AD 2017-15-09 Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes

Makes named: diamond, technify. Models named: DA 42. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Diamond Aircraft Industries (DAI) GmbH Model DA 42 airplanes, serial numbers 42.004 through 42.427 and 42.AC001 through 42.AC151, certificated in any category, that have: (1) Either a Technify Motors GmbH TAE 125-02-99 or TAE 125-02-114 engine installed; and (2) DAI part numbers (P/N) D60-7806-00-01 and P/N D60-7806-00-02 engine exhaust clamps installed.

Unless already done, do the actions in paragraphs (f)(1) through (6) of this AD. (1) Before or upon accumulating 40 hours time-in-service (TIS) on the affected engine exhaust pipes or within the next 10 hours TIS after August 1, 2017 (the effective date of this AD), whichever occurs later, do the actions in paragraphs (f)(1)(i) and (ii) of this AD. (i) Inspect each engine exhaust clamp for cracks following III.3 Action 3—Inspection of exhaust clamp for cracks of the INSTRUCTIONS section of Diamond Aircraft Industries GmbH (DAI) Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017. (ii) Reinstall any uncracked clamp or replace with a new clamp and incorporate spring washers following III.2 Action 2—installation of additional exhaust clamp in the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017. See figure 1 to paragraph (f)(1)(ii) of this AD for additional information on the sequence of installation actions as identified in DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017. Credit is not given for installation of an engine exhaust clamp installed following DAI Work Instruction WI-MSB 42-120, Revision 1, dated December 14, 2016, (installation of exhaust clamp without spring washers), or DAI Work Instruction MSB-42-120, Revision 2, dated June 7, 2017. ER01AU17.000 (2) Within 25 hours TIS after the installation required by paragraph (f)(1)(ii) of this AD and repetitively thereafter at intervals not to exceed 25 hours TIS, inspect each engine exhaust clamp for cracks following III.3 Action 3—Inspection of exhaust clamp for cracks of the INSTRUCTIONS section DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017. (3) If any crack(s) is found on any engine exhaust clamp during any inspection required by this AD, before further flight, replace or modify the affected engine exhaust clamp(s) following III.2 Action 2—installation of additional exhaust clamp in the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017. (4) If during any replacement or modification required by this AD the exhaust clamp assembly cannot be installed without side force using step 10 of III.2 Action 2—installation of additional exhaust clamp in the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, before further flight contact the FAA at the address specified in paragraph (i) of this AD to obtain and incorporate an FAA-approved repair/modification approved specifically for this AD. The FAA will coordinate with the European Aviation Safety Agency (EASA) and DAI for the development of a repair/modification to address the specific problem. (5) The replacement required by paragraphs (f)(1)(ii) or (f)(3) of this AD does not terminate the repetitive inspections required by paragraph (f)(2) of this AD when DAI part numbers (P/N) D60-7806-00-01 and P/N D60-7806-00-02 engine exhaust clamps are installed. (6) Within 10 days after any inspection where a cracked clamp is found or within 10 days after August 1, 2017 (the effective date of this AD), whichever occurs later, report the results to the FAA at the address specified in paragraph (i)(1) of this AD and to DAI at the address specified in paragraph (j)(3) of this AD. Report all the information included in the Appendix to this AD.

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.

This AD was prompted by cracks in the affected engine exhaust pipes, which could cause failure of the propeller regulating valve because of hot exhaust gases coming from the fractured pipes. We are issuing this AD to prevent an uncommanded engine in-flight shutdown or overheat damage, which could result in a forced landing, consequent damage, and occupant injury.

None.