Airworthiness Directive Schedule Aeroplanes Cessna 501 Series

Note 1: Stator disks stamped with ''CHG AI'' or ''CHG B'' or a higher change letter are not affected by this AD. Requirement: To prevent jamming of the wheel/tyre assembly which could result in loss of directional control or braking performance upon landing, accomplish the following: 1. Review the aircraft records or inspect the stator disks on the brake assembly to determine if ''CHG AI'' or ''CHG B'' or a higher change letter is impression-stamped on each disk per Goodrich SB 2-1528-32-2 for aircraft fitted with BFGoodrich brake assembly P/N 2-1528-6) and Goodrich SB 2-1530-32-2 for aircraft fitted with BFGoodrich brake assembly P/N 2-1530-4 both at revision 5, dated 19 February 2003 as applicable. If both disks are stamped with ''CHG AI'' or ''CHG B'' or a higher change letter, no further AD action is required. 2. For stator disks not stamped with ''CHG AI'' or ''CHG B'' or a higher change letter accomplish a detailed inspection for cracked or broken stator disks per Goodrich Service Bulletin 2-1528-32-2 or SB 2-1530-32-2, as applicable. If no cracked or broken stator disks are found, reassemble the brake assembly and if the piston housing is impression-stamped with the letters ''SB,'' obliterate the existing markings on the piston housing by stamping ''XX'' over the letters ''SB.'' If any cracked or broken stator disks are found, replace the brake assembly with a new or serviceable brake assembly per SB 2-1528-32-2 or SB 2-1530-32-2 as applicable before further flight. 3. Replace the brake assembly with a new or serviceable brake assembly per SB 2-1528-32-2 or SB 2-1530-32-2 as applicable, with new or serviceable brake assemblies that contain stator disks stamped with ''CHG AI'' or ''CHG B'' or a higher change letters. 4. An affected BFGoodrich brake assembly shall not be fitted to any aircraft unless it has been inspected in accordance with the requirements of this AD and found free of cracks or broken stator disks. Aeroplanes Cessna 501 Series Issued 24 September 2015 Page 4 of 6 CAA of NZ Note 2: For the purposes of this AD, a detailed inspection is defined as: ''An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.'' Note 3: The replacement of all brake assemblies fitted to the aircraft with new or serviceable brake assemblies that contain stator disks stamped with ''CHG AI'' or ''CHG B'' or a higher change letter terminates the inspections mandated by this AD. Note 4: BFGoodrich SB 2–1528–32–3 original issue, dated 23 March 2000, SB 2–1530–32–3 original issue, dated 23 March 2000, SB 2–1528–32–2 revision 5, dated 19 February 2003 and SB 2–1530–32–2 revision 5, dated 19 February 2003 pertains to the sunject of this AD. (FAA AD 2004-09-05 refers) Compliance: 1. Within the next 50 landings or by 27 August 2010 whichever occurs sooner, unless previously accomplished. 2. For aircraft fitted with thrust reversers: Before the accumulation of 376 total landings on the brake assembly or within the next 50 landings, whichever occurs later, and For aircraft not fitted with thrust reversers: Before the accumulation of 200 total landings on the brake assembly, or within the next 50 landings, whichever occurs later, and Thereafter if paragraph E.(3)(a) or E.(3)(b) in SB 2-1528-32-2 or SB 2-1530-32-2 as applicable, specifies repetitive inspections, repeat the inspections until accomlishment of requirement 3 of this AD. 3. Before the accumulation of 700 total landings since brake assembly installation or within the next 50 landings, whichever occurs later. 4. From 27 May 2010. Effective Date: 27 May 2010 DCA/CESS501/4 Engine and APU Fire Extinguisher Wiring – Inspection and Rework Applicability: Model 501 aircraft listed in Cessna SB500-26-02 revision 1, dated 7 July 2005 including the SB Supplemental Data dated 1 April 2005. Requirement: To prevent the non activation of engine/APU fire extinguishers due to possible incorrect fire extinguishers wiring which could result in an unextinguished fire in the nacelle or APU, accomplish the following: 1. Install identification sleeves on the wires for the positive and negative terminal studs of the engine fire extinguishing bottles per Cessna SB500-26-02 revision 1, dated 7 July 2005. Re-connect the wires to the correct studs, test the connection and re-connect the wires again as applicable until the connection tests correctly. Do all actions in accordance with the instructions Cessna SB500-26-02 revision 1, dated 7 July 2005 including the SB Supplemental Data dated 1 April 2005. 2. A fire extinguishing bottle may not be fitted to any aircraft unless the positive and negative terminal studs have identification sleeves fitted on the wires per the requirements of this AD. Aeroplanes Cessna 501 Series Issued 24 September 2015 Page 5 of 6 CAA of NZ (FAA AD 2007-11-17 refers) Compliance: 1. Within the next 100 hours TIS or by 27 August 2010 whichever occurs sooner unless previously accomplished. 2. From 27 May 2010. Effective Date: 27 May 2010 Aeroplanes Cessna 501 Series Issued 24 September 2015 Page 6 of 6 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.html 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. 2013-09-11 Air Conditioning Motor - Inspection Effective Date: 5 July 2013