Airworthiness directives › 2003-21-07
AD 2003-21-07 Airworthiness Directives; The Cessna Aircraft Company Model 525 Airplanes
Makes named: cessna. Models named: 525. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(c) This AD affects Model 525 airplanes, serial numbers 525-0001, 525-0002, and 525-0004 through 525-0159, that are certificated in any category.
Required actions
(e) To address this problem, you must accomplish the following: Actions Compliance (1) Disengage the PITCH TRIM circuit breaker located on the left circuit breaker panel. Install a tie strap (part number (P/N) MS3367-1-4 or equivalent part number) on the shaft of the PITCH TRIM circuit breaker to prevent the circuit breaker from being engaged Within 5 calendar days or 10 hours time-in-service after October 22, 2003 (the effective date of this AD), whichever occurs first. (2) Disengage the AP SERVOS circuit breaker located in the right circuit breaker panel. Install a tie strap (P/N MS3367-1-4 or equivalent part number) on the shaft of the AP SERVOS circuit breaker to prevent the circuit breaker from being engaged Within 5 calendar days or 10 hours time-in-service after October 22, 2003 (the effective date of this AD), whichever occurs first. (3) The Minimum Crew portion of Section II—Operating Limitations of the Airplane Flight Manual (AFM) provides information on applicable operating limitations with the autopilot inoperable Not Applicable. (4) All affected airplanes were originally equipped with a P/N 6518351-3 or P/N 65138351-5 Trim PC Board Assembly. If a P/N 6518351-8 Trim PC Board Assembly is installed, contact the Wichita Aircraft Certification Office at the address in paragraph (f) of this AD to determine if the installed P/N 6518351-8 Trim PC board assembly is an alternative method of compliance to this AD Not Applicable. (5) Cessna Citation Alert Service Letter ASL525-27-02, dated October 10, 2003, contains information related to this subject Not Applicable.
Unsafe condition
(d) This AD is the result of analysis that reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
Read the original on the Federal Register →
You just looked this one up by hand
TrackAD holds all 12,278 of them and matches them against the aircraft you actually look after — airframe, engine, propeller and appliances in one pass — then works out what falls due and when.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1