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CONDITIONS: In an OH-58D helicopter.

  • STANDARDS: Appropriate common standards plus the following:


    1. Execute the appropriate immediate action steps.

    2. Execute a smooth, controlled descent and touchdown with no rearward drift.

    3. Maintain heading 10 degrees.

    4. Do not allow lateral drift to exceed 3 feet.
    1. DESCRIPTION:


      1. Crew actions.

            1. The IP will confirm suitability of the landing area and comply with ARs and local requirements prior to initiating the maneuver. He will announce “HOVERING AUTO” when he retards the throttle. He will monitor the position of the aircraft and take corrective action if necessary.

            2. Upon detecting engine failure, the P* will focus outside the aircraft and adjust the flight controls as necessary to land.

            3. The P will assist the P* as directed.

      2. Procedures. Upon detecting engine failure, maintain heading with the pedals and correct any lateral or rearward drift with the cyclic. If the maneuver is initiated while the aircraft is moving forward over a smooth or prepared surface, adjust the cyclic to attain a landing attitude while avoiding a tail‑low condition. Make ground contact with some forward speed. When the helicopter is resting firmly on the ground, smoothly lower the collective to the full‑down position while simulta­neously neu­tralizing the pedals and cyclic.

    1. Do not use heading hold during this maneuver.
    1. NIGHT OR NVG CONSIDERATIONS: This is an NVG prohibited training task.

    2. TRAINING AND EVALUATION REQUIREMENTS:


      1. Training. Training will be conducted in the aircraft.

      2. Evaluation. Evaluation will be conducted in the aircraft.
    3. REFERENCES: Appropriate common references.


    1. 1074

      1. RESPOND TO ENGINE FAILURE AT ALTITUDE
    1. CONDITIONS: In an OH-58D helicopter.

    2. STANDARDS: Appropriate common standards plus the following:


      1. Perform the appropriate immediate action steps.

      2. Select a suitable landing area.

      3. Maintain airspeed between minimum rate of descent and maximum glide.
    3. DESCRIPTION:


      1. Crew actions.

            1. The IP will confirm availability of a landing area and comply with ARs and local requirements prior to initiating the maneuver. He will announce "SIMULATED ENGINE FAILURE" when he retards the throttle. He will monitor the position of the aircraft and take action corrective if necessary. He will provide adequate warning if aircraft limits are being reached. Prior to 400 feet AGL with the aircraft in a safe autorotative profile he will begin to advance the throttle to full open. The IP will visually, and by throttle pressure, confirm NP is 100%, announce “THROTTLE OPEN", and command the type of termination.

            2. The P* will perform emergency procedures in TMs 55-1520-248-10/CL. He will take corrective action if aircraft operating limits may be exceeded. He will call out NR, NG, and aircraft in trim. Simulate making a Mayday call to the appropriate agency. Complete or simulate emergency procedures outlined in TM 55‑1520‑248‑CL. He will terminate the maneuver as directed.

            3. If time permits the P will verify the emergency procedures with the checklist.

      2. Procedures. Upon detecting engine failure, adjust the collective to maintain rotor RPM within limits while simulta­neously adjusting the pedals to trim the aircraft. Select a suitable landing area. Use turns and vary the airspeed as neces­sary (between minimum rate of decent and maximum glide airspeed) to maneuver the aircraft for a safe landing at the intend­ed landing area. The final approach should be generally into the wind. Call out NR, NG, and aircraft in trim. Simulate making a Mayday call to the appropriate agency. Complete or simulate emergency procedures outlined in TM 55‑1520‑248‑CL. If time permits, verify the emergency procedures. Plan each forced landing as continuing to the ground. Before reaching 400 feet AGL with the aircraft in a safe autorotative profile, the IP will command one of the termination’s below.

            1. Power recovery. Upon receiving the command "Power recovery" continue autorotative descent. When full operating RPM has been confirmed, apply sufficient collective to establish a normal climb. Complete the recovery prior to reaching 200 feet AGL.

            2. Terminate with power. Upon receiving the command. “ Terminate with power,” continue the autorotative descent. Before reaching 100 feet, confirm normal operating RPM. Adjust the collective as necessary, trim the aircraft with the pedals, and maintain autorotation. At approximately 100 to 150 feet adjust the cyclic to decelerate the aircraft. At approximately 25 feet, apply sufficient collec­tive pitch to decrease the rate of descent to zero at 3 to 5 feet AGL with the aircraft in a landing attitude. The airspeed at this point should be the same as if an actual touchdown were to be effected. Maintain proper trim throughout the maneuver with the pedals, and maintain an altitude of 3 to 5 feet until the aircraft is brought to a stationary hover.

    1. Normal engine RPM must be established before passing through 200 feet AGL.

    2. Do not use heading hold during this maneuver.

    3. FADEC will cause NP to match NR during simulated engine failures. Care must be taken to ensure that NR is not allowed to increase to the point that NP limits are exceeded.
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