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Airworthiness Directive 02-29354

recurring
AD 02-29354 · 2002-11-25 · propeller

Airworthiness Directives; MT-Propeller Entwicklung GMBH Models MTV-9-B-C and MTV-3-B-C Propellers

What this AD requires

This amendment supersedes an existing airworthiness directive (AD), that is applicable to MT-Propeller Entwicklung GMBH Models MTV-9- B-C and MTV-3-B-C propellers. That AD currently requires initial and repetitive inspections of Torx head blade root lag screws that are used on certain serial number (SN) propellers and replacement of all lag screws on the propeller if any screws are found broken or with insufficient torque. In addition, that AD currently requires the replacement of certain part number (P/N) Torx head blade root lag screws with improved, hexagonal head blade root lag screws. This amendment requires the expansion of the applicability from certain SN propellers to all propellers with certain SN blades that may contain the suspect Torx head blade root lag screws. This amendment is prompted by FAA awareness that a propeller hub of an affected propeller could be changed, thereby changing the propeller serial number, creating a propeller that is not listed in the AD and that has affected blades and lag screws. The actions specified by this AD are intended to prevent failure of the blade root lag screw, which could result in propeller blade separation and loss of control of the airplane.

Repetitive inspection. Re-inspect every 100 hours or 12 months. The next-due date/hours depend on this aircraft’s time in service — a records report computes it from the logbooks.

Which aircraft AD 02-29354 applies to

MakesMt-Propeller
Part-conditional — A-549-85, A-550-85, A-983-85.

The AD applicability boilerplate references 'engine' but the compliance text concerns propeller blade root lag screws; applies to MT-Propeller Entwicklung GmbH propellers fitted with Torx-head lag screws P/N A-549-85 (3mm thread pitch) or P/N A-550-85 (4mm thread pitch), per MT-Propeller SB No. 17-A, dated March 5, 1999; affected screws are replaced with hexagonal-head P/N A-983-85.

Whether AD 02-29354 actually applies to your aircraft (by serial and installed parts) and whether it’s already complied with comes from that aircraft’s records.

Supersession

Supersedes AD 99-14-06.

How AD compliance is recorded

A valid compliance record (14 CFR 43.9) states:

Method of compliance — The specific action taken (inspected, replaced, modified) and to what revision.
Date — When the work was done.
Aircraft time — Total time in service / tach at compliance — how recurring next-due is computed.
Signature & certificate — The A&P/IA who returned it to service, with certificate number.
Is AD 02-29354 complied with on your aircraft?

Tailplate reads a tail number’s logbooks and matches every applicable AD — including this one — to its compliance evidence, with recurring next-due dates computed.

Look up a tail number →Read the full directive (Federal Register)

Applicability is derived from the FAA directive corpus and is advisory, not a legal airworthiness determination. Compliance is established only from an aircraft’s actual records.