITUTED ONE RIVET ON THE LH INSTALLATION AND 6 RIVETS ON THE RH INSTALLATION FOR HL18PB 5-4 PINS. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKETS 2612111-2, 2612112-2. ALL WORK DONE IAW C208 MM D2078-13: REVISION - 42, CHAPTER 20-10-10, SRM 51-40-00, AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) MATERIALS USED: RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C208 MM D2078-13: REVISION - 42 CHAPTER 20-10-10, C208 SRM D5132-13: REVISION - 9 CHAPTER 51-40-00, AND FROM AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURES INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

UPPER REAR STRUT FITTING ON THE LEFT WING HAS DAMAGE TO STRUT MOUNTING HOLES AND STRUCTURE. WING LIFT STRUT ATTACH FITTINGS FOUND CORRODED OR DAMAGED ON LEFT AND RIGHT WING AND FUSELAGE. WINGS - REMOVED WING LIFT STRUT ATTACH FITTINGS ON BOTH SIDES. TRANSFERRED ALL FASTENER HOLES TO NEW FITTINGS, DRILLED TO 0.188" FOR -6 HI-LOCK AS WELL AS NAS464P3 BOLT HOLES AND 0.248" FOR NAS464P4 BOLTS. INSTALLED ON BOTH SIDES NEW 2622246-201, AND NEW 2622246-202 WITH HL18PB6 PINS AND NAS464P3 / P4 BOLTS. FUSELAGE - REMOVED FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKET 2612111-2, 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-67 AND 2611011-44 DE-RIVETED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.188" ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES, USING NEW AN174-30A BOLTS, AN174-32A BOLTS, AN173-6A BOLTS, MS20470AD5 RIVETS, AND SUBSTITUTED ONE RIVET ON THE LH INSTALLATION AND 6 RIVETS ON THE RH INSTALLATION FOR HL18PB 5-4 PINS. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKETS 2612111-2, 2612112-2. ALL WORK DONE IAW C208 MM D2078-13: REVISION - 42, CHAPTER 20-10-10, SRM 51-40-00, AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) MATERIALS USED: RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C208 MM D2078-13: REVISION - 42 CHAPTER 20-10-10, C208 SRM D5132-13: REVISION - 9 CHAPTER 51-40-00, AND FROM AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURES INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

UPPER REAR STRUT FITTINGS ON THE RIGHT WING HAVE DAMAGE TO STRUT MOUNTING HOLES AND STRUCTURE. WING LIFT STRUT ATTACH FITTINGS FOUND CORRODED/DAMAGED ON LEFT AND RIGHT WING AND FUSELAGE. WINGS - REMOVED WING LIFT STRUT ATTACH FITTINGS ON BOTH SIDES. TRANSFERRED ALL FASTENER HOLES TO NEW FITTINGS, DRILLED TO 0.188" FOR -6 HI-LOCK AS WELL AS NAS464P3 BOLT HOLES AND 0.248" FOR NAS464P4 BOLTS. INSTALLED ON BOTH SIDES NEW 2622246-201, AND NEW 2622246-202 WITH HL18PB6 PINS AND NAS464P3 / P4 BOLTS. FUSELAGE - REMOVED FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKET 2612111-2, 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-67 AND 2611011-44 DE-RIVETED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.188" ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5 ON BOTH SIDES, USING NEW AN174-30A BOLTS, AN174-32A BOLTS, AN173-6A BOLTS, MS20470AD5 RIVETS, AND SUBSTITUTED ONE RIVET ON THE LH INSTALLATION AND 6 RIVETS ON THE RH INSTALLATION FOR HL18PB 5-4 PINS. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-17, 2611127-18, 2611127-25, 2611127-22 AND PULLY BRACKETS 2612111-2, 2612112-2. ALL WORK DONE IAW C208 MM D2078-13: REVISION - 42, CHAPTER 20-10-10, SRM 51-40-00, AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) MATERIALS USED: RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C208 MM D2078-13: REVISION - 42 CHAPTER 20-10-10, C208 SRM D5132-13: REVISION - 9 CHAPTER 51-40-00, AND FROM AC43.13 1B 4-60B.1. (P4-40), AND 4-57E (P4-19) CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURES INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

RH SIDE WALL SEAT RAIL IS CORRODED AT FRAME 5F. REPLACED RH WALL MIDDLE SEAT RAIL SECTION. RH WALL SEAT RAIL SECTION. REMOVED SEAT RAIL. FABRICATED NEW SEAT RAIL FROM 206196-1 :2024-T3511 SEAT RAIL STOCK TO SAME DIMENSIONS AS PREVIOUSLY INSTALLED. INSTALLED SEAT RAIL USING CR3242 RIVETS, NAS1670 FASTENERS, AND MS20426E RIVETS AS REQUIRED. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM PREVIOUS INSTALLATION. AS WELL AS AC43.13-1B 4.57B (P:4-16) 4.57F (P:4-19). CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

CRACKED U CHANNEL IN AFT LH CENTER WING SECTION STATION 2380, AS FLAGGED. REPLACED CRACKED STIFFENER WITH NEW. SEE 337 DATED 03/11/2025 FOR FURTHER INFO. FAA FORM 337 STATES: FOUND CRACK IN STIFFENER ON THE LEFT CENTER WING AFT BEAM AT W.S. 2380. CRACKED STIFFENER WAS REMOVED AND REPLACED WITH NEW, FABRICATED STIFFENER MADE FROM 2024-T3 ALUMINUM, 0.032" THICK TO SAME DIMENSIONS AS PREVIOUSLY INSTALLED. REPLACEMENT STIFFENER WAS ALODINED, THEN PRIMED WITH SUPER KOROPON 511K011 AND INSTALLED USING MS20470AD RIVETS AND CR3213 BLIND FASTENERS. ALL WORK WAS PERFORMED WITH REFERENCE TO CASA 212 SRM SECTION II FIG 2.38. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM.

FOUND A SMALL PUNCTURE IN THE AFT SIDE OF THE RH WEB OF FRAME 11, 2 INCHES ABOVE FLOOR LEVEL. REPAIRED PER CASA ENGINEERING DOC 252EA-00020 REV A. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED MATERIAL. DAMAGED AREA INSPECTED BY HFEC, NO INDICATIONS OF CRACKING FOUND, SEE AIX REPORT NUMBER 11504 FOR FURTHER INFORMATION. PRIMED UNFINISHED PORTION OF REPAIR AREA WITH SUPER KOROPON. FABRICATED REPAIR DOUBLER FROM 2024T3 0.080" TO FIT IN REPAIR AREA. ACID ETCHED, ALODINED AND PRIMED REPAIR DOUBLER WITH SUPER KOROPON. INSTALLED REPAIR DOUBLER WITH PS890B1/2 BETWEEN SHEETS USING MS20470E5 RIVETS AND HL18PB PINS AS NECESSARY.

LH SEAT RAIL LONGITUDINAL WEB CRUSHED AT F17. REPAIRED IAW C212 SRM B26. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED SECTION OF WEB ~ 5.5" X 9.5". FABRICATED REPLACEMENT WEB SECTION TO SAME DIMENSIONS AS REMOVED FROM 2024T3 0.025", AND SPLICE PLATE 9.75" X 2.25" FROM 2024T3 0.025". ACID ETCHED AND ALODINED THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED REPLACEMENT WEB AND SPLICE PLATE USING MS20470AD4 AND MS2470E5 RIVETS AS REQUIRED PER ORIGINAL INSTALLATION AND REPAIR SPECIFICATIONS.

RH SEAT RAIL LONGITUDINAL WEB CRUSHED AT F17. REPAIRED IAW C212 SRM B26. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED SECTION OF WEB ~4.5 X 9". FABRICATED REPLACEMENT WEB SECTION TO SAME DIMENSIONS AS REMOVED FROM 2024T3 0.025", AND SPLICE PLATE 9.75" X 2.25" FROM 2024T3 0.025". ACID ETCHED AND ALODINED THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED REPLACEMENT WEB AND SPLICE PLATE USING MS20470AD AND MS20470E5 RIVETS AS REQUIRED PER ORIGINAL INSTALLATION AND REPAIR SPECIFICATIONS.

CRACK IN FORWARD BULKHEAD OF HORIZONTAL STABILIZER, RIGHT HAND SIDE NEAR UPPER LIGHTNING HOLE. "REPLACED BULKHEAD WITH NEW BULKHEAD 1212136-14. SEE 337 DATED 1/23/25 FOR FURTHER DETAIL."

L/H AIRFRAME LOWER STRUT FITTING FOUND TO BE CORRODED/PITTED. REPLACED BOTH LH LOWER STRUT FITTINGS WITH NEW 2611113-5 AND 2611113-6. SEE 337 DATED 10/29/2024 FOR FURTHER DETAIL.

RIGHT FLAP MIDDLE FLAP TRACK HAS SEVERE CORROSION INBOARD SIDE. REMOVED AND REPLACED RIGHT FLAP MIDDLE FLAP TRACK IN REFERENCE TO C208 SRM 51-40-00.

LOWER RH SIDE SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL

UNDER SIDE OF THE UPPER "T" FLANGE AT FRAME 11, THERE IS EXFOLIATION CORROSION UNDER THREE DIFFERENT NUT PLATES (CENTER AREA). REMOVED A 21 INCH SECTION OF THE CENTER "T" FLANGE BETWEEN THE TWO FLOOR SEAT TRACKS. FABRICATED A NEW LENGTH OF "T" FLANGE FROM THE SAME MATERIAL, 2024 T3511, 0.110 THICK ALUMINUM AND SPLICED IN THIS SECTION USING 4 (APPROXIMATELY 10 INCH LONG) 90 DEGREE EXTRUDED DOUBLER ANGLES TO BED INTO ENDS OF "T" SECTION FROM 2024 T3511 ALUMINUM OF 0.130 THICKNESS. ETCHED AND ALODINE ALL THE NEW PARTS, THEN PRIMED WITH SUPPER KOROPON EPOXY PRIMER. INSTALL THE NEW "T" SECTION AND ANGLES USING A MINIMUM OF 8 RIVETS ON EACH SIDE OF EACH SPLICE JOINT WITH MS20470E5 AND MS20429E5 SERIES RIVETS, MS20470E4 RIVETS ON THE UN-SPLICED SECTION AND 4 HL20PB5 HI-LOCKS. THIS WAS PERFORMED IAW THE CASA SRM APPX. II FIG. B19 REPAIR SCHEME. DETAILS ALSO ON FILE ON FORM 337 DATED 9/20/2024.

LOWER CARGO DOOR CUTOUT FRAME, RH SIDE "C" CHANNEL HAS 2 CHAFE MARKS IN THE UPPER RADIUS, JUST FWD. OF FRAME 19. BLENDED CHAFFED AREAS AND INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CHAFFED AREAS. SEE FORM 337 FOR DETAILS OF THE REPAIR.

FRAME 19 CRACKED BEHIND LH ACTUATOR ATTACH POINT. FABRICATED AND INSTALLED NEW LOWER FRAME 19 AND ACTUATOR ATTACH POINT DOUBLER. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL

FRAME 19 RH CRACKED BEHIND ACTUATOR ATTACH POINT. REMOVED THE OLD REINFORCEMENT DOUBLER REPAIR. FABRICATED A NEW DOUBLER FROM 2024 T3 ALCLAD ALUMINUM 0.050 THICK, 6 INCHES TALLER THAN THE PREVIOUS DOUBLER (10 INCHES TOTAL). ETCHED AND ALODINE THE DOUBLER AND PRIMED WITH EPOXY PRIMER.

LOWER LH SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.

LOWER CARGO DOOR CUTOUT FRAME, LH SIDE "C" CHANNEL HAS A CRACK IN THE UPPER FLANGE JUST AFT OF FRAME 19. INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CRACK.. SEE FORM 337 FOR DETAILS OF THE REPAIR.

RH SIDE EXTRUSION ON FWD. SIDE OF FRAME 11, UNDER FLOOR IS CRACKED. (BOUNDARY LAYER CORROSION). REPLACED EXTRUSION WITH NEW 212-22406-06-1. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.

LH SIDE EXTRUSION ON AFT SIDE OF FRAME 11, UNDER FLOOR HAS EXFOLIATION CORROSION. REPLACED EXTRUSION WITH NEW 212-22406-07-2. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.

MECHANIC INDUCED DAMAGE TO FRAME 11 WEB, UNDER THE FLOOR, 5 INCHES LEFT OF CENTER. DRESSED OUT THE DAMAGED AREA & FABRICATED A DOUBLER 2 1/4 INCH BY 3 INCHES OF 2024 T3 ALUMINUM 0.040 THICK. ETCHED & ALODINED THAN PRIMED WITH SUPPER KOROPON EPOXY PRIMER. INSTALLED USING MS20470E4 AND E5 SERIES RIVETS. REPAIR WAS PERFORMED IAW THE CASA SRM, APPEX II, FIG. B25, WEB REPAIRS. FAA FORM 337 SUBMITTED, DATED 10/8/2024.

FRAME 16 IS BUCKLED UNDER THE FLOOR JUST LEFT OF CENTER. REMOVED BUCKLED SECTION OF FRAME 16 WEB AND SPLICED IN A NEW PIECE OF MATERIAL. WORK WAS DONE REFERENCING THE CASA 212 STRUCTURAL REPAIR MANUAL APPENDIX II FIGURE B25. DETAILS OF THE REPAIR ARE AVAILABLE ON THE FORM 337.

LH HORIZONTAL STABILIZER FORWARD ATTACH FITTING HAS CORROSION AT THE GUIDE PIN HOLE FOR THE TRIANGLE LEADING EDGE. (LOCATED INSIDE THE STABILIZER). REMOVED THE HORIZONTAL STABILIZER. DRESSED OUT THE CORROSION AND TREATED (ETCHED AND ALODYNED) PER THE CASA CORROSION CONTROL MANUAL SECTION 5, PARA 5.4, PG. 5-11 THRU 5-20, THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. REINSTALLED THE HORIZONTAL STABILIZER IAW THE CASA MM CH. 55-10-00.