Airworthiness Directive Schedule Aeroplanes Piper PA-24 Series (Comanche)

fuel tanks and the upper fasteners of the auxiliary fuel tanks which retain the bladder tanks to ensure security per section VIII of Piper Comanche Service Manual No. 753516 or accomplish an equivalent inspection approved by the manufacturer. The fuel tanks shall be empty when performing this inspection. Remove the tank filler caps and inspect the tank vent tubes under the wing for dirt or ice blockage. Apply suction to each vent tube outlet to assure that there is no blockage. Inspect all fuel tank filler caps for security and ensure the correct P/N cap is fitted. If the rubber portion of the "thermos" type filler caps (S/N 24-581 onwards) have any indications of dryness, or hardness which can cause the cap to gradually loosen, replace the cap before further flight. Accomplish a fuel quantity gauge sending unit check per section VIII of Piper Comanche Service Manual No. 753516 or accomplish an equivalent inspection approved by the manufacturer. 2. For aircraft S/N 24-581 through to 24-3495 modify the fuel tank drain tubes in accordance with Piper SB No. 216 dated 21 June 1963 or later FAA approved revisions, or embody an equivalent manufacturer approved modification. Note 2: Compliance with SL No. 516, or later FAA approved revisions, or a manufacturer approved modification is a terminating action to the requirements of this AD. Note 3: Piper SL No. 516 pertains to the embodiment of modification kit No. 760277 for fuel tank vents and drain tubes, and the embodiment of Kit No. 760281 for auxiliary tanks, if fitted. Note 4: Piper SB Nos. 216 and 231A pertain to the subject of this AD, and Piper SL Nos. 367 and 516 also pertain to the subject of this AD. (FAA AD 1968-13-03 refers) Compliance: 1. Within the next 25 hours TIS unless previously accomplished, and thereafter at intervals not to exceed 100 hours TIS. 2. Within the 100 hours TIS, unless previously accomplished. Effective Date: DCA/PA24/101A - 31 July 1969 DCA/PA24/101B - 27 August 2009 DCA/PA24/102 Vacuum Pump Splined Coupling - Replacement Applicability: All Requirement: Piper SB 218 Compliance: As detailed Effective Date: 31 July 1969 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 4 of 12 CAA of NZ DCA/PA24/103 30 Ampere Circuit Protector - Modification Applicability: All not equipped with 30 amp circuit protector. Requirement: Piper SL 356 Compliance: Within the next 100 hours TIS Effective Date: 31 July 1969 DCA/PA24/104 Main Landing Gear Door Hinges and Nose Gear Door Hinge - Inspection Applicability: As detailed. Requirement: Piper SL 380 Compliance: Within the next 100 hours TIS and at intervals not exceeding 100 hours TIS thereafter Effective Date: 31 July 1969 DCA/PA24/105 Muffler Shroud - Modification Applicability: S/N as detailed. Requirement: Piper SB 210 Compliance: Within the next 50 hours TIS Effective Date: 31 July 1969 DCA/PA24/106 Landing Gear Safety Switch Harness - Modification Applicability: S/N 24-1 through 24-3284. Requirement: Piper SL 379 Compliance: Within the next 50 hours TIS Effective Date: 31 July 1969 DCA/PA24/107 Auto Pilot Servo and Bridle Installation - Inspection Applicability: PA-24-260 S/N 24-4567 and up. Requirement: Piper SB 320A Compliance: Within the next 100 hours TIS and thereafter at intervals not exceeding 100 hours TIS Effective Date: 31 October 1970 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 5 of 12 CAA of NZ DCA/PA24/108 Emergency Gear Extension Placard - Modification Applicability: PA-24-260 S/N as detailed. Requirement: Piper SL 574 Compliance: Next periodic inspection Effective Date: 31 May 1971 DCA/PA24/109 Cancelled by DCA/PA24/110 DCA/PA24/110 Cancelled by DCA/PA24/111 DCA/PA24/111 Mass Balance Weights - Modification Applicability: All PA-24, PA-24-250 and PA-24-260. Requirement: To prevent possible adverse vibration effects the FAA have issued AD 72-22-5. Piper Service Bulletin 362A and Piper SL 687 also refer. Modify as follows: Install rudder balance weight installation kit, Piper Part Number 760 705 (Piper SB 362A). Remove the operating limitation placard fitted in accordance with DCA/PA24/110 and alter the Red Radial VNE line and the cautionary Yellow Arc of the Airspeed Indicator to reflect the following speed restrictions: (a) For PA24 aircraft: VNE of 202 MPH CAS. (b) For PA-24-250 and PA-24-260 aircraft: VNE of 203 MPH CAS and VNO of 180 MPH CAS. Note: For PA-24-250 and PA-24-260 aircraft only, installation of Piper kit part number 760 747 in addition to kit part number 760 705, will allow VNE to be returned to the original limit of 227 MPH CAS Compliance: By 1 March 1973 Effective Date: 31 December 1972 DCA/PA24/112A Stabilator Torque Tube Bearing Support Fittings - Inspection Applicability: Model PA-24-180, PA-24-250 and PA-24-260 S/N 24-1 through 24-5047 and 26-2 through 26-148, that have not incorporated Piper P/N 760 835 (Hi-Shear Rivet Replacement Kit) on all four stabilator torque tube bearing support fittings. Requirement: To prevent loss of pitch control because of looseness of the stabilator torque tube bearing support fittings, accomplish the following:- Inspect the stabilator torque tube bearing support fittings for looseness per Piper SB 411A. If looseness is found incorporate Piper P/N 760 835 (Hi-Shear Rivet Replacement Kit) on the affected fitting prior to further flight. (FAA AD 94-13-10 refers) Compliance: Within next 100 hours TIS and thereafter at intervals not to exceed 100 hours TIS. Effective Date: DCA/PA24/112 - 3 August 1974 DCA/PA24/112A - 2 September 1994 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 6 of 12 CAA of NZ * DCA/PA24/113B Stabilator Torque Tube Assembly Bolts - Inspection Applicability Model PA-24, PA24-180, PA-24-250, PA-24-260, S/N 24-1 through 24-5047, and PA- 24-400 S/N 26-2 through 26-148. Note: DCA/PA24/113B revised to introduce a terminating action for requirement 2. Requirement: To detect corroded stabilator torque tube assembly bolts accomplish the following:- 1. Inspect stabilator attachment bolts (4 places) per Piper SL 667A. Replace bolts found corroded before further flight. (FAA AD 74-13-03 refers) 2. Inspect the following bolts for corrosion paying particular attention to their condition where they pass inside the stabilator torque tube; (a) Bolts (2 places), attaching the balance weight tube to stabilator torque tube assembly. Replace bolts found corroded before further flight. (b) Bolts (2 places), attaching the collar assembly to stabilator torque tube assembly. Replace bolts found corroded before further flight. (Occurrence 95/2477 refers) Compliance: 1. Within next 100 hours TIS after 19 January 1996 (the effective date of DCA/PA24/113A) and thereafter at intervals not to exceed 3 years or 500 hours TIS whichever is the sooner. May be discontinued upon fitment of P/N 502 329 or 502 342 corrosion resistant bolts. 2. Within next 100 hours TIS after 19 January 1996 (the effective date of DCA/PA24/113A) and thereafter at intervals not to exceed 3 years or 500 hours TIS whichever is the sooner. The repetitive inspections per requirement 2.(a) and/or 2.(b) may be discontinued upon fitment of equivalent corrosion resistant bolts approved by the aircraft manufacturer. Effective Date: DCA/PA24/113 - 30 August 1974 DCA/PA24/113A - 19 January 1996 DCA/PA24/113B – 28 June 2018 DCA/PA24/114 Fin Forward Spar to Fuselage, Attachment Assembly - Inspection Applicability: All model PA-24, PA-24-250 and PA-24-260 Requirement: Affects the fin forward spar to fuselage attachment assembly where the channel P/N 20749-0 and the straps P/N 20749-5 and -6 are riveted together. 1. Inspect the channel P/N 20749-0 and the two straps P/N 20749-5 and -6 in the area of the channel bend relief holes for cracks using a dye penetrant method or an approved equivalent inspection. Polish the rough edges of the bend relief holes. 2. Visually inspect the channel and straps in the area of the channel relief holes for cracks using a magnifying glass of at least 5 power or an approved equivalent inspection. Repair cracked parts with an approved repair or replace parts with an unused part of the same number prior to further flight. Equivalent inspections may be approved by the CAA. (FAA AD 75-12-06 and Piper SL 751 refer) Compliance: 1. Para 1 of the AD Supplement - within the next 25 hours TIS. 2. Para 2 of the AD Supplement - within the next 125 hours TIS and thereafter at intervals not exceeding 100 hours TIS. Effective Date: 17 June 1975 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 7 of 12 CAA of NZ DCA/PA24/115 Stabilator Torque Tube Bearing Block - Inspection Applicability: Model PA-24, PA-24-250 and PA-24-460 S/N 24-1 through 24-5047. Requirement: Piper SB 464 Compliance: Within the next 50 hours TIS Effective Date: 14 November 1975 DCA/PA24/116 Stabilator Balance Weight Tube - Modification Applicability: Model PA-24-250 and PA-24-260 S/N 24-1, 24-103 through 24-3687, 24-4000 through 24-5047 which have Piper kit P/N 760747 embodied. Requirement: Piper SB 496 Compliance: Within the next 100 hours TIS Effective Date: 30 July 1976 DCA/PA24/117 Electric Trim Switch - Modification Applicability: Model PA-24-260 S/N 24-4783 and 24-4804 through 24-5047 which have Piper kit 760505 embodied per SB 331, or as otherwise detailed in SB 527. Requirement: Piper SB 527 Compliance: Within the next 100 hours TIS Effective Date: 14 December 1976 DCA/PA24/118 Aileron Spar - Inspection Applicability: Model PA-24, PA-24-250, PA-24-260 S/N 24-1 through 24-5047. Model PA-24-400 S/N 26-2 through 26-148. Requirement: Piper SL 787 (FAA AD 77-08-01 refers) Compliance: At 1000 hours TTIS and thereafter at intervals not exceeding 100 hours TIS until modified per Piper kit no. 760 914 Effective Date: 9 May 1977 DCA/PA24/119A Landing Gear Extension System – Inspection and Bungee Renewal Applicability: Model PA-24, PA-24-250 and PA-24-260 aircraft, all S/N Model PA- 24-400 aircraft, all S/N except S/N 1 Note: This AD revised to correct the Piper SB reference with no change to the AD requirement. Requirement: To prevent possible landing gear collapse after manual extension, accomplish the following: 1. Inspect the landing gear per the instructions in Piper SL No. 782A. Replace components which exceed the manufacturer specified wear limits. 2. Inspect the main landing gear bungee cords for frayed protective covering, breaks and soft areas. Replace cords found with defects. Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 8 of 12 CAA of NZ (FAA AD 77-13-21 refers) Compliance: 1. For aircraft with 1000 hours or more TIS: Within the next 100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 1000 hours TIS. For aircraft with less than 1000 hours TIS: By 1100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 1000 hours TIS. 2. For aircraft with 1000 hours or more TIS: Within the next 100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 500 hours TIS or 12 months whichever occurs sooner. For aircraft with less than 1000 hours TIS: By 1100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 500 hours TIS or 12 months whichever occurs sooner. Replace bungee cords at intervals not to exceed 500 hours TIS or 3 years whichever occurs sooner. Effective Date: 29 September 2011 DCA/PA24/120 Aileron Nose Rib - Inspection Applicability: Model PA-24 and PA-24-250 S/N 24-1 and up, model PA-24-260 S/N 24-3642, 24- 4000 and up, model PA-24-400 S/N 26-1 and up not incorporating Piper kit P/N 763893 Requirement: Inspect per Piper SL 850. (FAA AD 79-20-10 refers) Compliance: Within the next 50 hours TIS and thereafter at intervals not exceeding 100 hours TIS Effective Date: 9 November 1979 DCA/PA24/121 Cancelled - Purpose fulfilled DCA/PA24/122 Spar Cap - Inspection Applicability: Model PA-24-180, -250 and -260 S/N 24-1 and up Requirement: To preclude possible loss of structural integrity, inspect per Piper SB 751. Rectify or replace defective parts before further flight. Compliance: Within the next 100 hours TIS Effective Date: 15 July 1983 DCA/PA24/123A Parking Brake Operation - Placard Applicability: Model PA-24, PA-24-250, and PA-24-260 S/N 24-1 through 24-5034, PA-24-400 S/N 26-1 through 26-148. Requirement: To prevent aircraft controllability problems while involved in ground operation because of improper brake operation, accomplish the following: Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 9 of 12 CAA of NZ Install one of the following in a central location on the pilot’s instrument panel in full view of the pilot: (1) A Piper P/N 81090-02 placard; or (2) A Piper P/N 683-107 placard. Note: The above referenced placards both contain the following wording: WARNING NO BRAKING WILL OCCUR IF AIRCRAFT BRAKES ARE APPLIED WHILE PARKING BRAKE HANDLE IS PULLED AND HELD (FAA AD 85-02-05R1 refers) Compliance: Required within 100 hours time-in-service after 22 March 1985 or prior to the next flight after the effective date of this AD, whichever occurs later, unless already accomplished. Effective Date: DCA/PA24/123 - 22 March 1985 DCA/PA24/123A - 19 December 1997 DCA/PA24/124 Heated Alternate Air Induction System - Modification Applicability: Model PA-24-260 (fuel injected), S/N 24-3642, 24-4000 through 24-4255, 24-4257 through 24-4782, and 24-4784 through 24-4803 Requirement: To prevent inadvertent engine stoppage while flying in weather conditions conducive to induction system icing, install the manually operated heated alternate air induction system kit per Piper SB 861. (FAA AD 91-21-09 refers) Compliance: Within the next 100 hours TIS unless already accomplished Effective Date: 22 February 1991 DCA/PA24/125C Main Landing Gear Sidebrace Stud – Inspection and Replacement Applicability Models PA24, PA24-250, PA24-260 and PA24-400 aircraft, all S/N. Note 1: This AD revised to remove note 3. There is no terminating action to the repetitive inspections mandated by this AD for affected PA-24 aircraft. The larger 5/8” sidebrace stud P/N 78717-02 and bushing cannot be installed in the existing sidebrace bracket assembly. And bracket assembly P/N 95643-06, 95643-07, 95643- 08 or 95643-09 cannot be installed on affected PA-24 aircraft. Requirement: To prevent main landing gear (MLG) collapse due to possible main gear sidebrace stud cracks which if not detected and corrected could result in loss of aircraft control during landing, accomplish the following: Remove both the left and right main gear sidebrace studs from the aircraft per the instructions in the landing gear section of the aircraft MM. Inspect both the main gear sidebrace stud for cracks using Type I (fluorescent) liquid penetrant or magnetic particle inspection methods. Figure 1 of this AD depicts the area where the sidebrace stud is to be inspected. Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 10 of 12 CAA of NZ For any main gear sidebrace stud not found cracked, before to further flight reinstall the stud per the instructions in the Landing Gear section of the applicable MM, and reinspect and replace (as necessary) per this AD. For any main gear sidebrace stud found cracked, before to further flight replace the cracked stud with a serviceable part per the instructions in the Landing Gear section of the applicable MM, and reinspect and replace (as necessary) per this AD. Note 2: Models PA24 and PA24-250 aircraft were fitted with main gear sidebrace studs P/N 20829-00 at production. Models PA24-260 and PA24-400 aircraft were fitted with main gear sidebrace studs P/N 22512-00 at production. (FAA AD 97-01-01R1 refers) Compliance: Within the next 100 hours TIS unless previously accomplished and thereafter at intervals not to exceed 1000 hours TIS. Effective Date: DCA/PA24/125A - 14 March 1997 DCA/PA24/125B - 29 September 2011 DCA/PA24/125C - 27 October 2011 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 11 of 12 CAA of NZ DCA/PA24/126 Induction Air Filters – Removal from Service Applicability: The following models and S/Ns that are equipped with Purolator air filter P/N 638873, Model CA161PL, or Piper P/N 460-632 (PS60007-2); PA-24-180 and PA-24-250 S/N 24-103 through 24-3687 PA-24-260 S/N 24-3642, and 24-4000 through 24-5028 Requirement: To prevent pieces of a damaged induction air filter from being ingested into the engine, which could result in reduced or loss of engine power, accomplish the following:- Replace, per the maintenance manual, any Purolator/Facet induction air filter, Purolator P/N 638873, Model No. CA161PL, Piper P/N 460-632 (PS60007-2), that meets the following conditions: • Was manufactured anytime from January 1997 through September 1998; and • Is identified with a ¼ inch high (white) ink stamp "FACET - 638873", and may include "FAA-PMA". Note: Piper SB 1022, and Purolator SB 090298.01 provide information relating to this AD, including procedures on how to identify the affected air filters. (FAA AD 99-05-09 refers) Compliance: Within next 25 hours TIS. Effective Date: 25 March 1999 Aeroplanes Piper PA-24 Series (Comanche) Issued 28 June 2018 Page 12 of 12 CAA of NZ From 1 October 2012 the Civil Aviation Authority of New Zealand (CAA) will no longer rewrite the text of State of Design ADs. Applicable State of Design ADs will be listed below and can be obtained directly from the National Airworthiness Authority (NAA) web site. The link to the NAA web site is available on the CAA web site at http://www.caa.govt.nz/airworthiness-directives/states-of-design/ 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. 2012-17-06 Stabilator Horn Assembly – Inspection and Replacement Effective Date: 22 October 2012 68-05-01 Exhaust Mufflers – Inspection Effective Date: 31 March 1968 2015-24-05 Fuel System – Inspection Effective Date: 12 January 2016