Airworthiness Directive Schedule Aeroplanes Beechcraft 77 Series (Skipper)

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Issued 28 August 2008 Page 1 of 3 CAA of NZ Airworthiness Directive Schedule Aeroplanes Beechcraft 77 Series (Skipper) 28 August 2008 Notes 1. This AD schedule is applicable to Beechcraft 77 aircraft, manufactured under Federal Aviation Administration (FAA) Type Certificate No. A30CE. 2. The Federal Aviation Administration (FAA) is the National Airworthiness Authority (NAA) responsible for the issue of State of Design Airworthiness Directives (ADs) for these aircraft. State of Design ADs can be obtained directly from the FAA website at: Dynamic Regulatory System (faa.gov) 3. The date above indicates the amendment date of this schedule. 4. New or amended ADs are shown with an asterisk * Contents DCA/B77/1 Shoulder Harness Installation - Inspection ........................................................................ 2 DCA/B77/2 Wing Structure - Fatigue Life Limitation ............................................................................ 2 DCA/B77/3 Rudder Balance Weight Installation - Modification ............................................................ 2 DCA/B77/4 Electrical System - Modification ........................................................................................ 2 DCA/B77/5 NLG Fork - Inspection ....................................................................................................... 2 DCA/B77/6 Cancelled – Purpose Fulfilled ........................................................................................... 3 * DCA/B77/7 Circuit Breaker Toggle Switches – Replacement .............................................................. 3 Aeroplanes Beechcraft 77 Series (Skipper) Issued 28 August 2008 Page 2 of 3 CAA of NZ DCA/B77/1 Shoulder Harness Installation - Inspection Applicability: Model 77 S/N WA-3 through WA-235, WA-237, WA-238, WA-240 through WA-254, WA-256, WA-258, WA-261 through WA-264, WA-266, WA-267 and WA-269. Requirement: Inspect per Beechcraft SI 1173 Rev.1. Rectify incorrect installations as prescribed before further flight. (FAA AD 82-09-03 refers). Compliance: Within next 50 hours TIS. Effective Date: 25 June 1982 DCA/B77/2 Wing Structure - Fatigue Life Limitation Applicability: All model 77 Requirement: Retire basic wing structure at 12,000 hours TTIS. Effective Date: 24 September 1982 DCA/B77/3 Rudder Balance Weight Installation - Modification Applicability: Model 77 S/N WA-1 through WA-312. Requirement: To preclude possibility of rudder control loss, or flutter, modify per Beechcraft SI 1256. (FAA AD 83-23-03 refers). Compliance: Within next 25 hours TIS. Effective Date: 16 December 1983 DCA/B77/4 Electrical System - Modification Applicability: Model 77, S/N WA-1 through WA-312. Requirement: To prevent diode overheating and smoke in cockpit, modify per Beechcraft SB 2201 Rev.1. Compliance: Within next 100 hours TIS. Effective Date: 13 May 1988 DCA/B77/5 NLG Fork - Inspection Applicability: Model 77, S/N WA-1 through WA-312 not fitted with P/N 108-820010-653 fork and axle assembly. Requirement: To prevent failure of the NLG fork accomplish the following: 1. Fluorescent penetrant inspect the fork for cracks per Beechcraft SB 2241 Rev.1. If found cracked, replace the fork and axle assembly with a P/N 108-820010-653 fork and axle assembly before further flight. 2. Visually inspect the NLG fork axle assembly. (FAA AD 91-23-01 refers) Compliance: 1. Fluorescent inspection within next 50 hours TIS and thereafter at intervals not to exceed 500 hours TIS. Aeroplanes Beechcraft 77 Series (Skipper) Issued 28 August 2008 Page 3 of 3 CAA of NZ 2. Between fluorescent inspections, visually inspect at intervals not to exceed 100 hours TIS. Effective Date: 20 December 1991 DCA/B77/6 Cancelled – Purpose Fulfilled * DCA/B77/7 Circuit Breaker Toggle Switches – Replacement Applicability: Model 77 aircraft, S/N WA-1 through to WA-312 Fitted with circuit breaker toggle switches P/N 35-380132-1 through to P/N 35- 380132-53. Requirement: To prevent failure of affected circuit breaker toggle switches due to possible overheating which could result in smoke in the cockpit and the inability to turn the switch off, accomplish the following: 1. Replace all affected circuit breaker toggle switches with an improved circuit breaker toggle switch P/N 35-380132-61 through to 35-380132-113 as applicable, per the instructions in Hawker Beechcraft SB 24-3807, issued May 2007, and Raytheon Aircraft Company SB 24-3735, issued August 2005. 2. An affected circuit breaker shall not be fitted to any aircraft. (FAA AD 2008-13-17 refers) Compliance: 1. By 28 August 2009. 2. From 28 August 2008. Effective Date: 28 August 2008