Airworthiness directives › 2004-14-20
AD 2004-14-20 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 with the following serial numbers that are certificated in any category: (1) Group 1 (maintains the actions from AD 2003-21-07): 525-0001, 525-0002, and 525-0004 through 525-0159. (2) Group 2: 525-0160 through 525-0359.
Required actions
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) For Group 1 airplanes only: 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, 2003-21-07), whichever occurs first Not Applicable. (2) For Group 1 airplanes only: 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 from being engaged Within 5 calendar days or 10 hours time-in-service after October 22, 2003 (the effective date of AD 2003-21-07), whichever occurs first Not Applicable. (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 Not Applicable. (4) All affected airplanes were originally equipped with a P/N 6518351-3 or P/N 65138351-5 Trim PCB Assembly. If a P/N 6518351-8 Trim PCB 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 PCB assembly is an alternative method of compliance to this AD Not Applicable Not Applicable. (5) Cessna Citation Alert Service Letter ASL525-27-02, dated October 10, 2003, contains information related to this subject Not Applicable Not Applicable. (6) For both Group 1 and Group 2 airplanes: Do the trim PCB assembly change as follows: (i) Modify the 6518351-8 trim PCB assembly to a 6518351-10 trim PCB assembly; or (ii) Replace any 6518351-3 or 6518351-5 trim PCB assembly with a 6518351-10 (EX) trim PCB assembly. Within the next 24 calendar months after August 23, 2004 (the effective date of this AD) or within 300 hours time-in-service (TIS) after August 23, 2004 (the effective date of this AD), whichever occurs first, unless already done Follow the ACCOMPLISHMENT INSTRUCTIONS paragraph of Cessna Citation Service Bulletin No. SB525-27-17, dated December 9, 2003. (7) For both Group 1 and Group 2 airplanes: Remove any tie strap (P/N MS3367-1-4 or equivalent part number) on the AP SERVOS and PITCH TRIM circuit breakers. (Required by AD 2003-21-07.) Before further flight after the modification or replacement of the trim PCB assembly required by paragraph (e)(6)(i) or (e)(6)(ii) of this AD Follow the ACCOMPLISHMENT INSTRUCTIONS paragraph of Cessna Citation Service Bulletin No. SB525-27-17, dated December 9, 2003. (8) For both Group 1 and Group 2 airplanes: Do not install any 6518351-8, 6518351-3, or 6518351-5 trim PCB assembly As of August 23, 2004 (the effective date of this AD) Not Applicable.
Unsafe condition
(d) This AD is the result of Cessna having now developed and made changes in the design of the affected trim printed circuit board (PCB) assembly to allow the use of the assembly and the prevention of the single-point failure, and identification of additional airplanes that have the same unsafe condition. The actions specified in this AD are intended 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.
Affected ADs
(b) This AD supersedes AD 2003-21-07.
Read the original on the Federal Register →
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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