Division SMA Piston Engines - AD/SMA/2 Amdt 1 - Engine Electronic Control Unit - SMA Piston Engines

SMA Piston Engines

AD/SMA/2 Amdt 1	Engine Electronic Control Unit	4/2007 DM

<table cellspacing="0" cellpadding="0" style="width:510.3pt; margin-top:0pt; margin-bottom:0pt; border-collapse:collapse"><tbody><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Applicability:</span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>All aircraft with a Société de Motorisations Aéronautiques (SMA) SR305-230 or SR305-230-1 engine equipped with an electronic control unit (ECU) having a part number (P/N) listed below:</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td style="width:131.05pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:36pt; text-indent:-36pt"><span style="width:36pt; text-indent:0pt; display:inline-block"></span><span>SF01160009-0</span><br><span>SP01160051-0</span><br><span>SP01160051-3</span><br><span>SP01160089-0</span></p></td><td style="width:131.05pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>SF01160011-0</span><br><span>SP01160051-1</span><br><span>SP01160051-4</span><br><span>SP01160089-1</span></p></td><td style="width:131.05pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>SP01160013</span><br><span>SP01160051-2</span><br><span>SP01160051-5</span><br><span>SP01160089-2</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 1:</span><span> </span><span>These engines are known to be installed on, but not limited to, Cessna 182 and </span><span>Reims</span><span> F182 series aeroplanes.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>Requirement:</span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>1.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>If the ECU was not replaced in accordance with the original issue of the Directive, determine </span><span>the P/N and the serial number (S/N) of the ECU installed on the aircraft</span><span>.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>2.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>If the ECU is determined to have a P/N listed in the ‘Applicability’ section of this Amendment and a S/N 131 or below, </span><span>with the exception S/Ns 70, 71, 83 and 88</span><span>.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:42.55pt; text-indent:-21.25pt"><span>a.</span><span style="width:12.92pt; text-indent:0pt; display:inline-block"> </span><span>Do not operate the engine unless in accordance with restriction noted below.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:42.55pt; text-indent:-21.25pt"><span>b.</span><span style="width:12.25pt; text-indent:0pt; display:inline-block"> </span><span>Remove and replace the ECU with an ECU P/N SP01160089-3, in accordance with the SMA Service Bulletin </span><span>SB-01-76-005, dated 15</span><span> </span><span>December</span><span> </span><span>2006, or later EASA approved revision.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span>One ferry flight to a location capable of completing the ECU replacement is allowed. The pilot should be ready to react appropriately to a sudden power increase.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>3.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Replace all remaining affected P/N ECU with an ECU P/N SP01160089-3 in accordance with the SMA </span><span>SB-01-76-005 or later EASA approved revision.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p style="margin-left:21.3pt; text-indent:-21.3pt"><span>4.</span><span style="width:12.3pt; text-indent:0pt; display:inline-block"> </span><span>Spare ECUs having a part number listed in the ‘Applicability’ section of this Amendment may not be installed on any SMA SR305-230 or SR305-230-1 engine as a replacement part.</span></p></td></tr><tr><td style="width:74.35pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span></span></p></td><td colspan="3" style="width:414.55pt; padding-right:5.35pt; padding-left:5.35pt; vertical-align:top"><p class="Note"><span>Note 2:</span><span> </span><span>EASA Emergency AD 2007-0033 refers.</span></p></td></tr></tbody></table>

Compliance:	For Requirement 1 - Before further flight after 7 March 2007.
	For Requirement 2 - Immediately after the Requirement 1 determination.
	For Requirement 3 - Not later than 31 March 2007.
	For Requirement 4 - After 31 March 2007.
	This Amendment becomes effective on 7 March 2007.
Background:	The European Aviation Safety Agency (EASA) has been advised by the engine manufacturer that over a period of time, the alteration of one ECU electronic component can cause a rapid uncontrolled power increase. Several occurrences have already been reported during engine start or during engine warm-up. This could result in loss of control of the aircraft.
	This original issue of this Directive required the aircraft to be inspected to determine the ECU S/N and, if necessary, the replacement of the ECU. The Directive also allows a one time flight to a location capable of effecting replacement of the ECU. EASA has now advised that this was a temporary corrective action.
	This Amendment clarifies the applicability by including a part number range and advises that the affected engine may also be installed on Reims F182 aeroplanes. At the same time, the Amendment identifies a replacement ECU part number and requires the replacement of all affected ECUs, irrespective of their serial number. Additionally, the Amendment prohibits the fitment of an affected ECU as a spare after 31 March 2007.
	The original issue of this Directive became effective on 17 October 2006.

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