On November 1, 2016, about 1130 eastern daylight time, a Bell OH-58C, N139RD, operated by Helicopter Applicators Inc., was substantially damaged following a main rotor blade fracture during the initial climb after takeoff in Cameron, North Carolina. The commercial pilot sustained minor injuries. Visual meteorological conditions prevailed and no flight plan was filed for the local aerial application flight. The helicopter was operated under the provisions of Title 14 Code of Federal Regulations Part 137.According to the pilot, he flew earlier in the day at a different field, spraying an herbicide and made approximately 12 landings on a truck to refill the herbicide spray. He subsequently flew to a different field and sprayed one load of herbicide, landed and waited for the loading crew to arrive at the new field. Once the loading crew arrived and loaded the helicopter with 80 gallons (720 pounds) of herbicide, he took off and climbed to about 50 ft. The helicopter traveled about 200 yards away from the staging area, when he heard a loud bang and the helicopter fell to the ground. According to a witness, shortly after the helicopter took off, the tailboom appeared to have moved to the left and then straight up and into the main rotor blades. The helicopter then fell straight down to the ground and he ran over to help the pilot out of the helicopter. Examination of the wreckage by a Federal Aviation Administration (FAA) inspector revealed that helicopter came to rest on its left side. The damage to the tailboom was consistent with the main rotor blades striking the tailboom about 10 ft from the main fuselage. The outboard portion of one main rotor blade was found about 1,000 ft from where the helicopter came to rest. Further examination of the helicopter by an NTSB investigator, revealed that the "white" main rotor blade, part No. 206-011-250-3, serial No. TLK-9054 had two fractures. One fracture was inboard, near the root end, and one fracture was outboard, about 28 inches from the tip end. The inboard fracture was consistent with overload, and the outboard fracture displayed areas with curving arrest lines that were consistent with fatigue. The "red" main rotor blade, part No. 206-011-250-113, serial No. A-FS9, was generally intact. The transmission separated and the main rotor mast was bent. The right transmission mount remained attached to the transmission and the left transmission mount remained attached to the airframe; consistent with transmission separation prior to ground impact. The fractured outboard portions of the "white" main rotor blade were sent to the NTSB Materials Laboratory, Washington, DC for examination, which revealed fatigue features emanating from multiple origins in the area of the inertia weight attachment hole. The total length of the fatigue region measured at the lower surface of the blade was 1.4 inches from the leading edge of the inertia weight attachment hole to the leading boundary, and 3 inches from the trailing edge of the hole to the trailing boundary. Bell Helicopter Textron, Inc., published Military Alert Bulletin (MAB) USA-OH-58-87-1, revision B, originally dated August 12, 1987, and revised April 12, 2007. The purpose of the revised MAB was to notify military operators of model OH-58A, B, C and 206B-1 model helicopters with part numbers 206-011-250-003/113 main rotor blades to conduct initial visual inspections of the blades before returning them to service and subsequently inspect them at intervals of 8 hours or 32 flights, whichever occurred first. The inspection, to be performed with a 10x power scope was focused on the area of the inertia weight screw heads. Paint was to be removed prior to the first inspection, and a clear-coat finish was to be applied to facilitate subsequent inspections. On April 12, 2007, Bell also issued Operations Safety Notice (OSN) OSN-GEN-07-38, Revision A, to all OH-58 operators referencing the aforementioned MAB and providing a notification of changes incorporated in the revised MAB. Both the MAB and OSN noted that the inspection requirement did not apply to main rotor blades manufactured by Bell Helicopter identified with serial Nos. A-1 and subsequent. The NTSB Materials Laboratory examination also revealed that the black paint on the lower leading edge of the main rotor blade had a tapered edge consistent with erosion wear. No evidence of a clear-coat finish was observed on the surface of the inertia weight attachment hole, as required by the MAB and OSN. According to FAA airworthiness records, the accident helicopter, serial No. 71-20396 was manufactured in 1971. It was originally owned and operated by the U.S. Army, and issued an FAA special airworthiness certificate in the restricted category for the purpose of agriculture and pest control on May 4, 1999. According to the FAA type certificate database, the accident helicopter serial No. and registration No. were listed in the approved serial number list under type certificate data sheet No. R00006DE. The original holder of this type certificate was Garlick Helicopters, Inc., and the type certificate was transferred to Rotorcraft Development Corporation on February 2, 2009. Review of the maintenance records revealed that the helicopter's most recent 100-hour inspection was completed on September 29, 2016. At that time, the helicopter's total airframe time was noted as 12,604.5 hours. The engine total time was noted as 2,690.3 hours since new. The helicopter had been operated about 52 hours since the inspection. The operator indicated that they were unaware of the MAB and immediately initiated a campaign to implement and inspect the rest of their OH-58 helicopter fleet. Garlick Helicopters, Inc. preventive maintenance services inspection program, publication No. GHI-OH58-PMS, contained recurrent inspection requirements for Garlick Model OH-58A, OH-58A+, and OH-58C helicopters. The daily inspection criteria included an inspection of the main rotor blade for nicks, scratches, dents, security, and delamination of the bonded areas. Additionally, the blade finish was to be inspected for bare spots, blistered paint, and evidence of corrosion. A 25-hour inspection required inspection of the main rotor blades' protective coating, and to clean and wax the blades as required. No inspections of the main rotor blade tip area, specifically of the area of the inertia weight, was found in GHI-OH58-PMS. Rotorcraft Development Corporation stated that in a search of documents pertaining to OH-58 helicopters, they did not have the aforementioned MAB and OSN.