N206CM

BELL 206L-3 No injuries Part 91 — Omni Flight Helicopters Inc

Operated by OMNI FLIGHT HELICOPTERS INC. (per NTSB report)

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

DURING MAINTENANCE INSPECTION AT IAI, 3 EA SPOTS WITH CORROSION WERE FOUND ON THE CENTER WING UPPER SURFACE SKIN, AT STA 955 LBL 72, LBL 80 AND RBL 91. THE CORROSION WAS REMOVED AND UT INSPECTION WAS ACCOMPLISHED ON THE BLENDED AREAS TO DETERMINE THE REMAINING MATERIAL THICKNESS. AT STA 955 LBL 72 – NOMINAL THICKNESS WAS FOUND 0.317”, MINIMAL REMAINING THICKNESS 0.180”, 43.3% MATERIAL REMOVED. AT STA 955 LBL 80 – NOMINAL THICKNESS WAS FOUND 0.328”, MINIMAL REMAINING THICKNESS 0.241”, 26.6% MMATERIAL REMOVED. AT STA 955 RBL 91 – NOMINAL THICKNESS WAS FOUND 0.340”, MINIMAL REMAINING THICKNESS 0.235”, 31% MATERIAL REMOVED. THE BLENDED AREAS WERE FOUND BEYOND SRM 57-10-01 ALLOWABLE DAMAGE 1.

ATA 5200

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

SEC 48, STA 1854 TO 1863: FOUND EXISTING DOUBLER REPAIR ON RH DOOR EXTERNAL SKIN AROUND LATCH CUTOUT LOWER LONGERON.

ATA 5200

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

: R/H MAIN LANDING GEAR TRUNNION DOOR AT OUTER SKIN, FWD EDGE LOWER CORNER: DURING MAINTENANCE INSPECTION, SHOP FOUND UNDOCUMENTED DOUBLER REPAIR AT THE NOTED AREA.DIMENSION OF DOUBLER REPAIR: 6.0"X7.5".

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

SEC 43, STA 654 TO 654+22, STR 31L TO 32L: DURING MAINTENANCE INSPECTION, SHOP HAS DISCOVERED A BUCKLE ON FUSELAGE SKIN AT THE NOTED AREA, AND PERFORMED A CUT OUT BY 1.2"X1.5".

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #2 CF6-80C2B6F STRUT, AFT FAIRING PANEL ASSY, BETWEEN NAC STA 304.54 AND NAC STA 308.00: SHOP FOUND AN EXISTING REPAIR ON THE OUTBD SIDE OF STRUT #2 IN THE OUTER SKIN PANEL LOCATED BELOW ACCESS DOOR BT NAC STA 304.54 TO 308.00. SIZE OF THE REPAIR: 3.5"X1.2". P/N 314U2100-72 S/N 1915A.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #1 OUTBD CORE COWL SKIN: DURING MAINTENANCE INSPECTION AT IAI FOUND TWO EXISTING UNDOCUMENTED DOUBLER REPAIRS ON OUTBD CORE COWL. M0149 – LOCATED NAC STA 268 TO 283 AT 6 O'CLOCK SIZE 15"X4.8". M0151 – LOCATED NAC STA 303.75 BT 11 TO 12 O'CLOCK SIZE 1.6"X7.2".

ATA 5330

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

REPAIR – EXTERNAL FUSELAGE SKIN, STA 1809 TO 1824, 4.0" ABOVE STR 22R: DURING MAINTENANCE INSPECTION AT IAI, SHOP FOUND AN UNDOCUMENTED DOUBLER REPAIR AT THE NOTED AREA. SIZE: 14.5"X15.5".

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

STA 1333, STR 20R, DOOR SILL: FOUND DEEP REDUCTION OF MATERIAL ON THE FAIL SAFE STRAP OF THE UPPER SILL AT STA 1333, STR 20R. HFEC INSPECTION WAS PERFORMED AND NO CRACKS OR CORROSION WERE FOUND.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

STRUT FAIRING SKIN, INBD SIDE: EXISTING UNDOCUMENTED 2.8"X1.4" DOUBLER REPAIR ON THE INBD SIDE OF STRUT FAIRING SKIN BELOW DOOR PANEL BT STA 304.54 – 307.34.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #2, BT NAC STA 268.7 TO 303.7 AND BT 9 TO 10 O'CLOCK: DURING MAINTENANCE INSPECTION SEVERAL SCRATCHES DAMAGE WERE FOUND ON CORE COWL SKIN. FASTENERS REMOVED, AND INSTALLED AFTER THE AREA WAS BLENDED PER SRM 51-40-02. SMOOTHING WAS PERFORMED IN THE AREA OF THE SCRATCHES PER SRM 51-10-02. ALSO PERFORMED HFEC INSPECTION AND FOUND NO CRCKS OR CORROSION. PERFORMED UT THICK INSP AND FOUND: ORIGINAL 0.063" MIN 0.061"; ORIGINAL 0.042" MIN 0.040".

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #2 – LH CORE COWL, NAC STA 264.50, UPPER CORNER EDGE: DURING MAINTENANCE INSPECTION, SHOP FOUND A 0.9" LONG CRACK ON AN INCOMING REPAIR AT THE NOTED AREA. IN ADDITION, THE EXISTING REPAIR CONFIGURATION IS MISSING SEAL-FLEX P/N S700S1310-1, FILLER P/N 224-2301-165 AND SEAL RETAINER P/N 224-2301-155.

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

SECTION 41 – FUSELAGE SKIN AT STA 159.5 AND ABOVE STR30R: DURING MAINTENANCE INSPECTION, EXISTING BLEND OUT AND LIGHTING STRKE WERE FOUND. SKIN P/N 141T3211, IS MADE FROM 0.08” CLAD 2024-T3 (CHEM-MILLED 0.045”0. THE BLEND OUT IS BEYOND LIMITS PER SRM 53-00-01, ALLOWABLE DAMAGE 2, FIG 101.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE # 2 OUTBD CORE COWL SKIN: DURING MAINTENANCE INSPECTION AT IAI FOUND UNDOCUMENTED DOUBLER REPAIR ENG # 2 OUTBD CORE COWL AROUND FWD LATCH CUTOUT BT NAS STA 264.37 TO 270.57 AT 6 O’CLOCK.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENG #2 FAN COWL OUTER SKIN: 8 (EIGHT) DENTS WERE FOUND WITH CLOSE GAPS IN THE OUTER SKIN OF THE ENG #2 FAN COWL, ON THE OUTBD SIDE BT 4 O'CLOCK TO 5 O'CLOCK.

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

FUSELAGE SKIN, STA 325 BT STR21L-22L: TWO EXISTING BLENDOUTS FOUND ON EXTERNAL FUSELAGE SKIN. NOMINAL THICKNESS: 0.130". (-0.002" THICKNESS BLENDED). ONLY ONE BLENDOUT IS DOCUMENTED.

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #2 CF6-80C2B6F, EXHAUST, NAC STA 332.34 AND NAC STA 360.73: SHOP FOUND A DENT WITH SHARP CREASE ON THE EXTERNAL EXHAUST SKIN LOCATED ON ENGINE 2 NAC STA 332.34, BT 6 TO 5 O’CLOCK. SIZE: L=0.50”, Y=0.020, A=0.47 A/Y=23. IN ADDITION, SHOP FOUND ANOTHER DENT THAT IS LESS THAN 2.0 INCHES FROM PANEL EDGE ON THE EXTERNAL EXHAUST SKIN LOCATED ON ENGINE 2, NAC STA 360.73, BT 2 TO 3 O’CLOCK AND 0.85” FROM AFT RING CUTOUT. SIZE: L=2.51”, A=1.07, Y=0.050, A/Y=21. P/N 314U2100-72; S/N 1915A.

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

DURING MAINTENANCE INSPECTION AT IAI, A DENT WAS FOUND ON THE LOWER SKIN PANEL OF LAP SPLICE AT STR 36L, STA 1433 (BELOW BULK CARGO DOOR). DENT DIMENSIONS: L=2.24", A=1.95, Y=0.050, A/Y=39.

ATA 5300

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

DURING MAINTENANCE INSPECTION, AIRCRAFT MAINTENANCE CORRODED AREA WAS FOUND AT DRAIN MUST BETWEEN STA 1395 AND STA 1417 AND STR 35R AND STR 36R. A UT INSPECTION WAS ACCOMPLISHED ON BLENDED AREA TO DETERMINE THE REMAINING MATERIAL THICKNESS AS CONTAINED IN REF /A/. PER REF /D/, AND THE BLENDED AREA WAS FOUND TO SLIGHTLY EXCEED ALLOWABLE PARENT MATERIAL LOSS LIMITS AND EXCEED ALLOWABLE LIMITS. REWORKED AREA, NOMINAL THICKNESS 0.135" (0.010"+/-0.007"), REMAINING MATERIAL 0.118", 12.5% MATERIAL REMOVED. REWORKED AREA, NOMINAL THICKNESS 0.105" (0.010"+/-0.005"), REMAINING MATERIAL 0.103", 2.5% MATERIAL REMOVED. REWORKED AREA, NOMINAL THICKNESS 0.056" (0.010" /-0.003"), REMAINING MATERIAL 0.051", 9% MATERIAL REMOVED

ATA 5400

Part: NONE — NONE · airframe 116,246 hrs · 20,837 cycles

ENGINE #2 INBD CORE COWL SKIN: DURING MAINTENANCE INSPECTION AT IAI FOUND EXISTING HAT FRAME REPAIR NOT ACCORDING TO SRM ON INBD CORE COWL ENG #2 NAC STA 303.75 BT 11 TO 12 O’CLOCK.EXTERNAL DOUBLER SIZE: 1.7”X7.1”. ENGEL PATCH SIZE: 6”X4” APP. P/N: 224-2301-513, S/N: 0233.