Airworthiness Directive · Amendment 39-11658 · Dornier Model 328-100 Series Airplanes
Dornier Model 328-100 Series Airplanes
Model 328-100 series airplanes having serial numbers (S/N) 3005 through 3098 inclusive, and S/N 3100, 3103, 3104, 3106, 3107, 3109, and 3110, on which Dornier Service Bulletin SB-328-76-268, dated August 11, 1998, or Revision 1, dated December 9, 1998, has not been accomplished; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (g) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires repetitive tests of the flight idle backup system of the propeller control system; repetitive inspections to determine the level of wear of the pins and bushings of the cam followers on the power lever rods of the engine controls; and follow-on corrective actions, if necessary. This amendment also requires eventual replacement of the power lever and condition lever rods of the engine controls with new, improved parts, which constitutes terminating action for the repetitive tests and inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the flight idle backup system. In the event of failure of the primary propeller control system, such failure of the flight idle backup system could lead to uncommanded movement of the pitch of the propeller blade to below flight idle and into reverse thrust during flight, and consequent reduced controllability of the airplane.
To prevent failure of the flight idle backup system, which, in the event of failure of the primary propeller control system, could lead to uncommanded movement of the pitch of the propeller blade to below flight idle and into reverse thrust during flight, and consequent reduced controllability of the airplane, accomplish the following:
(a) Prior to the accumulation of 3,000 total flight hours, or within 3 days after the effective date of this AD, whichever occurs later, perform a test of the flight idle backup system of the propeller control system in accordance with Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998. If any discrepancy is detected, prior to further flight, accomplish the actions required by either paragraph (a)(1) or (a)(2) of this AD. Repeat the test thereafter at intervals not to exceed 1 day until accomplishment of the requirements of paragraph (c), (d), (e), or (f), as applicable.
(1) Repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Luftfahrt-Bundesamt (LBA) (or its delegated agent). Or
(2) Accomplish the inspection required by paragraph (b) of this AD, and the applicable follow-on corrective actions required by paragraph (c), (d), or (e) of the AD; AND, if Type C wear is found during the inspection required by paragraph (b), prior to further flight, adjust or calibrate the power lever microswitches in accordance with Dornier Airplane Maintenance Manual JIC 76-11-05-820-000.
(b) Prior to the accumulation of 3,000 total flight hours, or within 7 days after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to determine the level of wear of the pins and bushings of the cam followers of the power lever rods of the engine controls, in accordance with Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998. Classify the level of wear for each power lever rod as specified in paragraphs (b)(1), (b)(2), and (b)(3) and accomplish the requirements of paragraph (c), (d), or (e) of this AD, as applicable, at the times specified in that paragraph.
(1) Type A wear: The bushing is worn such that the pin is visible in one or more locations.
(2) Type B wear: The bushing is worn, but the pin is not visible.
(3) Type C wear: The bushing is not worn.
(c) For power lever rods on which Type A wear is detected during the inspection required by paragraph (b) of this AD: Within 900 flight hours after accomplishment of that inspection, accomplish the requirements of paragraph (c)(1) or (c)(2) of this AD in accordance with Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998. Accomplishment of paragraph (c)(1) or (c)(2) terminates the tests required by paragraph (a) of this AD for that power lever rod only.
(1) Replace the power lever rod with a new power lever rod.
(2) Replace the pins and bushings with new pins and bushings, and accomplish paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
(i) Thereafter, accomplish follow-on inspections and corrective actions (i.e. inspections for wear or looseness of the replaced pins and bushings), at the times and in accordance with the Accomplishment Instructions of the alert service bulletin; and,
(ii) Within 900 flight hours after replacement of the pins and bushings, replace the power lever rod with a new power lever rod.
(d) For power lever rods on which Type B wear is detected during the inspection required by paragraph (b) of this AD: Thereafter, accomplish follow-on inspections and corrective actions at the times and in accordance with the Accomplishment Instructions of Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998, until the requirements of paragraph (f) of this AD are accomplished.
(e) For power lever rods on which Type C wear is detected during the inspection required by paragraph (b) of this AD: Determination of Type C wear terminates the tests required by paragraph (a) of this AD for that power lever rod only. Thereafter, accomplish follow-on inspections and corrective actions at the times and in accordance with the Accomplishment Instructions of Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998, until the requirements of paragraph (f) of this AD are accomplished.
(f) Within 6 months after the effective date of this AD: Replace the power lever and condition lever rods of the engine controls with new, improved parts in accordance with Dornier Service Bulletin SB-328-76-268, Revision 1, dated December 9, 1998. Accomplishment of the replacement constitutes terminating action for the requirements of this AD.
Note 2: Replacement of the power lever and condition lever rods accomplished prior to the effective date of this AD in accordance with Dornier Service Bulletin SB-328-76-268, dated August 11, 1998, is considered acceptable for compliance with paragraph (f) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
