Type Acceptance Report

of G positions, the airplane is safety controllable and a pilot can perform all the manoeuvres and operations necessary to effect a safe landing following any probable electric trim tab runaway which might be reasonably expected in service allowing for appropriate time delay after pilot recognition. (b) In addition to the requirements of 23.629, it must be shown by analysis or test, or a combination of both, that the airplane is free from flutter, control reversal, and divergence up to V D / MD after the failure, malfunction, or disconnection of any single element in the elevator tabs control system. (iii) Exemptions: FAA Exemption No.4661 – FAR §23.207(c) - Requires the stall warning to begin at a speed at least 5 kt above Vs but not more than 10 kt or 15% above Vs. This is not possible with a high power-to-weight aircraft like the F406. The exemption permitted compliance to be shown at the wings-level power off Vs at forward c.g. and MTOW, plus evaluation of further specific conditions. (iv) Equivalent Level of Safety Findings: FAR 23.1189 (a) Shutoff Means – A firewall shutoff valve was not required provided equivalent safety was achieved by having hydraulic system components on the engine side of the firewall being fireproof and flexible hose assemblies must meet specified fire resistance criteria. (v) Airworthiness Limitations: See Maintenance Manual Chapter 4 – Airworthiness Limitations Type Acceptance Report TAR 96/16 – F406 Rev.1 : 19 January 2016 4 (3) Aircraft Noise and Engine Emission Standards: (i) Environmental Standard: The Model F406 has been certificated for noise in accordance to ICAO Annex 16, Volume1, Chapter 6. (ii) Compliance Listing: Approved Noise Level : 72.0 dB(A) – See TCDS Note 1. (4) Certification Compliance Listing: The following documents were originally supplied in 1986: Cessna Report No. 406-82-066 – Master Compliance Check List – dated 11-9-1984 Cessna Report No. 406-84-017 – Electrical Load Analysis – CAA Cessna Report No. S-406-110 – Model 406 Structures Data Summary DM406-0 Delegation Option Manufacture Flight Test Report Model 406 (FAR 23) DM406-1 Delegation Option Manufacture Flight Test Rpt. Model 406 (SFAR 41) Report No.508 D’Etude - DGAC Mesures de Bruit Avions F 406 [Reims Aviation] Suivant L’Annexe 16 de l’OACI dated Avril 1985 (5) Flight Manual: F406 EASA Approved Pilot’s Operating Handbook Publication D1624-E2R11-13PH – CAA Accepted as AIR 2582 (6) Operating Data for Aircraft: (i) Maintenance Manual: F406 Maintenance Manual – Publication D2536R5-13 F406 Wiring Diagram Manual – Publication D2537-3-13 (ii) Current service Information: Service Bulletins and Service Information Letters (iii) Illustrated Parts Catalogue: F406 IPC – Publication P673-14-12 Note: Reims letter Ref: DM 97905 dated 3 Feb 1997 confirms that Cessna manuals are applicable to the Reims-manufactured Model F406. (Cessna Report No.DM406-0 on FAA Exemption 4661 states “Through a long and involved process of negotiations, the Model F406 is constructed by Reims Aviation in France to type design data developed by Cessna in the United States. Key to this process is utilization of identical type design data for both the Models 406 and F406 airplanes.”) (7) Agreement from manufacturer to supply updates of data in (5), and (6): CAA 2171 from ASI-Aviation Head of Airworthiness Deputy dated 26-08-2015 Publications are available on the website: http://documentation.asi-aviation.fr/ Type Acceptance Report Rev.1 : 19 January 2016 TAR 96/16 – F406 5 5. Additional New Zealand Requirements Compliance with the retrospective airworthiness requirements of NZCAR Part 26 has been assessed as they are a prerequisite for the grant of an airworthiness certificate. Civil Aviation Rules Part 26 Subpart B – Additional Airworthiness Requirements Appendix B – All Aircraft PARA: REQUIREMENT: MEANS OF COMPLIANCE: B.1 Marking of Doors and Emergency Exits To be determined on an individual aircraft basis B.2 Crew Protection Requirements – CAM 8 Appdx. B # .35 Not Applicable – Agricultural Aircraft only Appendix C – Air Transport Aeroplanes – More than 9 Pax PARA: REQUIREMENT: MEANS OF COMPLIANCE: C.1 Doors and Exits Complies – See Fax from Reims dated 26 June 1997 C.2.1 Additional Emergency Exits – FAR 23.807(b) @ 10.5.93 The F406 has exits on both sides of the fuselage. C.2.2 Emergency Exit Evacuation Equipment – Descent means N/A – Overwing exit less than 2m from the ground C.2.3 Emergency Exit Interior Marking – Size/self-illuminating Complies – See Fax from Reims dated 26 June 1997 C.3.1 Landing Gear Aural Warning – Automatic Flap Linking Fitted as Standard – See Flight Manual Page 7-25 Compliance with the following additional NZ operating requirements has been reviewed and were found to be covered by either the original certification requirements or the basic build standard of the aircraft, except as noted: Civil Aviation Rules Part 91 Subpart F – Instrument and Equipment Requirements PARA: REQUIREMENT: MEANS OF COMPLIANCE: 91.505 Seating and Restraints – Safety belt/Shoulder Harness 5-point Restraint system fitted as standard – See AFM 7-30 91.507 Pax Information Signs – Smoking, safety belts fastened N/A – No separation between crew and pax compartments 91.509 Min. VFR (1) ASI (2) Machmeter (3) Altimeter (4) Magnetic Compass (5) Fuel Contents (6) Engine RPM (7) Oil Pressure FAR §23.1303(a) N/A – No mach limitations FAR §23.1303(b) FAR §23.1303(c FAR §23.1305(a) FAR §23.1305(e) FAR §23.1305(b) (8) Coolant Temp (9) Oil Temperature (10) Manifold Pressure (11) Cylinder Head Temp. (12) Flap Position (13) U/c Position (14) Ammeter/Voltmeter N/A – Air cooled engine FAR §23.1305(c) FAR §23.1305(h) FAR §23.1305(f) FAR §23.699(a)(2) FAR §23.729(e) FAR §23.1351 (d) 91.511 Night (1)Turn and Slip (2) Position Lights Fitted as std – See AFM/POH FAR §23.1385 (3) Anti-collision Lights (4) Instrument Lighting FAR §23.1401 FAR §23.1381 91.513 VFR Communication Equipment Operating Rule – Compliance to be determined by Operator 91.517 IFR Instruments and Equipment Operating Rule – Compliance to be determined by Operator 91.519 IFR Communication and Navigation Equipment Operating Rule – Compliance to be determined by Operator 91.523 Emergency Equipment: (a) More Than 9 pax – First Aid Kits per Table 7 – Fire Extinguishers per Table 8 (b) More than 20 pax – Axe readily accessible to crew (c) More than 61 pax – Portable Megaphones per Table 9 Operating Rule – Compliance to be determined Operating Rule – Compliance to be determined Not Applicable – Less than 20 passenger seats Not Applicable – Less than 61 passenger seats 91.529 ELT - TSO C126 406 MHz after 22/11/2007 To be determined on an individual aircraft basis 91.531 Oxygen Indicators – Volume/Pressure/Delivery Operating Rule – Compliance to be determined by Operator 91.533 Supplemental Oxygen for non-Pressurised Aircraft >30 min above FL100 – Supplemental for crew, 10% Pax – Therapeutic for 3% of Pax Above FL100 – Supplemental for all Crew, Pax – Therapeutic for 1% of Pax – 120 litre PBE for each crew member Maximum Operating Altitude Limit in Flight Manual (with oxygen equipment) is 30,000 ft Operating Rule – Compliance to be determined as applicable [ An optional oxygen system is a 114.9 cu.ft. bottle in the nose compartment. The plumbed outlets for the pilot and copilot are located inside the stowage compartment under the outboard armrests, while outlets for passengers are located overhead of each seat position. The oxygen control, and pressure gage are located on the instrument panel. ] 91.541 SSR Transponder and Altitude Reporting Equipment Operating Rule – Compliance to be determined by Operator 91.543 Altitude Alerting Device - Turbojet or Turbofan Not Applicable – Not turbo jet or turbofan powered 91.545 Assigned Altitude Indicator Operating Rule – Compliance to be determined by Operator A.15 ELT Installation Requirements To be determined on an individual aircraft basis Type Acceptance Report TAR 96/16 – F406 Rev.1 : 19 January 2016 6 Civil Aviation Rules Part 135 Subpart F – Instrument and Equipment Requirements PARA: REQUIREMENT: MEANS OF COMPLIANCE: 135.355 Seating and Restraints – Shoulder harness flight-crew seats FAR §23.785 135.357 Additional Instruments (Powerplant and Propeller) FAR §23.1305 135.359 Night Flight Landing light, Pax compartment Operating Rule – Compliance to be determined by Operator 135.361 IFR Operations Speed, Alt, spare bulbs/fuses Operating Rule – Compliance to be determined by Operator 135.363 Emergency Equipment (Part 91.523 (a) and (b)) To be determined on an individual aircraft basis 135.367 Cockpit Voice Recorder N/A – Only for 2-crew helicopters with more than 10 pax 135.369 Flight Data Recorder Not Applicable – Part 135 requires less than 10 pax seats 135.371 Additional Attitude Indicator Not Applicable – Not turbo jet or turbofan powered NOTES: 1. A Design Rule reference in the Means of Compliance column indicates the Design Rule was exactly equivalent to the CAR requirement, and compliance is achieved for the basic aircraft type design by certification against the original Design Rule. 2. The CAR Compliance Tables above were correct at the time of issue of the Type Acceptance Report. The Rules may have changed since that date and should be checked individually. 3. Some means of compliance above are specific to a particular model/configuration. Compliance with Part 91/119 operating requirements should be checked in each case, particularly oxygen system capacity and emergency equipment. Attachments The following documents form attachments to this report: Photographs First-of-Type example s/n F406-0012 ZK-CII Three-view drawing Reims Cessna Model F406 Copy of EASA Type Certificate Data Sheet Number A.109 Sign off …………………………………….. ……………………………............... David Gill Checked – Peter Gill Team Leader Airworthiness Team Leader Design Appendix 1 List of Type Accepted Variants: Model: Applicant: CAA Work Request: Date Granted: F406 Aeromotive Limited 97/21B/8 3 July 1997