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Aviation Learning Center Document AC 91-75 - Attitude Indicator
Author: Federal Aviation Administration Date: June 2003
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6. Compliance Requirements
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a. This AC is only applicable to part 23-certificated airplanes of less than 12,500 pounds operated under part 91, subparts A through D that do not require more than one crewmember.

b. This AC provides an Administrator-approved method of compliance with the requirement to have a gyroscopic rate-of-turn indicator specified by section 91.205(d)(3), excluding aircraft covered by section 91.205(d)(3)(i) and (ii).

c. Part 91 airplanes with an FAA-approved minimum equipment list (MEL) must have the MEL modified to reflect changes accomplished under this AC.

d. An FAA-approved attitude indicator with a failure warning flag that monitors power supply is acceptable under this AC. This attitude indicator must have an independent power source from the primary attitude indicator. This provides an equivalent level of safety to existing rate-of-turn gyro arrangements.

used for alignment Replacement Guidelines used for alignment
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used for alignment If your airplane is equipped with...  Then the rate-of-turn indicator may be replaced with: used for alignment
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used for alignment Vacuum-powered primary attitude indicators and electrically-powered rate-of-turn indicators  (a) An electrically-powered attitude indicator, or (b) A vacuum- or pressure-powered attitude indicator connected by independent lines to a second, independent vacuum or pressure pump used for alignment
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used for alignment Pressure-powered primary attitude indicators and electrically-powered rate-of-turn indicators  (a) An electrically-powered attitude indicator, or (b) A vacuum- or pressure-powered attitude indicator connected by independent lines to a second, independent vacuum or pressure pump used for alignment
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used for alignment All-electric gyro systems that have two independent electrical power sources in accordance with AC23-17A, section 23.1331  An electrically-powered attitude indicator used for alignment
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used for alignment Electrically-powered primary attitude indicators and vacuum- or pressure-powered rate-of-turn indicators  A vacuum- or pressure-powered attitude indicator used for alignment
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used for alignment Electrically-powered primary attitude indicators and vacuum- or pressure-powered rate-of-turn indicators and has two independent electrical power sources in accordance with AC 23-17A, section 23.1331  An electrically-powered attitude indicator used for alignment
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e. An attitude indicator installed in accordance with this AC must be located within the pilot's primary field of view.

f. The slip/skid indicator required by section 91.205(d)(4) must be permanently mounted on the panel or on a flight instrument within the pilot's primary field of view.

g. Aircraft with autopilots that receive inputs from a turn coordinator require that the applicant do one of the following:

  • (1) Obtain a new Supplemental Type Certificate for the autopilot system to receive inputs from an electrically powered attitude indicator;

  • (2) Deactivate or remove the autopilot in a manner acceptable to the Administrator; or

  • (3) Relocate the rate-of-turn instrument and maintain the autopilot connection in accordance with data acceptable to the Administrator (generally viewed as a minor alteration).

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