Airworthiness directives › 2004-05-01
AD 2004-05-01 Airworthiness Directives; Bombardier Inc. Model Otter DHC-3 Airplanes
Applicability*9
(c) This AD affects any Model Otter DHC-3 airplane (all serial numbers) that: (1) Has a turbine engine installed per Supplemental Type Certificate (STC) No. SA3777NM (A.M. Luton installation of Pratt and Whitney PT6A-34/-135 engine); and (2) is certificated in any category.
Required actions
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) Do not operate any airplane that has a turbine engine installed per STC No. SA3777NM and DOES NOT have an elevator servo-tab and redundant control linkage per STC No. SA01059SE Within 3 calendar months after April 20, 2004 (the effective date of AD 2004-05-01) or within 250 hours time-in-service (TIS) after April 20, 2004 (the effective date of AD 2004-05-01), whichever occurs first Not Applicable. (2) You may install at the same time a turbine engine per STC No. SA3777NM and a new elevator servo-tab and redundant control linkage per STC No. SA01059SE Before further flight as of April 20, 2004 (the effective date of AD 2004-05-01) Follow American Aeromotives, Inc. DHC-3 Otter Service Letter No. AAI-DHC3-02.01, Revision No. IR, dated April 9, 2002. (3) You may operate an affected airplane installed with a turbine engine per STC No. SA3777NM if you install a new elevator servo-tab and redundant control linkage per STC No. SA01059SE Within 3 calendar months after April 20, 2004 (the effective date of AD 2004-05-01) or within 250 hours time-in-service (TIS) after April 20, 2004 (the effective date of AD 2004-05-01), whichever occurs first Follow American Aeromotives, Inc. DHC-3 Otter Service Letter No. AAI-DHC3-02.01, Revision No. IR, dated April 9, 2002. (4) Do not install a turbine engine per STC No. SA3777NM, unless you have installed a new elevator servo-tab and redundant control linkage per STC No. SA01059SE As of April 20, 2004 (the effective date of AD 2004-05-01) Not Applicable.
Unsafe condition
(d) This AD is the result of reports of the control rod to the servo trim tab system detaching from the servo trim tab and causing the servo trim tab to flutter on airplanes with a turbine engine installed. The actions specified in this AD are intended to prevent a single failure of the elevator servo trim tab system, which could cause severe elevator flutter. Such elevator flutter could lead to possible loss of control of the airplane.
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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