Airworthiness Directive Schedule Aeroplanes Cessna 310 and 320 Series

Applicability: Model 310 Series S/N 310 G 0001 through 310 P 0166 Model E310 J All S/N’s Model E310 H All S/N’s Model 320 All S/N’s Requirement: Comply with Cessna MESL ME 69-16 & Supl. 1 (FAA AD 69-14-01 refers) Compliance: By 28 February 1970 DCA/CESS310/109 Fuel Line Support - Modification Applicability: Model 310 Series S/N 35000 through 35999 & S/N 39001 through 39299 Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 4 of 9 CAA of NZ Model 310 F S/N 310 F 0001 through 310 F 0156 Requirement: Comply with Cessna MESL ME 69-14 (FAA AD 69-12-03 refers) Compliance: By 30 September 1969 DCA/CESS310/110 Cancelled DCA/CESS310/111 Fuel System - Inspection and Modification Applicability: Model 310 Series All S/N’s Model 320 Series All S/N’s Requirement: Comply with Cessna MESL ME 73-5 and Cessna Service Kit SK 310-90 (FAA AD 73-07-07 refers) Compliance: Within the next 25 hours TIS Effective Date: 31 May 1973 DCA/CESS310/112A Wing Tip Fuel Tank Strobe Light Installations - Inspection and Modification Applicability: All model 310 320 & 340 Series with strobe lights fitted in wing tip fuel tank nose caps, except those with symbolic displays P/N 30-0005, 30-0199-3 and 701133-1; Whelan Engineering Co. Inc. P/N A430, and Grimes Manufacturing Co. (Grimes) P/N 30-0515-5, 30-1172-1, 30-0531-1 and 30-0467-5 strobe lights Requirement: Comply with FAA AD 76-08-02 R2 (Cessna MESL ME 75-16 refers) Compliance: Within the next 100 hours TIS Effective Date: 31 May 1976 DCA/CESS310/113 Flexible Fuel Tanks - Inspection Applicability: All model 310 320 & 340 Series with Goodyear BTC-39 series fuel tanks Requirement: Accomplish the following: 1. Visual inspection per Cessna MESL ME 78-7. 2. Detailed inspection and pressure test per Cessna MESL ME 78-7. (Goodyear SB FT-77-1 and FAA AD 78-05-06 also refer) Compliance: 1. Within the next 25 hours TIS or 30 days whichever is the sooner. 2. Within the next 100 hours TIS or 6 months whichever is the sooner and thereafter at intervals not exceeding 12 months. Effective Date: 21 July 1978 Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 5 of 9 CAA of NZ DCA/CESS310/114 Auxiliary Fuel pump Wiring - Modification Applicability: All model 310 320 & 340 Series which have been modified per Cessna MEB 88-3 Requirement: To overcome unsatisfactory features introduced by Cessna MEB 88-3, modify per Cessna MEB 88-3 Rev. 1. Compliance: Within the next 100 hours TIS unless already accomplished Effective Date: 16 February 1990 DCA/CESS310/115 MLG Inner Bearing - Inspection Applicability: Model 310 Series S/N 310L0001 through 310R1690 Model 320 Series S/N 320E0001 through 320F0045 Model 340 Series S/N 340-0001 through 340A0801 Aircraft fitted with P/N 5141109-1 bearing in each MLG are not affected. Requirement: To prevent jamming of the MLG inner and outer barrels, inspect per Cessna MEB 88- 7. Rectify defective assemblies before further flight (FAA AD 90-02-13 refers) Compliance: At 1300 hours TTIS or within next 300 hours TIS whichever is the later and thereafter at intervals not exceeding 1000 hours TIS Effective Date: 25 May 1990 DCA/CESS310/116 Cancelled – DCA/CESS310/122 now refers DCA/CESS310/117 Rudder Balance Weight Installation-Inspection Applicability: Model 340 S/N 3400001 through 3400555 Model 340A S/N 340A0001 through 340A1521 Requirement: Inspect rudder balance weight rib P/N 0831311-1 per Cessna MESIL ME 82-8. Replace cracked ribs with P/N 5331004-2 before further flight. (FAA AD 82-26-05 refers) Compliance: At intervals not exceeding 100 hours TIS until rib P/N 5331004-2 installed. Effective Date: 9 October 1987 Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 6 of 9 CAA of NZ DCA/CESS310/118 Turbosupercharger Installation - Inspection Applicability: Model T310P S/N T310P0001 through T310P0240 Model T310Q S/N T310Q0001 through T310Q0291 Model 320D S/N 320D0001 through 320D0130 Model 320E 320E0001 through 320E0110 Model 320F 320F0001 through 320F0045 Model 340A S/N 340A0001 through 340A1521 Requirement: To detect incipient failure of turbosuperchargrer turbine housings accomplish the following: Remove engine top cowling and turbosupercharger turbine insulation blanket and visually inspect T.C.M. turbosupercharger assy. P/N632729 (AID P/N 406610) complete turbine housing surface for cracks, bulges and burnt areas. Renew defective parts before further flight. (FAA AD 70-03-04 R1 refers) Compliance: At 425 hours total turbine housing TIS, or within next 25 Hrs. TIS whichever is the latter, and thereafter at intervals not exceeding 100 Hrs. TIS until stainless steel heat shields installed per Cessna MESL ME 72-4. Effective Date: 9 October 1987 DCA/CESS310/119A Crossfeed Fuel Line - Inspection and Modification Applicability: Model 340 & 340A S/N 3400001 through 340A1817 Requirement: To detect and correct fuel line chaffing and leaks in engine firewall area, inspect and modify per Cessna SB MEB 87-7 Rev. 1. Renew chafed fuel lines before further flight. (FAA AD 88-03-07 refers) Compliance: Within next 50 hours TIS Effective Date: DCA/CESS310/119 - 19 February 1988 DCA/CESS310/119A - 8 April 1988 DCA/CESS310/120 Fuel, Oil or Hydraulic Hose - Removal Applicability: All model 310, 320 and 340 series, all S/Ns. Requirement: To prevent fuel, oil or hydraulic systems failure caused by a collapsed hose, check the aircraft maintenance records for any fuel, oil or hydraulic hose, Cessna P/N S51- 10, replaced between March 1995 and 14 March 1997. If any fuel, oil or hydraulic hose, Cessna P/N S51-10, has been replaced between March 1995 and 14 March 1997, accomplish the following:- Before further flight physically check for a diagonal or spiral external reinforcement wrap per Cessna SB MEB96-10. Replace any P/N S51-10 hose that has a diagonal or spiral pattern external reinforcement wrap with a P/N S51-10 hose that has a criss- cross pattern external wrap per SB MEB96-10. (FAA AD 97-01-13 refers) Compliance: Within next 60 hours TIS or 60 days, whichever is the sooner. Effective Date: 14 March 1997 Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 7 of 9 CAA of NZ DCA/CESS310/121 Severe Icing Conditions - Flight Manual Revision Applicability: Models 310R and T310R 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 requirements or autopilot trim warnings are encountered while the aircraft is in icing conditions. - All wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night. This supersedes any relief provided by the Master Minimum Equipment List (MMEL).” 2. Normal Procedures Section of the Aircraft Flight Manual “THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING: - Visible rain at temperatures below 0 degrees Celsius ambient air temperature. - Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air temperature. PROCEDURES FOR EXITINGTHE SEVERE ICING ENVIRONMENT: These procedures are applicable to all flight phases from takeoff to landing. Monitor the ambient air temperature. While severe icing may form at temperatures as cold as -18 degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in the Limitations Section of the AFM for identifying severe icing conditions are observed, accomplish the following: - Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the aircraft has been certificated. - Avoid abrupt and excessive manoeuvring that may exacerbate control difficulties. Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 8 of 9 CAA of NZ - Do not engage the autopilot. - If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. - If an unusual roll response or uncommanded roll control movement is observed, reduce the angle-of-attack. - Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area. - If the flaps are extended, do not retract them until the airframe is clear of ice. - Report these weather conditions to Air Traffic Control.” Note: This may be accomplished by inserting a copy of this AD in the AFM or by incorporating a manufacturer’s flight manual revision that contains the wording per this AD. 3. Flight Crew Notification Operators must ensure that flight crew are aware of the flight manual revision. (FAA AD 98-04-28 refers) Compliance: By 10 May 1998 Effective Date: 10 April 1998 DCA/CESS310/122 Exhaust System – Inspection, Pressure Testing and V Band Clamp Replacement Applicability: All model T310P, T310Q, T310R, 320, 320A, 320B, 320C, 320D, 320E, 320F, 320-1, 335, 340 and 340A. Requirement: To detect and correct cracks and corrosion in the exhaust system, which could result in exhaust system failure and a possible uncontrollable in-flight fire, accomplish FAA AD 2000-01-16. A copy of FAA AD 2000-01-16 will be provided free of charge to aircraft owners and maintenance engineers. A copy may be obtained from: The Library Civil Aviation Authority PO Box 31441 Lower Hutt Compliance: Compliance is required at the times specified within FAA AD 2000-01-16. Effective Date: 24 February 2000 Aeroplanes Cessna 310 and 320 Series Issued 29 September 2016 Page 9 of 9 CAA of NZ The State of Design ADs listed below are available directly from the National Airworthiness Authority (NAA) websites. Links to NAA websites are available on the CAA website at https://www.aviation.govt.nz/aircraft/airworthiness/airworthiness-directives/links-to-state-of- design-airworthiness-directives/ 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. 2014-03-03 Flight Limitations – AFM Amendment, Maintenance Records and Placards Effective Date: 7 April 2014 * 2016-07-24 Cancelled – FAA AD 2016-17-08 refers Effective Date: 12 September 2016 * 2016-17-08 Elevator Trim Push-pull Rod – Inspection Effective Date: 12 September 2016