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Composite Technology, Inc.
Worldwide Rotor Blade and Composite Services

Special Products
Apache AH-64
Main Rotor Blade Spar Disbond
  • CTI has developed a modification to return to service Apache main rotor blades, currently scrapped due to spar disbond.

  • All developmental tests and analysis are complete. Fully instrumented test flights have been conducted at Fort Rucker, Alabama and completed March 23, 1998.

  • This repair, at a fraction of the cost of a new blade, was approved by AMCOM engineering on June 1998.

  • Turn time to repair the blade and return it to service is expected to be 45 days from the date of receipt at CTI.

  • CTI has already repaired and returned to service over 200 AH-64 main rotor blades under contracts with the U.S. Government.
Tail Rotor Blade FOD and Erosion Protection
  • CTI has developed and tested a nickel erosion strip which will eliminate the scrapping of blades due to FOD and erosion.

  • All developmental fatigue testing was completed April 27, 1997. This repair, at a fraction of the cost of a new blade, was approved by AMCOM engineering on February 1999.

  • As of November 1999. the three lead time flight test blades have 960+ flight hours each flying on the same; another test blade has 630+ flight hours on another aircraft.

  • The erosion strip can be applied to serviceable blades as protection from erosion and FOD. If the nickel leading edge becomes damaged before the blade service life limit is reached it can be replaced and the blade returned to service.

  • Since 2004, CTI has been under contract with the U.S. Army to install the erosion strip on all AH-64 tail rotor blades in service.
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Engine Exhaust Cowling Heat Damage Repair
  • Current Problem: The inner portion of the panel is in close proximity to the engine exhaust nozzles which reaches temperatures between 350-400°F. These temperatures are reached during dwell times in ground run operations. The high temperature causes the composite skin to be severely damaged. Typical damage consists of burned and delaminated composite layers.

  • Solution: CTI has developed a repair for the damaged skins using a high temperature adhesive system. We then apply a heat abative coating over the heat sensitive portion of the panel.

  • This repair was approved by AMCOM engineering on November 1999. Turn around time will be on average three weeks from date of receipt at CTI.
  • The first engine nacelle panel was repaired using this method for the Florida National Guard in March 1997.

  • The heat ablative coating can withstand temperatures up to 1,000°F.

  • A new replacement panel costs $12K. The CTI repair is about $2,500. Please call Terry Reininger at 972-606-4400 for current price.

  • The first CTI repaired engine nacelle panel has 350+ flight hours on a Florida National Guard AH-64 with no signs of heat damage as of April 1999. We have since repaired over 25 cowlings.
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