Airworthiness Directive Schedule Aeroplanes Beechcraft 60 and A60 Series (Duke)

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Issued 22 February 2001 Page 1 of 4 CAA of NZ Airworthiness Directive Schedule Aeroplanes Beechcraft 60 and A60 Series (Duke) 22 February 2001 Notes 1. This AD schedule is applicable to Beechcraft 60 and A60 (Duke) aircraft, manufactured under Federal Aviation Administration (FAA) Type Certificate No. A12CE. 2. As there are no aircraft of this type currently registered in New Zealand this AD schedule is not being maintained. The schedule will be reactivated once the New Zealand Civil Aviation Authority receives an application to register an aircraft of this type. At that time the applicable ADs will include all those published by the state of design (FAA). 3. The date above indicates the amendment date of this schedule. 4. New or amended ADs are shown with an asterisk * Contents DCA/B60/1 Airworthiness Directive Compliance at Initial Airworthiness Certificate Issue ................... 2 DCA/B60/2 Pressurisation System Outflow Safety Valves - Replacement .......................................... 2 DCA/B60/3 Severe Icing Conditions - Flight Manual Revision ............................................................. 3 DCA/B60/4 Cabin Heater Wiring - Modification.................................................................................... 4 * DCA/B60/5 Lower Forward Wing Bolts - Inspection............................................................................. 4 Aeroplanes Beechcraft 60 and A60 Series (Duke) Issued 22 February 2001 Page 2 of 4 CAA of NZ DCA/B60/1 Airworthiness Directive Compliance at Initial Airworthiness Certificate Issue Applicability: All Model A60 Requirement: Compliance with the following FAA Airworthiness Directives (as applicable) is required:- 71-05-03 - Known icing conditions 72-22-04 - Elevator movement interference 74-05-05 - Pilot's side window 74-12-02 - Aft facing seats 74-24-03 - Strobe light system 75-06-09 - Elevator inboard hinge support 77-02-04 - Wing tip strobe lights 77-14-08 - Water in fuselage 80-04-07 - Outboard wing panel nuts 83-08-05 - Air conditioner modification 85-22-05 - Nut and bolt replacement 95-22-03 - Flight Manual Revision Note: Each part of this AD (each individual FAA AD) shall be certified in the aircraft log book separately. Compliance: Before issue of New Zealand Certificate of Airworthiness. Repetitive inspections to be accomplished at intervals not exceeding the times specified in the FAA Airworthiness Directives Effective Date: 10 April 1998 DCA/B60/2 Pressurisation System Outflow Safety Valves - Replacement Applicability: The following model 60 series that are equipped with AlliedSignal Aerospace outflow safety valves listed. Model 60 and A60 S/N P-3 through P-246 with Kit No. 60-5024-1S incorporated, Model B60 S/N P-247 through P-307 with Kit No.60-5024-3S incorporated and B60 S/N P-308 through P-596. Valve model 103598-2 S/N 16-808, 39-2434, 45-747, 87-1600, and 116-1238. Valve model 103648-1 S/N 11-4913 through 11-4916, 12-3832, 20-3006, 22-4950, 12-3912, 30-3076, 39-2412, 41-4918, 41-4919, 61-3300, 101-4920, 101-4922 through 101- 4924, 101-4926 through 101-4931, 101-4933, 101-4935, 101-4936, 101-4938, 101- 4940, 101-4941, 121-3683, 121-4942, 129-2904, and 129-2920. Note: The above outflow/safety valves are referenced in AlliedSignal Aerospace SB 103570-21-4012 Rev 1, SB 103648-21-4022 Rev 1, and SB 103598-21-4024, Rev 1. In addition, Beech SB 2484 Rev 1 references the AlliedSignal SBs. Requirement: To prevent outflow/safety valve cracking and consequent failure, which could result in rapid decompression of the aircraft, accomplish the following:- Replace (with a new or serviceable valve) any outflow/safety valve that does not have one of the following: The valve identification plate MOD RECORD stamped "PCA" (Poppet Change Accomplished); or A valve with an inked ATD Quality Assurance "Functional Test (FT)" stamp that is dated June 1992, or later. (FAA AD 97-23-17 refers) Compliance: By 31 August 1998 Effective Date: 10 April 1998 Aeroplanes Beechcraft 60 and A60 Series (Duke) Issued 22 February 2001 Page 3 of 4 CAA of NZ DCA/B60/3 Severe Icing Conditions - Flight Manual Revision Applicability: All model 60 series. Requirement: To minimise the potential hazards associated with operating the aircraft in severe icing conditions (by providing more clearly defined procedures and limitations associated with such conditions), incorporate the following into the Aircraft Flight Manual (AFM):- 1. Limitations Section of the Aircraft Flight Manual “WARNING Severe icing may result from environmental conditions outside of those for which the aircraft is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the aircraft. • During flight, severe icing conditions that exceed those for which the aircraft is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. - Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. - Accumulation of ice on the upper surface of the wing aft of the protected area. - Accumulation of ice on the engine nacelles and propeller spinners farther aft than normally observed. • Since the autopilot, when installed and operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist, or when unusual lateral trim