N831ME

ATA 5310

Part: FLOOR SKIN — DENTED (ZONE 100) · airframe 11,412 hrs · 34,388 cycles

DENTS AND LOCALIZED DELAMINATION WERE FOUND ON THE UNDERSIDE SKIN OF THE CABIN FLOOR, MEASURING UP TO 89 MM × 914 MM (3.5 IN × 36 IN) AND 50 MM × 610 MM (2 IN × 24 IN). REPAIRED IN ACCORDANCE WITH AIRBUS HELICOPTERS RDAS RDAS EC135 53 2026 2040A, ISSUE DATE 11 JUN 2026. THE REPAIR INCLUDED REMOVAL OF DAMAGED SKIN, INSPECTION AND REPAIR OF HONEYCOMB CORE AS REQUIRED, AND INSTALLATION OF AN ALUMINUM UNDERSIDE SKIN DOUBLER BONDED AND CURED PER APPROVED DATA. SURFACE PROTECTION AND FINISH WERE RESTORED. REPAIR INSPECTED BY VISUAL AND TAP TEST AND FOUND SATISFACTORY.

ATA 6210

Part: LINER — CRACKED (M/R BLADE) · airframe 11,412 hrs · 34,388 cycles

POST REMOVING DAMAGED TEFLON LINER ON BLADE. DISCOVERED CRACK ON WEDGE ON WEDGE OF UPPER TRAILING BUSH HOLE TO OUTER ROVING LOOP.

ATA 5314

Part: KEELBEAM — CORRODED (ZONE 100) · airframe 11,412 hrs · 34,388 cycles

DAMAGE WAS NOTED TO THE RH KEEL BEAM CAP (P/N: L533M1010203) HORIZONTAL FLANGE IN THE FORM OF SEVERAL AREAS OF CORROSION. THERE ARE REPORTED TO BE 3EA AREAS OF CORROSION IN THE RH KEEL BEAM CAP. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2026-1925, ISSUE A.

ATA 5310

Part: DECK PLATE — DENTED (ZONE 200) · airframe 11,412 hrs · 34,388 cycles

DURING 500-HOUR INSPECTION, A DENT WAS DISCOVERED ON THE R/H SIDE OF THE TRANSMISSION DECK (P/N: L533M1017295). THE MAXIMUM DEPTH IS APPROXIMATELY 0.022" WITH A MAXIMUM DIAMETER OF 0.8. AN APPROXIMATE LOCATION OF THE DAMAGE IS AT STA. 4600MM, W.L. 2465MM, AND R.B.L. 50MM. A DETAILED DESCRIPTION OF THE DAMAGE REPAIR AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 23-5300-EA-5655, INITIAL REVISION DATED 18 MAY 2026 AND IS SUBSTANTIATED BY FAA FORM 8110-3,

ATA 2312

Part: VHF COMM — FAULTED (ZONE 100) · airframe 11,061 hrs · 336,421 cycles

#1 VHF RADIO STOPPED TRANSMITTING. SHORTLY AFTER, DURING LEVEL FLIGHT, IFR, 6000MSL, 120KN, ON ATC VECTOR IN HEADING MODE AND THE NAV SOURCE IN ILS2, THE AUTOPILOT MADE AN UNCOMMANDED, ABRUPT LEFT TURN AND PITCH UP. THE MASTER CAUTION ILLUMINATED ALONG WITH AN AUTOPILOT WARNING LIGHT AND THE AUTOPILOT TURNED OFF. CONTINUED THE ILS APPROACH WITH THE AUTOPILOT IN OFF MODE AND BY USING #2 VHF RADIO TO COMMUNICATE WITH CENTER. 07/25 RML NOTE: COULD NOT DUPLICATE AUTO PILOT FAULT ON GROUND AND NO DISCREPANCIES NOTED DURING T/S. COULD NOT MOC FLIGHT DUE TO WEATHER. WILL PERFORM FUNCTIONAL CHECKS THIS MORNING. PERFORMED MULTIPLE FUNCTION CHECKS. THIS AIRCRAFT HAS BEEN RETURNED TO REVENUE SERVICE, REF # MEC-012816.

ATA 5311

Part: FRAME — CRACKED (ZONE 200) · airframe 10,039 hrs · 31,508 cycles

DAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH.

ATA 5311

Part: ANGLE — CRACKED (ZONE 200) · airframe 10,039 hrs · 31,508 cycles

DAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH

ATA 5311

Part: ANGLE — CRACKED (ZONE 200) · airframe 10,039 hrs · 31,508 cycles

DAMAGE WAS FOUND TO THE FRAME 5 (P/N: L533M1088219/L533M1105219) IN THE FORM OF CRACKS. THERE ARE FOUR CRACKS TO BOTH THE L/H AND R/H FRAME NEAR THE UPPER AND LOWER MOST POINTS WHERE THE MEDICAL INTERIOR BEAM ATTACHES. THE LONGEST CRACK MEASURED TO BE APPROXIMATELY 1.625" ON THE FWD L/H SIDE OF THE FRAME 5 UPPER MOUNT LOCATION OF THE MEDICAL WALL. CRACKS WERE ALSO DISCOVERED ON BOTH L/H AND R/H FRAME 5 ANGLES (P/N: L533M1088218/L533M1105218) AT THE AFT INBOARD LOWER ATTACHMENT POINT OF THE MEDICAL STC. THE L/H ANGLE CRACKED MEASURED APPROXIMATELY 1.05", WITH THE R/H CRACK MEASURING 1.0" IN LENGTH.

ATA 5311

Part: KEEL FITTING — CORRODED (ZONE 100) · airframe 10,039 hrs · 31,508 cycles

DAMAGE WAS NOTED TO THE R/H KEEL BEAM CAP (P/N: L533M1010203) IN THE FORM OF 2 EA SPOTS OF CORROSION LOCATED BENEATH THE EDGE OF THE COCKPIT FLOOR. THE CORROSION AT LOCATION 1 MEASURED AT APPROXIMATELY 1.0” X 0.50” AND 0.020” DEEP. CORROSION AT LOCATION 2 MEASURED AT APPROXIMATELY 0.70” X 0.50” AND 0.027” DEEP.

ATA 2210

Part: AUTOPILOT SYS — BINDING · airframe 3,876 hrs

AUTOPILOT FAILED PREFLIGHT TEST, AUTOPILOT ME LED. DURING TROUBLESHOOTING OF AUTOPILOT SYSTEM BY MAINTENANCE THE AIRCRAFT EXPERIENCED UNUSUAL VIBRATIONS/OSCILLATIONS IN THE HOVER CHECK. FOUND FAULTY ELECTRO HYDRAULIC ACTUATOR

ATA 5312

Part: BULKHEAD — CRACKED (FUSELAGE)

A 4 INCH CRACK WAS DISCOVERED ON THE BULKHEAD SKIN ADJACENT TO FRAME 5 (FR5), RT SIDE NEAR THE NR 2 ENGINE FACEC COMPUTER. THE CRACK WAS DISCOVERED WHEN THE PELICAN RACK WAS LOWERED DURING INSPECTION.