SCHEDULE OF AIRWORTHINESS DIRECTIVES

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 1 of 6 AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 35/70 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. Beechcraft 35 (Bonanza) Series Aeroplanes AD/BEECH 35/70 Amdt 1 Airspeed Restriction 1/2003 Applicability: Models 35, A35, B35, and 35R aircraft, all serial numbers. Requirement: 1. Fabricate a placard that restricts the never exceed speed (Vne) to no more than 144 miles per hour (MPH) or 125 knots (KTS) indicated airspeed (IAS), and install this placard on the instrument panel within the pilot’s clear view. The placard should utilise letters at least 2.54mm (0.10-inch) in height and contain the following words: “Never exceed speed, Vne, 144 MPH (125 KTS) IAS” 2. Mark a red line on the airspeed indicator glass at 144 MPH (125 kts) and mark a white slippage mark on the outside surface of the airspeed indicator between the glass and the case. 3. Insert a copy of this Directive into the Limitations Section of the aircraft flight manual. 4. Visually inspect the empennage, aft fuselage, and ruddervator control system for damage in accordance with the procedures in paragraphs (5)(a) through (5)(f) of the Accomplishment Instructions section of Raytheon Service Bulletin No. SB 27-3358, Issued February 2000, and use a digital ultrasonic skin tester or equivalent skin tester or direct methods that utilise callipers and micrometers. a. Part of this is an inspection of the aft fuselage skin for wrinkles or cracks. Specific skin thicknesses are presented in Figures 1 and 2 of this Directive. The skin thickness measurement is not repetitive. b. The inspection and setting of the travels on the elevator and elevator trim tabs are not repetitive. c. Repair or replace any damaged parts and set the elevator controls, rudder and tab system controls, cable tensions, and rigging. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 2 of 6 Beechcraft 35 (Bonanza) Series Aeroplanes AD/BEECH 35/70 Amdt 1 (continued) 5. Verify the accuracy of the aircraft basic weight and balance information and correct any discrepancies, in accordance with the following procedures: a. Weight and Balance Accuracy Method No. 1: (i) Review existing weight and balance documentation to assure completeness and accuracy of the documentation from the most recent approved weighing or from factory delivery to date of compliance with this Directive. (ii) Compare the actual configuration of the aircraft to the configuration described in the weight and balance documentation. (iii) If equipment additions or deletions are not reflected in the documentation or if modifications affecting the location of the centre of gravity (eg. paint or structural repairs) are not documented, determine the accuracy of the aircraft weight and balance data in accordance with Method No. 2. b. Weight and Balance Information Accuracy Method No. 2: (i) Determine the basic empty weight and centre of gravity (CG) of the empty aircraft using the weighing instructions in the Weight and Balance section of the aircraft flight manual/pilot’s operating handbook (AFM/POH). (ii) Record the results in the aircraft records, and use these new values as the basis for computing the weight and CG information as specified in the Weight and Balance section of the AFM/POH. 6. Inspect the aft fuselage, ruddervator, and related systems for acceptable condition in accordance with the procedures in the Accomplishment Instructions section of Raytheon Service Bulletin No. SB 27-3358. Accomplish the rebalancing in accordance with Section 3A(8) of the service bulletin and use the procedure in Section 3 of Beech Shop Manual 35-590096B19 (or subsequent revision). a. Repair or replace any parts found unacceptable as specified in the Requirement document. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 3 of 6 Beechcraft 35 (Bonanza) Series Aeroplanes AD/BEECH 35/70 Amdt 1 (continued) b. Rebalance the ruddervators to the new specifications that reduce the upper limit from 19.8 to 18 inch-pounds (tail heavy). This is not necessary initially if it can be positively verified in the logbook that the ruddervators meet the limits specified in the Requirement document: (i) To positively show this, the entry must indicate that the ruddervator is within the specified limits and list the details of the balancing. (ii) This must include the balancing methods used and the amount of weights and washers used. c. Discontinue the placard and operating limitations of Requirements 1, 2, and 3 of this Directive. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 4 of 6 Beechcraft 35 (Bonanza) Series Aeroplanes AD/BEECH 35/70 Amdt 1 (continued) Skin Thickness - Raytheon Aircraft (Beech) Models 35, 35R, A35, and B35 INDEX NUMBER PART NUMBER SKIN THICKNESS SKIN TOLERANCE LOCATION EFFECTIVITY 1 35-410006-26 0.016 See ANSI AA H35.2(M) 2 35-410006-20 0.025 See ANSI AA H35.2(M) 3 35-410008-2 0.016 See ANSI AA FS 151-FS272 D-1 through D-15