Airworthiness directives › 2005-05-14
AD 2005-05-14 Airworthiness Directives; Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B Airplanes
Models named: Eagle 150B. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(c) This AD affects Model Eagle 150B airplanes, manufacturer serial numbers (MSN) 016 through 042, that are: (1) Equipped with a co-pilot rudder pedal assembly welded design, part number (P/N) 2720D07-02; and (2) Certificated in any category.
Required actions
(e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Inspect the co-pilot rudder pedal assembly welded design, part number (P/N) 272ODO7-02, for cracks (i) If cracks are found replace the assembly with a new bolted design co-pilot rudder pedal assembly, P/N 2720D07-10 (ii) If no cracks are found, either: Inspect within 30 days after April 22, 2005 (the effective date of this AD). If cracks are found during the inspection, before further flight replace the rudder pedal assembly. If no cracks are found during the inspection, before further flight, modify or replace the rudder pedal assembly To inspect and modify the rudder pedal assembly, follow Eagle Aircraft Optional Service Bulletin SB 1096, dated September 16, 2003. To replace the rudder pedal assembly, follow Eagle Aircraft Optional Service Bulletin SB 1097, dated September 16, 2003. (A) Modify P/N 2720D07-02 by replacing the rudder control bushing with a new P/N 2720D08-39 and installing a rudder control stopper, P/N 2720D08-44; or (B) Replace P/N 2720D07-02 with a new bolted design co-pilot rudder pedal assembly, P/N 2720D07-10 (2) Do not install a co-pilot rudder pedal assembly, P/N 2720D07-02, unless it has been inspected and modified as required in paragraphs (e)(1) and (e)(1)(ii)(A) of this AD As of April 22, 2005 (the effective date of this AD) Not applicable.
Unsafe condition
(d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia. The actions specified in this AD are intended to prevent binding of the co-pilot rudder pedal assembly due to premature wear of the bushing, which could result in loss of co-pilot rudder and brake control. This failure could result in loss of control of the airplane.
Affected ADs
(b) None.
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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