Airworthiness Directive Schedule Aeroplanes Piper PA-46 Series (Malibu and Meridian)

“THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING: • Visible rain at temperatures below 0 degrees Celsius ambient air temperature. • Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air temperature. PROCEDURES FOR EXITINGTHE SEVERE ICING ENVIRONMENT: These procedures are applicable to all flight phases from takeoff to landing. Monitor the ambient air temperature. While severe icing may form at temperatures as cold as -18 degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in the Limitations Section of the AFM for identifying severe icing conditions are observed, accomplish the following: • Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the aircraft has been certificated. • Avoid abrupt and excessive manoeuvring that may exacerbate control difficulties. • Do not engage the autopilot. • If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. • If an unusual roll response or uncommanded roll control movement is observed, reduce the angle-of-attack. • Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area. • If the flaps are extended, do not retract them until the airframe is clear of ice. • Report these weather conditions to Air Traffic Control.” Note: This may be accomplished by inserting a copy of this AD in the AFM or by incorporating a manufacturer’s flight manual revision that contains the wording per this AD. 3. Flight Crew Notification Operators must ensure that flight crew are aware of the flight manual revision. (FAA AD 98-04-26 refers) Compliance: By 10 May 1998 Effective Date: 10 April 1998 DCA/PA46/3 Cancelled – DCA/PA46/7 refers Effective Date: 21 April 2011 Aeroplanes Piper PA-46 Series (Malibu and Meridian) Issued 21 December 2023 Page 4 of 8 CAA of NZ DCA/PA46/4 Flap Drive Bellcrank Assemblies - Inspection Applicability: Model PA-46-310P S/N 46-8408001 through 46-8408087, 46-8508001 through 46- 8508109, 46-8608001 through 46-8608067, and 4608001 through 4608140. Model PA-46-350P S/N 4622001 through 4622200 and 4636001 through 4636313. Model PA-46-500TP S/N 4697001 through 4697020, 4697023, 4697024, 4697025, 4697027 through 4697037, 4697040 through 4697052, 4697054, 4697055, 4697058, and 4697059. Requirement: To prevent failure of the flap drive bellcrank assemblies and subsequent inability to control the flaps and possible loss of control of the aircraft, accomplish the following:- 1. Inspect LH and RH inboard flap drive bellcrank assemblies, Piper P/N 82905-2 and P/N 82905-3, per Piper SB 1062, to ensure that the welding is complete and adequate. Replace any assembly that has incomplete or inadequate welding prior to further flight. 2. Do not install any inboard flap drive bellcrank assembly, Piper P/N 82905-2 or P/N 82905-3, unless you have ensured that the welding is complete and adequate. (FAA AD 2001-12-01 refers) Compliance: 1. Within next 10 hours TIS. 2. From 28 June 2001. Effective Date: 28 June 2001 DCA/PA46/5A Control Wheel Attachment – Inspection and Modification Applicability: Group A aircraft: Model PA-46-350P aircraft, S/N 4636132 through to 4636344, and Model PA–46–500TP aircraft, S/N 4697001 through to 4697162. Group B aircraft: Model PA-46-350P aircraft, S/N 4636345 through to 4636348, and model PA–46–500TP aircraft, S/N 4697163 through to 4697174. Note: No action required if already in compliance with DCA/PA46/5. The AD applicability revised to include PA-46-500TP aircraft. Requirement: To detect and correct inadequate control wheel attachment design, which could result in loss of control, accomplish the following; 1. For Group A aircraft: Inspect the control wheel attachment screw and nut-plate for proper thread engagement (minimum one thread showing past the end of the nut plate), and replace the screw and/or nut plate if insufficient thread engagement is found. Reassemble the control wheel onto the control wheel shaft and apply Loctite thread-locking compound. 2. For Group A and B aircraft: Install the retainer clip P/N 104687-002 per part II of New Piper Aircraft SB 1139A. (FAA AD 2004-14-12 refers) Compliance: 1. Inspect within the next 25 hours TIS unless previously accomplished. 2. Install the retainer clip within the next 100 hours TIS unless previously accomplished. Effective Date: DCA/PA46/5 - 26 August 2004 DCA/PA46/5A - 28 October 2010 Aeroplanes Piper PA-46 Series (Malibu and Meridian) Issued 21 December 2023 Page 5 of 8 CAA of NZ DCA/PA46/6 Airworthiness Directive Compliance at Initial Airworthiness Certificate Issue Applicability: Model PA-46-500TP aircraft, all S/N Requirement: Compliance with the following Federal Aviation Administration (FAA) Airworthiness Directives (as applicable) is required: FAA AD No: Piper Service Information: Subject and Applicability: AD Requirement: 2004-03-32 Piper SB No. 1132 dated 4 June 2003. Electronic Control Modules. Model PA-46-500TP aircraft, S/N 4697001 through to 4697140 and 4697142 through to 4697153. Accomplish the AD requirements per the instructions in Piper SB No. 1132. 2004-15-19 Piper SB No. 1140 dated 16 September 2003. Protective percussion caps or silicone tube installed over the end of the trigger mechanism. Model PA-46-500TP aircraft, S/N 4697001 through to 4697163. Accomplish the AD requirements per the instructions in Piper SB No. 1140. 2008-26-11 Piper SB No. 1192 dated 15 September 2008, drawing no. 88452 dated 19 June 2008. Stall Vane Heater. Model PA-46-500TP aircraft, S/N 4697001 through to 4697365. Accomplish the instructions in Piper SB No. 1192 and drawing no. 88452. Note 1: Each part of this AD (each individual FAA AD) shall be certified in the aircraft log book separately. Note 2: Manufacturer service information at later FAA approved revisions is acceptable to comply with the requirements of this AD. Compliance: Before issue of a New Zealand Certificate of Airworthiness, or at the next ARA inspection after the effective date of this AD whichever is the sooner, unless previously accomplished. Effective Date: 28 October 2010 DCA/PA46/7 Turbine Inlet Temp Gauge System – Inspection, Calibration and Replacement Applicability: Group 1 aircraft previously affected by DCA/PA46/3: Model PA–46–310P (Malibu) aircraft, S/N 46–8408001 through to 46–8608067 and 4608001 through to 4608140, Model PA–46–350P (Malibu Mirage) aircraft, S/N 4622001 through to 4622200 and 4636001 through to 4636020, and Group 2 aircraft previously not affected by DCA/PA46/3: Model PA–46–350P (Malibu Mirage) aircraft, S/N 4636021 onwards, Model PA–46R–350T (Matrix) aircraft, S/N 4692001 onwards, and Fitted with a Turbine Inlet Temperature (T.I.T.) system identified in Table 1: Aeroplanes Piper PA-46 Series (Malibu and Meridian) Issued 21 December 2023 Page 6 of 8 CAA of NZ Table 1 Model S/N Indication System P/N Probe P/N PA-46-310P 46-8408001 through 46- 8608067 and 4608001 through to 4608140 Lewis T.I.T. analog indicators P/N 471- 008 471-009 or 481-387 PA-46-350P 4622001 through 4622200 and 4636001 through to 4636020 Lewis T.I.T. analog indicators P/N 471- 008 481-389 or 481- 392 or 686-216 (preferred) PA-46-350P 4636021 through 4636374 Lewis T.I.T. digital indicators P/N 548- 811 481-389 or 481-392 or 686-216 (preferred) PA-46-350P 4636375 onwards Avidyne Entegra or other Electronic Flight Information System (EFIS) display 686-216 PA-46R-350T 4692001 onwards Avidyne Entegra or other EFIS display 686-216 Note 1: This AD retains the requirements in superseded AD DCA/PA46/3, expands the applicability to include certain model PA-46R-350T aircraft and other T.I.T. systems, and introduce new service information. Note 2: Relief from this AD is available only if the gauge and probe are replaced through an STC and not if a second T.I.T. gauge was installed while retaining the Lewis or Transicoil T.I.T. gauge and probe. Requirement: To prevent engine damage/failure due to possible incorrectly calibrated T.I.T. indicators or defective T.I.T. probes which could result in loss of engine power and aircraft control, accomplish the following: 1. Group 1 aircraft previously affected by DCA/PA46/3: Clean and inspect the T.I.T. gauge and probe per the instructions in Piper MM PA-46- 310P/PA-46-350P P/N 761-783, chapter 77-20-00, section A.(1)(d), pages 1 and 2, dated 1 July 1998, and Piper MM PA-46-350P/PA-46R-350T P/N 761-876, chapter 77-20-00, section 1.C, pages 1 and 2, dated 31 July 2008, as applicable. Calibrate the T.I.T. system per the instructions in Piper MM PA-46-310P/PA-46-350P P/N 761-783, chapter 77-20-00, section A.(1)(g), pages 3 and 4, dated 1 July 1998, and Piper MM PA-46-350P/PA-46R-350T P/N 761-876, chapter 77-20-00, section 1.F, page 2, dated 31 July 2008, and pages 3 and 4, dated 28 August 2007, as applicable, or Piper SB No. 995C, dated 17 November 2009. If the T.I.T. probe fails the inspection requirements and/or the T.I.T. system indicator cannot be calibrated, replace defective parts with a serviceable part listed in table 1 of this AD provided the replacement parts have been inspected, passed the inspection, and been properly calibrated per the requirements of this AD. Accomplish these requirements per the instructions in Piper MM PA-46-310P/PA-46-350P P/N 761-783, chapter 77-20-00, section A.(1)(f), page 2, dated 1 July 1998; and Piper MM PA-46- Aeroplanes Piper PA-46 Series (Malibu and Meridian) Issued 21 December 2023 Page 7 of 8 CAA of NZ 350P/PA-46R-350T P/N 761-876, chapter 77-20-00, section 1.E., page 2, dated 31 July 2008, as applicable, or Piper SBn No. 995C, dated 17 November 2009. Incorporate the information in appendix 1 and appendix 2 of FAA AD 2011-06-10, as applicable into the emergency procedures section of the AFM. This may be done by inserting a copy of FAA AD 2011-06-10 into the AFM. Note 3: For all group 1 aircraft the parts listed in Table 1 of this AD may only be fitted once they have been inspected and correctly calibrated per the requirements of this AD. 2. Group 1 model PA-46-350P aircraft only (this action is not required for model PA-46-310P: Replace the T.I.T. probe with a new P/N 481-389, 481-392 or 686-216 probe (preferred). For S/N 4622001 through to 4622200 accomplish this requirement per the instructions in Piper MM PA-46-310P/PA-46-350P P/N 761-783, chapter 77-20-00, section A.(1)(f), page 2, dated 1 July 1998, or Piper SB No. 995C, dated 17 November 2009. For S/N 4636001 through to 4636020 accomplish this requirement per the instructions in Piper MM PA-46-350P/PA-46R-350T P/N 761-876, chapter 77-20-00, section 1.E., page 2, dated 31 July 2008, or Piper SB No. 995C, dated 17 November 2009. 3. Group 2 aircraft previously not affected by DCA/PA46/3: For model PA-46-350P aircraft, S/N 4636021 through to 4636374 clean and inspect the T.I.T. gauge and probe per the instructions in Piper MM PA-46-350P/PA-46R- 350T P/N 761-876, chapter 77-20-00, section 1.C, page 1, dated 28 August 2007, and page 2, dated 31 July 2008. If the T.I.T. probe fails the inspection, replace defective parts with a serviceable part listed in table 1 of this AD provided the replacement parts have been inspected, passed the inspection per the requirements of this AD. Accomplish these requirements per the instructions in Piper SB No. 995C, dated 17 November 2009. For all Group 2 aircraft incorporate the information in appendix 2 of FAA AD 2011-06- 10 into the emergency procedures section of the AFM. This may be accomplished by inserting a copy of FAA AD 2011-06-10 into the AFM. 4. Group 2 aircraft previously not affected by DCA/PA46/3: Replace the T.I.T. probe with a new P/N 686-216 probe per the instruction in Piper SB No. 995C, dated 17 November 2009. Note 4: For all group 2 aircraft the parts listed in Table 1 of this AD may only be fitted once they have been inspected and correctly calibrated per the requirements of this AD. (FAA AD 2011-06-10 refers) Compliance: 1. Within the next 100 hours from 27 August 1999 (the effective date of DCA/PA46/3) unless previously accomplished. 2. Before accumulating 250 hours TIS on the currently installed T.I.T. probe or within the next 100 hours TIS after 27 August 1999 (the effective date of DCA/PA46/3) whichever occurs later, unless previously accomplished and thereafter at intervals not to exceed 250 hours TIS. 3. Within the next 100 hours TIS. 4. Before accumulating 250 hours TIS on the currently installed T.I.T. probe or within the next 100 hours TIS whichever occurs later, and thereafter at intervals not to exceed 250 hours TIS. Effective Date: 21 April 2011 Aeroplanes Piper PA-46 Series (Malibu and Meridian) Issued 21 December 2023 Page 8 of 8 CAA of NZ The State of Design ADs listed below are available directly from the National Airworthiness Authority (NAA) websites. Links to NAA websites are available on the CAA website at https://www.aviation.govt.nz/aircraft/airworthiness/airworthiness-directives/links-to-state-of- design-airworthiness-directives/ If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ, they will be added to the list below. 2013-13-01 Fuel Vent Valves – Inspection Note: FAA AD 2013-13-01 dated 12 September 2013 is re-issued with corrections. The AD effective date remains 10 July 2013. Effective Date: 10 July 2013 2015-13-09 Cabin Altitude Encoder – Inspection Effective Date: 13 July 2015 2016-01-01 Upper Wing Skin – Inspection Effective Date: 17 February 2016 2021-09-02 Stall Warning Heat Control System – Inspection Applicability: Piper PA-46-350P (Malibu Mirage) aircraft, S/N 4622041, 4636041, 4636142, 4636143, 4636313, 4636341 and 4636379, Piper PA-46-500TP (Malibu Meridian) aircraft, S/N 4697141, 4697161, 4697086, and 4697020, Piper PA-46-350P (Malibu Mirage), PA-46R-350T (Malibu Matrix), and PA-46-500TP (Malibu Meridian) aircraft, all S/N, if the left wing has been replaced with a serviceable (more than zero hours TIS) wing. Note: This AD supersedes FAA AD 2021-04-07 which was effective 30 March 2021. Effective Date: 29 April 2021 * 2023-25-02 Controll Column Mount Bearing – Inspection Applicability: PA-46-350P aircraft, S/N 4636811 through to 4636814 inclusive and 4636816 through to 4636829 inclusive. PA-46-500TP aircraft, S/N 4697692 through to 4697700 inclusive. PA-46-600TP aircraft, S/N 4698224 through to 4698240 inclusive and 4698242 through to 4698274 inclusive. Effective Date: 19 December 2023