83 FR 23780 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 100 (May 23, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 100 (May 23, 2018)
| Page Range | 23780-23788 | |
| FR Document | 2018-10580 |
[Federal Register Volume 83, Number 100 (Wednesday, May 23, 2018)] [Rules and Regulations] [Pages 23780-23788] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-10580] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0188; Product Identifier 2018-CE-002-AD; Amendment 39-19285; AD 2018-10-10] RIN 2120-AA64 Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2017-01-12, AD 2017-11-08, and AD 2017-15-09 for certain Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as uncommanded engine shutdown during flight due to failure of the propeller-regulating valve caused by hot exhaust gases coming from fractured engine exhaust pipes. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective June 12, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 12, 2018. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 31, 2017 (82 FR 24843, May 31, 2017) and August 1, 2017 (82 FR 35630, August 1, 2017). We must receive comments on this AD by July 9, 2018. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. [[Page 23781]] Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Diamond Aircraft Industries GmbH, N.A. Otto-Stra[beta]e 5, A-2700 Wiener Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780; email: office@diamond-air.at; internet: http://www.diamondaircraft.com. You may review copies of the referenced service information at the FAA, Small Airplane Standards Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. It is also available on the internet at http://www.regulations.gov by searching for locating Docket No. FAA-2018-0188. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0188; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: mike.kiesov@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued AD 2017-01-12, Amendment 39-18779 (82 FR 5359, January 18, 2017) (``AD 2017-01-12''); AD 2017-11-08, Amendment 39-18907 (82 FR 24843, May 31, 2017) (``AD 2017-11-08''), and AD 2017-15-09, Amendment 39-18969 (82 FR 35630, August 1, 2017) (``AD 2017-15-09''). Those ADs required actions intended to address an unsafe condition on certain Diamond Aircraft Industries GmbH Model DA 42 airplanes and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. Since we issued AD 2017-01-12, AD 2017-11-08, and AD 2017-15-09, the European Aviation Safety Agency (EASA) has issued a new AD. The EASA, which is the Technical Agent for the Member States of the European Community, has issued AD No. 2017-0254, dated December 21, 2017 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Two cases were reported of uncommanded engine in-flight shutdown (IFSD) on DA 42 aeroplanes. Subsequent investigation identified that these occurrences were due to failure of the propeller regulating valve, caused by hot exhaust gases coming from fractured engine exhaust pipes. The initiating cracks on the exhaust pipes were not detected during previous inspections, since those exhaust pipes are equipped with non-removable heat shields that do not allow inspection for certain sections of the exhaust pipe. This condition, if not corrected, could lead to further cases of IFSD or overheat damage, possibly resulting in a forced landing, with consequent damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Diamond Aircraft Industries (DAI) developed an exhaust pipe without a directly attached integral heat shield that allows visual inspection over the entire exhaust pipe length. DAI issued Mandatory Service Bulletin (MSB) 42-120 and relevant Working Instruction (WI) WI-MSB 42-120, providing instructions to install the modified exhaust pipes. As an interim measure, an additional bracket was designed to hold the exhaust pipe in place in case of a pipe fracture. EASA issued AD 2016-0156 (later revised), requiring replacement of the exhaust pipes with pipes having the new design, or installation of the additional brackets. After EASA AD 2016-0156R1 was issued, cracks were found during inspection on modified exhaust pipes. Further investigation determined that, with the modified exhaust pipe design, vibration leads to cracking. Consequently, DAI published MSB 42-129, providing instructions for inspection of modified exhaust pipes, and EASA issued AD 2017-0090, retaining the requirements of EASA AD 2016- 0156R1, which was superseded, and additionally requiring repetitive inspections of modified exhaust pipes and, depending on findings, repair or replacement. After EASA AD 2017-0090 was issued, cracks were found on additional brackets, as previously installed per DAI WI-MSB 42-120. Prompted by these findings, DAI revised MSB 42-120 and the relevant part of WI-MSB 42-120 (now at Revision 4), providing improved instructions for the installation of brackets, and additional instructions to inspect those brackets. Consequently, EASA issued AD 2017-0120, retaining the requirements of EASA AD 2017-0090, which was superseded, and additionally requiring those actions for the additional brackets. That [EASA] AD also required reinstallation of the additional brackets in accordance with improved instructions. Since EASA AD 2017-0120 was issued, it has been determined that installation of additional exhaust pipe brackets, combined with additional inspections, is the most adequate solution to address the original unsafe condition, while it was also established that the modified exhaust pipes without directly attached heat shield are not adequate as replacement parts. Durability analysis of the design is still under investigation and further improvements in the exhaust design are expected. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2017-0120, which is superseded, removing the option to install a modified exhaust pipe without direct heat shield, and adding inspection requirements for aeroplanes modified in accordance with Section III.2 of DAI WI-MSB 42-120 Revision 3 or later (installation of additional brackets), and for aeroplanes on which an exhaust pipe with directly attached heat shield was re-installed in accordance with DAI OSB 42-131. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0188. Relative Service Information Under 1 CFR Part 51 Diamond Aircraft Industries GmbH (DAI) has issued Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, Work Instruction WI-MSB 42-120, Revision 4, dated December 20, 2018, Mandatory Service Bulletin MSB-42-129, dated May 17, 2017, and Work Instruction WI-OSB 42-131, dated December 20, 2017. DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, and Work Instruction WI-MSB 42-120, Revision 4, dated December 20, 2018, have identical procedures for installing additional engine exhaust pipe clamps with spring washers on original engine exhaust pipes. DAI Work Instruction WI-MSB 42-120, Revision 4, dated December 20, 2018, also includes procedures for inspecting the original engine exhaust pipe for cracks. DAI Mandatory Service Bulletin MSB-42-129, dated May 17, 2017, describes procedures for inspecting the modified engine exhaust pipe for cracks. DAI Work Instruction WI-OSB 42-131, dated December 20, 2017, describes procedures for replacing either the original or the modified engine exhaust pipe if cracks are found. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. [[Page 23782]] FAA's Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA's Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because affected engine exhaust pipes could crack and cause hot gases to leak from fractured exhaust pipes and lead to an uncommanded engine in- flight shutdown. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reason stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0188; Directorate Identifier 2018-CE-002-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD will affect 130 products of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspect engine exhaust pipe...... 2 work-hours x $85 = N/A................ $170 $22,100 $170. Install additional engine exhaust 4 work-hours x $85 per $100 (for both 440 57,300 pipe clamps with spring washers. hour = $340 (for both clamps). clamps). Inspect engine exhaust pipe 2 work-hours x $85 per N/A................ 170 22,100 clamps. hour = $170. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that will be required based on the results of the inspections. We have no way of determining the number of airplanes that may need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replace cracked engine exhaust pipe... 4 work-hours x $85 per hour = $1,900.................. .............. $340. Replace cracked engine exhaust pipe 4 work-hours x $85 per hour = $100 (for both clamps).. $440 clamps. $340 (for both clamps). ---------------------------------------------------------------------------------------------------------------- We estimate that 20 of the affected airplanes have the ``modified exhaust pipes,'' Diamond Aircraft Industries P/N D60-9078-06-01_01 or Technify P/N 52-7810-H0014 01, installed that may be subject to replacement by this AD and 110 of the affected airplanes are subject to the initial installation of additional engine exhaust pipe clamps and spring washers, inspections, and the conditional replacement requirement of this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and [[Page 23783]] responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Amendment 39-18779 (82 FR 5359, January 18, 2017), Amendment 39-18907 (82 FR 24843, May 31, 2017), and Amendment 39-18969 (82 FR 35630, August 1, 2017) and adding the following new AD: 2018-10-10 Diamond Aircraft Industries GmbH: Amendment 39-19285; Docket No. FAA-2018-0188; Directorate Identifier 2018-CE-002-AD. (a) Effective Date This airworthiness directive (AD) becomes effective June 12, 2018. (b) Affected ADs This AD replaces 2017-01-12, Amendment 39-18779 (82 FR 5359, January 18, 2017) (``AD 2017-01-12''); AD 2017-11-08, Amendment 39- 18907 (82 FR 24843, May 31, 2017) (``AD 2017-11-08''), and AD 2017- 15-09, Amendment 39-18969 (82 FR 35630, August 1, 2017) (``AD 2017- 15-09''). (c) Applicability This AD applies to Diamond Aircraft Industries GmbH Model DA 42 airplanes, serial numbers 42.004 through 42.427 and 42.AC001 through 42.AC151, certificated in any category, that have either a TAE 125- 02-99 or TAE 125-02-114 engine installed, and: (1) are equipped with an original engine exhaust pipe, Diamond Aircraft Industries (DAI) part number (P/N) D60-9078-06-01 or Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, 52-7810-H0001 04; or (2) are equipped with a modified engine exhaust pipe DAI P/N D60-9078-06-01_01 or Technify 52-7810-H0014 01. (d) Subject Air Transport Association of America (ATA) Code 78: Engine Exhaust. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. It has been determined that installation of additional exhaust pipe brackets, combined with additional inspections, is the most adequate solution to address the original unsafe condition, while it was also established that the modified exhaust pipes without directly attached heat shield are not adequate as replacement parts. Durability analysis of the design is still under investigation and further improvements in the exhaust design are expected. For these reasons, this AD removes the option to install a modified exhaust pipe without direct heat shield, adds inspection requirements for airplanes modified in accordance with Section III.2 of Diamond Aircraft Industries (DAI) WI-MSB 42-120 Revision 3, dated July 6, 2017 (installation of additional brackets), and for airplanes on which an exhaust pipe with directly attached heat shield was re-installed in accordance with DAI Work Instruction WI- OSB 42-131, dated December 20, 2017. The MCAI describes the unsafe condition as uncommanded engine shutdown during flight due to failure of the propeller regulating valve caused by hot exhaust gases coming from fractured engine exhaust pipes. We are issuing this AD to prevent failure of the propeller regulating valve, which could result in forced landing, consequent damage and occupant injury. (f) Compliance Unless already done, do the following actions. (1) An airplane is only required to have the actions of either (g) or (h) of this AD accomplished depending on the configuration. (2) For the purpose of this AD, if the flight hours accumulated since first installation of an affected exhaust pipe or additional exhaust pipe clamp is not known, use the total hours time-in-service (TIS) accumulated on the airplane. (g) Actions for Airplanes With Installed Original Engine Exhaust Pipes as of June 12, 2018 (the Effective Date of This AD) See Appendix 1 to AD 2018-10-10 for a chart of required actions. An original engine exhaust pipe is defined in paragraph (c), Applicability, of this AD. (1) At the applicable compliance time in paragraphs (g)(1)(i) and (ii) of this AD, and repetitively thereafter at intervals not to exceed 500 hours time-in-service (TIS), inspect the installed engine exhaust pipe. Do this inspection following section III.4--Inspection of exhaust pipe in the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 4, dated December 20, 2017. (i) If the engine exhaust pipe has 1,300 hours TIS or less since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Before or upon accumulating 1,500 hours TIS since the engine exhaust pipe was first installed on an airplane, and repetitively thereafter at intervals not to exceed 500 hours TIS. (ii) If the engine exhaust pipe has more than 1,300 hours TIS since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Within the next 200 hours TIS after June 12, 2018 (the effective date of this AD), and repetitively thereafter at intervals not to exceed 500 hours time-in-service (TIS). (2) During any inspection required in paragraph (g)(1) of this AD, if the engine exhaust pipe does not pass the inspection criteria, before further flight replace the engine exhaust pipe following section III.1--Re-installation of Exhaust Pipes with Directly Attached Heat Shield in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017 (which includes installing additional engine exhaust pipe clamps, an exhaust sheet, and incorporates spring washers). After replacement continue with the 500-hour TIS repetitive inspections. (i) If only the engine exhaust pipe heat shield is loose, a one- time single weld is allowed following section III.3--Repair of Heat Shields of DAI P/N D60-9078-06-01/Technify P/Ns 52-7810-H0001 03 and 52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017. After a repair of the heat shield, if a single weld point is subsequently found cracked, the heat shield is considered to be loose and the exhaust pipe must be replaced. After replacement or repair, continue with the 500-hour TIS repetitive inspections. (ii) Engine exhaust pipes re-qualified following section III.2-- Re-Qualification of Exhaust Pipes DAI P/N D60-9078-06-01/Technify P/ Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017, are considered to have accumulated 1,500 hours TIS. (3) Before further flight after the initial inspection required in paragraph (g)(1) of this AD and if no cracks were found or a repair to the exhaust pipe heat shield was done as required in paragraph (g)(2)(i) of this AD, then install additional engine exhaust pipe clamps, DAI P/Ns D60-7806-00-01 and D60-7806-00-02, and exhaust sheet, P/N D60-7806-00-03, and incorporate spring washers. Do the installations 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, or Revision 4, dated December 20, 2017. See figure 1 to paragraph (g)(3) 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 and Revision 4, dated December 20, 2017. [[Page 23784]] [GRAPHIC] [TIFF OMITTED] TR23MY18.000 (4) During any engine exhaust pipe clamp and exhaust sheet with spring washer installation/replacement required in paragraphs (g)(2), (3), (6), and (7) of this AD, if 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, or Revision 4, dated December 20, 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) At the applicable compliance time in paragraphs (g)(5)(i) and (ii) of this AD and repetitively thereafter at intervals not to exceed 25 hours TIS, remove and inspect each engine exhaust clamp for cracks. Do this inspection following III.3 Action 3--Inspection of exhaust clamp for cracks of the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, or Revision 4, dated December 20, 2017. (i) If the engine exhaust pipe clamp has less than 40 hours TIS since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Before or upon accumulating 50 hours TIS since the engine exhaust pipe clamp was first installed on an airplane. (ii) If the engine exhaust pipe clamp has 40 hours TIS or more since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Within the next 10 hours TIS after June 12, 2018 (the effective date of this AD). (6) Before further flight after any inspection required in paragraph (g)(5) of this AD and no crack is found, reinstall the engine exhaust pipe 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, or Revision 4, dated December 20, 2017. See figure 1 to paragraph (g)(3) 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, and or Revision 4, dated December 20, 2017. Continue with the 25-hour TIS repetitive inspection as long as no cracks are found. (7) Before further flight after any inspection required in paragraph (g)(5) of this AD and a cracked engine exhaust pipe clamp is found, replace the cracked engine exhaust pipe clamp with a new engine exhaust pipe clamp and incorporate spring washers following the service instructions specified in paragraph (g)(6) of this AD. All newly installed engine exhaust pipe clamps are subject to an initial 50-hour TIS and repetitive 25-hour TIS inspections for cracks following the service instructions specified in paragraph (g)(5) of this AD. (h) Actions for Airplanes With Installed Modified Engine Exhaust Pipes as of June 12, 2018 (the Effective Date of This AD) See Appendix 2 to AD 2018-10-10 for a chart of required actions. A modified engine exhaust pipe is defined in paragraph (c), Applicability, of this AD. (1) At the applicable compliance time in paragraphs (h)(1)(i) and (ii) of this AD and repetitively thereafter at intervals not to [[Page 23785]] exceed 50 hours TIS, inspect each engine exhaust pipe for cracks. Do this inspection following I.9 Accomplishment/Instructions in DAI Mandatory Service Bulletin MSB-42-129, dated May 17, 2017. (i) If the engine exhaust pipe has less than 40 hours TIS since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Before or upon accumulating 50 hours TIS since the affected engine exhaust pipe was first installed on an airplane, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. (ii) If the engine exhaust pipe has 40 hours TIS or more since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Within the next 10 hours TIS after June 12, 2018 (the effective date of this AD), repetitively thereafter inspect at intervals not to exceed 50 hours TIS. (2) If a crack is found during any inspection required by paragraph (h)(1) of this AD, before further flight replace the engine exhaust pipe with an engine exhaust pipe, DAI P/N D60-9078- 06-01 or Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52- 7810-H0001 04. Do the replacement following section III.1--Re- installation of Exhaust Pipes with Directly Attached Heat Shield in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017, which includes installing additional engine exhaust pipe clamps, an exhaust sheet, and incorporates spring washers. (3) After installing an engine exhaust pipe, DAI P/N D60-9078- 06-01 or Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52- 7810-H0001 04 (which includes installing additional engine exhaust pipe clamps, an exhaust sheet, and incorporates spring washers), repetitively thereafter inspect at intervals not to exceed 500 hours TIS. Do this inspection following section III.4--Inspection of exhaust pipe in the INSTRUCTIONS section of DAI Work Instruction WI- MSB 42-120, Revision 4, dated December 20, 2017. (4) During any inspection required in paragraph (h)(3) of this AD, if the engine exhaust pipe does not pass the inspection criteria, before further flight replace the engine exhaust pipe following section III.1--Re-installation of Exhaust Pipes with Directly Attached Heat Shield in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017 (which includes installing additional engine exhaust pipe clamps, an exhaust sheet, and incorporates spring washers). After replacement, continue with the 500-hour TIS repetitive inspections. (i) If only the engine exhaust pipe heat shield is loose, a one- time single weld is allowed following section III.3--Repair of Heat Shields of DAI P/N D60-9078-06-01/Technify P/Ns 52-7810-H0001 03 and 52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017. After a repair of the heat shield, if a single weld point is subsequently found cracked, the heat shield is considered to be loose and the exhaust pipe must be replaced. After replacement or repair, continue with the 500-hour TIS repetitive inspections. (ii) Engine exhaust pipes re-qualified following section III.2-- Re-Qualification of Exhaust Pipes DAI P/N D60-9078-06-01/Technify P/ Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated December 20, 2017, are considered to have accumulated 1,500 hours TIS. (5) During any engine exhaust pipe clamp, exhaust sheet with spring washer installation/replacement required in paragraphs (h)(2), (4), (7), and (8) of this AD, if 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, or Revision 4, dated December 20, 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. (6) At the applicable compliance time in paragraphs (h)(6)(i) and (ii) of this AD and repetitively thereafter at intervals not to exceed 25 hours TIS, remove and inspect each engine exhaust clamp for cracks. Do this inspection following III.3 Action 3--Inspection of exhaust clamp for cracks of the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, or Revision 4, dated December 20, 2017. (i) If the engine exhaust pipe clamp has less than 40 hours TIS since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Before or upon accumulating 50 hours TIS since the engine exhaust pipe clamp was first installed on an airplane. (ii) If the engine exhaust pipe clamp has 40 hours TIS or more since first installed on an airplane as of June 12, 2018 (the effective date of this AD): Within the next 10 hours TIS after June 12, 2018 (the effective date of this AD). (7) Before further flight after any inspection required in paragraph (h)(6) of this AD and no crack is found, reinstall the engine exhaust pipe 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, or Revision 4, dated December 20, 2017. See figure 2 to paragraph (g)(7) 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, and or Revision 4, dated December 20, 2017. Continue with the 25-hour TIS repetitive inspection as long as no cracks are found. [[Page 23786]] [GRAPHIC] [TIFF OMITTED] TR23MY18.001 (8) Before further flight after any inspection required in paragraph (h)(6) of this AD and a cracked engine exhaust pipe clamp is found, replace the cracked engine exhaust pipe clamp with a new engine exhaust pipe clamp and incorporate spring washers following the service instructions specified in paragraph (h)(7) of this AD. All newly installed engine exhaust pipe clamps are subject to an initial 50-hour TIS and repetitive 25-hour TIS inspections for cracks following the service instructions specified in paragraph (h)() of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: mike.kiesov@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (j) Related Information Refer to MCAI EASA AD No. 2017-0254, dated December 21, 2017, for related information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0188. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 12, 2018. (i) Diamond Aircraft Industries GmbH Work Instruction WI-MSB 42- 120, Revision 4, dated December 20, 2017. (ii) Diamond Aircraft Industries GmbH Work Instruction WI-OSB 42-131, dated December 20, 2017. (4) The following service information was approved for IBR on May 31, 2017 (82 FR 24843, May 31, 2017). [[Page 23787]] (i) Diamond Aircraft Industries GmbH Mandatory Service Bulletin MSB-42-129, dated May 17, 2017. (ii) Reserved. (5) The following service information was approved for IBR on August 1, 2017 (82 FR 35630, August 1, 2017). (i) Diamond Aircraft Industries GmbH Work Instruction WI-MSB 42- 120, Revision 3, dated July 6, 2017. (ii) Reserved. (6) For Diamond Aircraft Industries GmbH service information identified in this AD, contact Diamond Aircraft Industries GmbH, N.A. Otto-Strasse 5, A-2700 Wiener Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780; email: office@diamond-air.at; internet: http://www.diamondaircraft.com. (7) You may view this service information at FAA, Small Airplane Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. It is also available on the internet at http://www.regulations.gov by searching for locating Docket No. FAA-2018-0188. (8) You may view the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. BILLING CODE 4910-13-P [GRAPHIC] [TIFF OMITTED] TR23MY18.002 [[Page 23788]] [GRAPHIC] [TIFF OMITTED] TR23MY18.003 Issued in Kansas City, Missouri, on May 11, 2018. Melvin J. Johnson, Aircraft Certification Service, Deputy Director, Policy and Innovation Division, AIR-601. [FR Doc. 2018-10580 Filed 5-22-18; 8:45 am] BILLING CODE 4910-13-C
![23780 Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
(a) Applicability telephone (817) 222–5110; email 9-ASW- www.archives.gov/federal-register/cfr/ibr-
This AD applies to Model AS332L2 and FTW-AMOC-Requests@faa.gov. locations.html.
Model EC225LP helicopters, certificated in (2) For operations conducted under a 14 Issued in Fort Worth, Texas, on May 16,
any category, with an extended aluminum CFR part 119 operating certificate or under 2018.
splice installed on frame 5295, except 14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or Scott A. Horn,
helicopters with steel splice kit part number
332A08–2649–3072 installed. lacking a principal inspector, the manager of Deputy Director for Regulatory Operations,
the local flight standards district office or Compliance & Airworthiness Division,
Note 1 to paragraph (a) of this AD: Aircraft Certification Service.
Helicopters with Modification (MOD) certificate holding district office, before
0726517 have an extended aluminum splice operating any aircraft complying with this [FR Doc. 2018–10921 Filed 5–22–18; 8:45 am]
installed. AD through an AMOC. BILLING CODE 4910–13–P
(h) Additional Information
(b) Unsafe Condition
(1) Airbus Helicopters Service Bulletin
This AD defines the unsafe condition as a DEPARTMENT OF TRANSPORTATION
(SB) No. 05–019, Revision 4, dated
crack on helicopter frame 5295. This
September 22, 2014, and Eurocopter
condition could result in structural failure of Federal Aviation Administration
Helicopters (now Airbus Helicopters) SB No.
the frame and subsequent loss of control of
53–003, Revision 4, and SB No. 53.01.52,
the helicopter. 14 CFR Part 39
Revision 5, both dated July 23, 2010, which
(c) Effective Date are not incorporated by reference, contain [Docket No. FAA–2018–0188; Product
This AD becomes effective June 27, 2018. additional information about the subject of Identifier 2018–CE–002–AD; Amendment
this AD. For service information identified in 39–19285; AD 2018–10–10]
(d) Compliance this AD, contact Airbus Helicopters, Inc.,
You are responsible for performing each 2701 N. Forum Drive, Grand Prairie, TX RIN 2120–AA64
action required by this AD within the 75052; telephone (972) 641–0000 or (800)
specified compliance time unless it has 232–0323; fax (972) 641–3775; or at http:// Airworthiness Directives; Diamond
already been accomplished prior to that time. www.airbushelicopters.com/techpub. You Aircraft Industries GmbH Airplanes
may view the referenced service information
(e) Required Actions at the FAA, Office of the Regional Counsel, AGENCY: Federal Aviation
(1) Before a splice reaches 1,700 hours Southwest Region, 10101 Hillwood Pkwy., Administration (FAA), DOT.
time-in-service (TIS), within 50 hours TIS, or Room 6N–321, Fort Worth, TX 76177. ACTION: Final rule; request for comments
before the helicopter reaches 11,950 hours (2) The subject of this AD is addressed in
TIS, whichever occurs later, do the following: European Aviation Safety Agency (EASA) AD SUMMARY: We are superseding
(i) Install the rail support cut-out and No. 2014–0098–E, dated April 25, 2014. You Airworthiness Directive (AD) 2017–01–
identify the right-hand and left-hand junction may view the EASA AD on the internet at 12, AD 2017–11–08, and AD 2017–15–
profile in accordance with the http://www.regulations.gov in Docket No.
09 for certain Diamond Aircraft
Accomplishment Instructions, paragraph FAA–2015–3883.
3.B.2, of Airbus Helicopters Alert Service Industries GmbH Model DA 42
(i) Subject airplanes. This AD results from
Bulletin (ASB) No. EC225–05A038, Revision
0, dated April 15, 2014 (ASB EC225– Joint Aircraft Service Component (JASC) mandatory continuing airworthiness
05A038), or ASB No. AS332–05.00.97, Code: 5310, Fuselage Main, Structure. information (MCAI) issued by the
Revision 0, dated April 15, 2014 (ASB (j) Material Incorporated by Reference aviation authority of another country to
AS332–05.00.97), whichever is applicable to identify and address an unsafe
your helicopter. (1) The Director of the Federal Register
condition on an aviation product. The
(ii) Inspect each splice for a crack in the approved the incorporation by reference of
the service information listed in this MCAI describes the unsafe condition as
area depicted as Area Y in Figure 3 of ASB
paragraph under 5 U.S.C. 552(a) and 1 CFR uncommanded engine shutdown during
EC225–05A038 or ASB AS332–05.00.97,
whichever is applicable to your helicopter. If part 51. flight due to failure of the propeller-
a crack exists, repair or replace the splice (2) You must use this service information regulating valve caused by hot exhaust
before further flight. as applicable to do the actions required by gases coming from fractured engine
(2) Thereafter at intervals not to exceed 110 this AD, unless the AD specifies otherwise. exhaust pipes. We are issuing this AD
hours TIS, inspect each splice for a crack in (i) Airbus Helicopters Alert Service to require actions to address the unsafe
the area depicted as Area Y in Figure 3 of Bulletin No. EC225–05A038, Revision 0, condition on these products.
ASB EC225–05A038 or ASB AS332–05.00.97. dated April 15, 2014.
(ii) Airbus Helicopters Alert Service DATES: This AD is effective June 12,
If a crack exists, repair or replace the splice
before further flight. Bulletin No. AS332–05.00.97, Revision 0, 2018.
dated April 15, 2014. The Director of the Federal Register
(f) Credit for Actions Previously Completed (3) For Airbus Helicopters service approved the incorporation by reference
Installing rail support cut-outs in information identified in this AD, contact of certain publications listed in this AD
accordance with MOD 0728090 or Airbus Airbus Helicopters, Inc., 2701 N. Forum as of June 12, 2018.
Helicopters Service Bulletin No. 05–019, Drive, Grand Prairie, TX 75052; telephone The Director of the Federal Register
Revision 4, dated September 22, 2014, before (972) 641–0000 or (800) 232–0323; fax (972)
approved the incorporation by reference
the effective date of this AD is considered 641–3775; or at http://
www.airbushelicopters.com/techpub. of certain other publications listed in
acceptable for compliance with the
corresponding actions specified in paragraph (4) You may view this service information this AD as of May 31, 2017 (82 FR
(e)(1)(i) of this AD. at the FAA, Office of the Regional Counsel, 24843, May 31, 2017) and August 1,
Southwest Region, 10101 Hillwood Pkwy., 2017 (82 FR 35630, August 1, 2017).
(g) Alternative Methods of Compliance Room 6N–321, Fort Worth, TX 76177. For We must receive comments on this
(AMOCs) information on the availability of this AD by July 9, 2018.
daltland on DSKBBV9HB2PROD with RULES
(1) The Manager, Safety Management material at the FAA, call (817) 222–5110.
ADDRESSES: You may send comments by
Section, Rotorcraft Standards Branch, FAA, (5) You may view this service information
may approve AMOCs for this AD. Send your that is incorporated by reference at the any of the following methods:
proposal to: Gary Roach, Aviation Safety National Archives and Records • Federal eRulemaking Portal: Go to
Engineer, Regulations & Policy Section, Administration (NARA). For information on http://www.regulations.gov. Follow the
Rotorcraft Standards Branch, FAA, 10101 the availability of this material at NARA, call instructions for submitting comments.
Hillwood Pkwy., Fort Worth, TX 76177; (202) 741–6030, or go to: http:// • Fax: (202) 493–2251.
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![Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations 23781
• Mail: U.S. Department of on mandatory continuing airworthiness was superseded, and additionally requiring
Transportation, Docket Operations, M– information (MCAI) originated by an those actions for the additional brackets. That
30, West Building Ground Floor, Room aviation authority of another country. [EASA] AD also required reinstallation of the
Since we issued AD 2017–01–12, AD additional brackets in accordance with
W12–140, 1200 New Jersey Avenue SE, improved instructions.
Washington, DC 20590. 2017–11–08, and AD 2017–15–09, the Since EASA AD 2017–0120 was issued, it
• Hand Delivery: U.S. Department of European Aviation Safety Agency has been determined that installation of
Transportation, Docket Operations, M– (EASA) has issued a new AD. additional exhaust pipe brackets, combined
30, West Building Ground Floor, Room The EASA, which is the Technical with additional inspections, is the most
W12–140, 1200 New Jersey Avenue SE, Agent for the Member States of the adequate solution to address the original
Washington, DC 20590, between 9 a.m. European Community, has issued AD unsafe condition, while it was also
No. 2017–0254, dated December 21, established that the modified exhaust pipes
and 5 p.m., Monday through Friday,
2017 (referred to after this as ‘‘the without directly attached heat shield are not
except Federal holidays. adequate as replacement parts. Durability
For service information identified in MCAI’’), to correct an unsafe condition analysis of the design is still under
this AD, contact Diamond Aircraft for the specified products. The MCAI investigation and further improvements in
Industries GmbH, N.A. Otto-Strabe 5, states: the exhaust design are expected.
A–2700 Wiener Neustadt, Austria, Two cases were reported of uncommanded For the reasons described above, this
telephone: +43 2622 26700; fax: +43 engine in-flight shutdown (IFSD) on DA 42 [EASA] AD partially retains the requirements
2622 26780; email: office@diamond- aeroplanes. Subsequent investigation of EASA AD 2017–0120, which is
identified that these occurrences were due to superseded, removing the option to install a
air.at; internet: http:// modified exhaust pipe without direct heat
www.diamondaircraft.com. You may failure of the propeller regulating valve,
caused by hot exhaust gases coming from shield, and adding inspection requirements
review copies of the referenced service for aeroplanes modified in accordance with
fractured engine exhaust pipes. The initiating
information at the FAA, Small Airplane cracks on the exhaust pipes were not Section III.2 of DAI WI–MSB 42–120
Standards Branch, 901 Locust, Kansas detected during previous inspections, since Revision 3 or later (installation of additional
City, Missouri 64106. For information those exhaust pipes are equipped with non- brackets), and for aeroplanes on which an
on the availability of this material at the removable heat shields that do not allow exhaust pipe with directly attached heat
inspection for certain sections of the exhaust shield was re-installed in accordance with
FAA, call (816) 329–4148. It is also DAI OSB 42–131.
available on the internet at http:// pipe.
www.regulations.gov by searching for This condition, if not corrected, could lead You may examine the MCAI on the
to further cases of IFSD or overheat damage, internet at http://www.regulations.gov
locating Docket No. FAA–2018–0188.
possibly resulting in a forced landing, with by searching for and locating Docket No.
Examining the AD Docket consequent damage to the aeroplane and FAA–2018–0188.
injury to occupants.
You may examine the AD docket on To address this potential unsafe condition, Relative Service Information Under 1
the internet at http:// Diamond Aircraft Industries (DAI) developed CFR Part 51
www.regulations.gov by searching for an exhaust pipe without a directly attached
and locating Docket No. FAA–2018– integral heat shield that allows visual Diamond Aircraft Industries GmbH
0188; or in person at Docket Operations inspection over the entire exhaust pipe (DAI) has issued Work Instruction WI–
between 9 a.m. and 5 p.m., Monday length. DAI issued Mandatory Service MSB 42–120, Revision 3, dated July 6,
through Friday, except Federal holidays. Bulletin (MSB) 42–120 and relevant Working 2017, Work Instruction WI–MSB 42–
The AD docket contains this AD, the Instruction (WI) WI–MSB 42–120, providing 120, Revision 4, dated December 20,
regulatory evaluation, any comments
instructions to install the modified exhaust 2018, Mandatory Service Bulletin MSB–
pipes. As an interim measure, an additional 42–129, dated May 17, 2017, and Work
received, and other information. The bracket was designed to hold the exhaust Instruction WI–OSB 42–131, dated
street address for Docket Operations pipe in place in case of a pipe fracture. EASA December 20, 2017. DAI Work
(telephone (800) 647–5527) is in the issued AD 2016–0156 (later revised),
Instruction WI–MSB 42–120, Revision
ADDRESSES section. Comments will be requiring replacement of the exhaust pipes
with pipes having the new design, or 3, dated July 6, 2017, and Work
available in the AD docket shortly after
installation of the additional brackets. Instruction WI–MSB 42–120, Revision
receipt.
After EASA AD 2016–0156R1 was issued, 4, dated December 20, 2018, have
FOR FURTHER INFORMATION CONTACT: identical procedures for installing
cracks were found during inspection on
Mike Kiesov, Aerospace Engineer, FAA, modified exhaust pipes. Further investigation additional engine exhaust pipe clamps
Small Airplane Standards Branch, 901 determined that, with the modified exhaust with spring washers on original engine
Locust, Room 301, Kansas City, pipe design, vibration leads to cracking. exhaust pipes. DAI Work Instruction
Missouri 64106; telephone: (816) 329– Consequently, DAI published MSB 42–129, WI–MSB 42–120, Revision 4, dated
4144; fax: (816) 329–4090; email: providing instructions for inspection of December 20, 2018, also includes
mike.kiesov@faa.gov. modified exhaust pipes, and EASA issued
procedures for inspecting the original
AD 2017–0090, retaining the requirements of
SUPPLEMENTARY INFORMATION:
EASA AD 2016–0156R1, which was engine exhaust pipe for cracks. DAI
superseded, and additionally requiring Mandatory Service Bulletin MSB–42–
Discussion
repetitive inspections of modified exhaust 129, dated May 17, 2017, describes
We issued AD 2017–01–12, pipes and, depending on findings, repair or procedures for inspecting the modified
Amendment 39–18779 (82 FR 5359, replacement. engine exhaust pipe for cracks. DAI
January 18, 2017) (‘‘AD 2017–01–12’’); After EASA AD 2017–0090 was issued, Work Instruction WI–OSB 42–131,
AD 2017–11–08, Amendment 39–18907 cracks were found on additional brackets, as dated December 20, 2017, describes
(82 FR 24843, May 31, 2017) (‘‘AD previously installed per DAI WI–MSB 42– procedures for replacing either the
2017–11–08’’), and AD 2017–15–09, 120. Prompted by these findings, DAI revised original or the modified engine exhaust
daltland on DSKBBV9HB2PROD with RULES
MSB 42–120 and the relevant part of WI–
Amendment 39–18969 (82 FR 35630, pipe if cracks are found. This service
MSB 42–120 (now at Revision 4), providing
August 1, 2017) (‘‘AD 2017–15–09’’). improved instructions for the installation of information is reasonably available
Those ADs required actions intended to brackets, and additional instructions to because the interested parties have
address an unsafe condition on certain inspect those brackets. Consequently, EASA access to it through their normal course
Diamond Aircraft Industries GmbH issued AD 2017–0120, retaining the of business or by the means identified
Model DA 42 airplanes and was based requirements of EASA AD 2017–0090, which in the ADDRESSES section of this AD.
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![Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations 23783
responsibilities among the various Technify P/Ns 52–7810–H0001 02, 52–7810– Instruction WI–MSB 42–120, Revision 4,
levels of government. H0001 03, 52–7810–H0001 04; or dated December 20, 2017.
For the reasons discussed above, I (2) are equipped with a modified engine (i) If the engine exhaust pipe has 1,300
certify that this AD: exhaust pipe DAI P/N D60–9078–06–01_01 hours TIS or less since first installed on an
or Technify 52–7810–H0014 01. airplane as of June 12, 2018 (the effective
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866, (d) Subject date of this AD): Before or upon
accumulating 1,500 hours TIS since the
(2) Is not a ‘‘significant rule’’ under Air Transport Association of America engine exhaust pipe was first installed on an
the DOT Regulatory Policies and (ATA) Code 78: Engine Exhaust. airplane, and repetitively thereafter at
Procedures (44 FR 11034, February 26, intervals not to exceed 500 hours TIS.
(e) Reason
1979), (ii) If the engine exhaust pipe has more
(3) Will not affect intrastate aviation This AD was prompted by mandatory
continuing airworthiness information (MCAI) than 1,300 hours TIS since first installed on
in Alaska, and an airplane as of June 12, 2018 (the effective
issued by the aviation authority of another
(4) Will not have a significant date of this AD): Within the next 200 hours
country to identify and address an unsafe
economic impact, positive or negative, condition on an aviation product. It has been TIS after June 12, 2018 (the effective date of
on a substantial number of small entities determined that installation of additional this AD), and repetitively thereafter at
under the criteria of the Regulatory exhaust pipe brackets, combined with intervals not to exceed 500 hours time-in-
Flexibility Act. additional inspections, is the most adequate service (TIS).
solution to address the original unsafe (2) During any inspection required in
List of Subjects in 14 CFR Part 39 condition, while it was also established that paragraph (g)(1) of this AD, if the engine
Air transportation, Aircraft, Aviation the modified exhaust pipes without directly exhaust pipe does not pass the inspection
safety, Incorporation by reference, attached heat shield are not adequate as criteria, before further flight replace the
replacement parts. Durability analysis of the engine exhaust pipe following section III.1—
Safety.
design is still under investigation and further Re-installation of Exhaust Pipes with Directly
Adoption of the Amendment improvements in the exhaust design are Attached Heat Shield in the INSTRUCTIONS
expected. For these reasons, this AD removes section of DAI Work Instruction WI–OSB 42–
Accordingly, under the authority the option to install a modified exhaust pipe 131, dated December 20, 2017 (which
delegated to me by the Administrator, without direct heat shield, adds inspection includes installing additional engine exhaust
the FAA amends 14 CFR part 39 as requirements for airplanes modified in pipe clamps, an exhaust sheet, and
follows: accordance with Section III.2 of Diamond incorporates spring washers). After
Aircraft Industries (DAI) WI–MSB 42–120 replacement continue with the 500-hour TIS
PART 39—AIRWORTHINESS Revision 3, dated July 6, 2017 (installation of repetitive inspections.
DIRECTIVES additional brackets), and for airplanes on (i) If only the engine exhaust pipe heat
which an exhaust pipe with directly attached shield is loose, a one-time single weld is
■ 1. The authority citation for part 39 heat shield was re-installed in accordance allowed following section III.3—Repair of
continues to read as follows: with DAI Work Instruction WI–OSB 42–131, Heat Shields of DAI P/N D60–9078–06–01/
dated December 20, 2017. The MCAI Technify P/Ns 52–7810–H0001 03 and 52–
Authority: 49 U.S.C. 106(g), 40113, 44701. describes the unsafe condition as 7810–H0001 04 in the INSTRUCTIONS
uncommanded engine shutdown during section of DAI Work Instruction WI–OSB 42–
§ 39.13 [Amended]
flight due to failure of the propeller 131, dated December 20, 2017. After a repair
■ 2. The FAA amends § 39.13 by regulating valve caused by hot exhaust gases of the heat shield, if a single weld point is
removing Amendment 39–18779 (82 FR coming from fractured engine exhaust pipes. subsequently found cracked, the heat shield
5359, January 18, 2017), Amendment We are issuing this AD to prevent failure of is considered to be loose and the exhaust
39–18907 (82 FR 24843, May 31, 2017), the propeller regulating valve, which could pipe must be replaced. After replacement or
result in forced landing, consequent damage
and Amendment 39–18969 (82 FR repair, continue with the 500-hour TIS
and occupant injury.
35630, August 1, 2017) and adding the repetitive inspections.
following new AD: (f) Compliance (ii) Engine exhaust pipes re-qualified
Unless already done, do the following following section III.2—Re-Qualification of
2018–10–10 Diamond Aircraft Industries Exhaust Pipes DAI P/N D60–9078–06–01/
GmbH: Amendment 39–19285; Docket actions.
(1) An airplane is only required to have the Technify P/Ns 52–7810–H0001 02, 52–7810–
No. FAA–2018–0188; Directorate H0001 03, or 52–7810–H0001 04 in the
Identifier 2018–CE–002–AD. actions of either (g) or (h) of this AD
accomplished depending on the INSTRUCTIONS section of DAI Work
(a) Effective Date configuration. Instruction WI–OSB 42–131, dated December
(2) For the purpose of this AD, if the flight 20, 2017, are considered to have accumulated
This airworthiness directive (AD) becomes
hours accumulated since first installation of 1,500 hours TIS.
effective June 12, 2018.
an affected exhaust pipe or additional (3) Before further flight after the initial
(b) Affected ADs exhaust pipe clamp is not known, use the inspection required in paragraph (g)(1) of this
This AD replaces 2017–01–12, Amendment total hours time-in-service (TIS) accumulated AD and if no cracks were found or a repair
39–18779 (82 FR 5359, January 18, 2017) on the airplane. to the exhaust pipe heat shield was done as
(‘‘AD 2017–01–12’’); AD 2017–11–08, required in paragraph (g)(2)(i) of this AD,
(g) Actions for Airplanes With Installed then install additional engine exhaust pipe
Amendment 39–18907 (82 FR 24843, May 31,
Original Engine Exhaust Pipes as of June 12, clamps, DAI P/Ns D60–7806–00–01 and
2017) (‘‘AD 2017–11–08’’), and AD 2017–15–
2018 (the Effective Date of This AD) D60–7806–00–02, and exhaust sheet, P/N
09, Amendment 39–18969 (82 FR 35630,
August 1, 2017) (‘‘AD 2017–15–09’’). See Appendix 1 to AD 2018–10–10 for a D60–7806–00–03, and incorporate spring
chart of required actions. An original engine washers. Do the installations following III.2
(c) Applicability exhaust pipe is defined in paragraph (c), Action 2—installation of additional exhaust
This AD applies to Diamond Aircraft Applicability, of this AD. clamp in the INSTRUCTIONS section of DAI
(1) At the applicable compliance time in Work Instruction WI–MSB 42–120, Revision
daltland on DSKBBV9HB2PROD with RULES
Industries GmbH Model DA 42 airplanes,
serial numbers 42.004 through 42.427 and paragraphs (g)(1)(i) and (ii) of this AD, and 3, dated July 6, 2017, or Revision 4, dated
42.AC001 through 42.AC151, certificated in repetitively thereafter at intervals not to December 20, 2017. See figure 1 to paragraph
any category, that have either a TAE 125–02– exceed 500 hours time-in-service (TIS), (g)(3) of this AD for additional information
99 or TAE 125–02–114 engine installed, and: inspect the installed engine exhaust pipe. Do on the sequence of installation actions as
(1) are equipped with an original engine this inspection following section III.4— identified in DAI Work Instruction WI–MSB
exhaust pipe, Diamond Aircraft Industries Inspection of exhaust pipe in the 42–120, Revision 3, dated July 6, 2017 and
(DAI) part number (P/N) D60–9078–06–01 or INSTRUCTIONS section of DAI Work Revision 4, dated December 20, 2017.
VerDate Sep<11>2014 16:18 May 22, 2018 Jkt 244001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\23MYR1.SGM 23MYR1](https://thefederalregister.org/doc/83_FR_23880/page/4.svg)
Document Created: 2018-05-22 23:49:11
Document Modified: 2018-05-22 23:49:11
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments | |
| Dates | This AD is effective June 12, 2018. | |
| Contact | Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: [email protected] | |
| FR Citation | 83 FR 23780 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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