Type Acceptance Report TAR 19/21B/27 – Piper PA-36 Pawnee Brave

The PA-36 was first announced in 1972 as a new version of the PA-25 Pawnee with a 285 hp Continental Tiara 6-285 flat-six engine. The aircraft had a new wing with removable leading edges, improved ventilation and heating system, and a larger standard hopper of 30 cubic feet. An optional 38 cu.ft. hopper was also available. The FAA determined that the airframe had changed so much that it required a new type certificate, and Piper therefore gave it a new Model number PA-36. In 1974 a new version was introduced with the 300 hp Lycoming IO-540 engine. The new model was called the PA-36 Pawnee Brave 300 while the original aircraft was redesignated the PA-36 Pawnee Brave 285. In 1977 the Brave 300 became the standard model and another more powerful model was introduced, the PA-36 Brave 375 with the 375 hp Lycoming IO-720 flat-eight engine. The sole PA-36-300 Pawnee Brave in New Zealand was registered ZK-EIA in May 1977, while the first of ten PA-36-375 was registered ZL-EIG in June 1978. The Piper PA-36 Series is also approved by the FAA in the Restricted category under type certificate number A10SO. However in New Zealand the PA-36 Series would operate in the agricultural role under Part 137 using the Overload Weight provisions of Appendix B. Type Acceptance Report Rev.0 : 30 June 2020 TAR 19/21B/27 – Piper PA-36 5 4. NZCAR §21.43 Data Requirements The type data requirements of NZCAR Part 21B Para §21.43 have been satisfied by supply of the following documents, or were already held by the CAA: (1) State-of-Design Type certificate: FAA Type Certificate Number A9SO (Normal Category) FAA Type Certificate Data Sheet no. A9SO at Revision 10 dated August 1, 2006 – Model PA-36-285 approved May 31, 1972 – Model PA-36-300 approved November 22, 1974 – Model PA-36-375 approved October 4, 1977 (2) Airworthiness design requirements: (i) Airworthiness Design Standards: The certification basis of the PA-36 Series in the Normal Category under A9SO is FAR Part 23, effective February 1, 1965, including Amendments 23-1 through 23-6 dated August 1, 1967. This is an acceptable certification basis in accordance with NZCAR Part 21B Paragraph §21.41 and Advisory Circular 21-1A, because FAR Part 23 is the basic standard for Normal Category Airplanes called up under Part 21 Appendix C. There are no non-compliances and no additional special conditions have been prescribed by the Director under §21.23. (ii) Special Conditions: Nil (iii) Equivalent Level of Safety Findings: Nil (iv) Airworthiness Limitations: See TCDS Note 8 for wing spar life limits. (3) Aircraft Noise and Engine Emission Standards: Not Applicable (4) Certification Compliance Listing: Report FT-64: Normal Category Certification, Flight Test Program – PA-36-285 Report FT-64 Section II: Substantiation of the Lycoming IO-540-K1A5 Engine Report FT-82 Part II: Piper Model PA-36-300 Restricted Category Certification Report VB-226 Structural Substantiation Model PA-36 (Sections 1-10) Section VI – Flap Loads; Section VII – Control System Loads; Section VIII – Ground and Landing Gear Loads; Appendix A – Lycoming IO-540-K1A5 Report VB-346 PA-36 Electrical Substantiation (Sections 1, 2 & 3) Report VB-346 Section IV: Powerplant Substantiation Data IO-540-K1A5 Engine Report VB-413 PA-36 Wing Fatigue Test Procedure Report VB-450 PA-36 Propulsion & Systems Substantiation, Restricted Category Report VB-451 Appendix A: Structural Considerations – Lycoming IO-540-K1A5 Report 2112/VB-877 Structural Loads & Substantiation Data PA-36-375 Type Acceptance Report TAR 19/21B/27 – Piper PA-36 Rev.0 : 30 June 2020 6 Report 2111/FT-119: Restricted Category Flight Test Report Report 2110/FT-117: Normal Category Flight Test Report Report 2032: Airplane Flight Manual (Normal Category) Model PA-36-300 Report 2114/VB-884: Normal Category Airplane Flight Manual (PA-36-375) Report VB-227 Section II – Fuselage Static Test PA-36-285 Report No. 2019 – Model PA-36 – Seat and Shoulder Harness Re-Test for the Australian Requirement (Re-numbering of Report VB-583) Report No. 1993 – Model PA-36 – Compliance Check List FAR/CAR/Special Conditions (Re-numbering of Report VB-332.) (5) Flight Manual: Pilot’s Operating Manual Piper Pawnee Brave (PA-36-285) – Part Number 761-469 [serial number 36-7360001 thru 36-7460041] – CAA Accepted as AIR 3932. This document includes the FAA-Approved Airplane Flight Manual: Report VB-645 (Normal Category) and VB-646 (Restricted Category) Operating Manual Piper Pawnee Brave (PA-36-285) – Part Number 761 614 [s/n 36-756001 and up] – CAA Accepted as AIR 3923 This document includes the FAA-Approved Airplane Flight Manual: Report VB-682 (Normal Category) and VB-683 (Restricted Category) FAA-Approved Pilot’s Operating Handbook – Piper Pawnee Brave 300 (Restricted Category) Report 2077 – CAA Accepted as AIR 3924 FAA-Approved Pilot’s Operating Handbook – Piper Brave 375 (Restricted Category) – Report 2125 – CAA Accepted as AIR 3925 NOTE: The Restricted Category POH is used in lieu of the Normal Category AFM because the POH includes the AFM and has full performance data. (6) Operating Data for Aircraft: (i) Maintenance Manual: Pawnee Brave – Service Manual – PA-36-285-300-375 – Part No. 761 471 (ii) Current service Information: Service Bulletin and Service Letter Index – Part Number 762 332 (iii) Illustrated Parts Catalogue: PA-36 Pawnee Brave (PA-36-285, PA-36-300, PA-36-375) Parts Catalog Part Number 761 470 (7) Agreement from manufacturer to supply updates of data in (5), and (6): Piper now provides CAA access to publications through the NAA portal (8) Other information: Restricted Category Weight and Balance for Pawnee/Brave (PA-36-285) Normal Category Weight and Balance for Pawnee/Brave (PA-36-285) Type Acceptance Report Rev.0 : 30 June 2020 TAR 19/21B/27 – Piper PA-36 7 5. New Zealand Operational Rule Compliance 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 Appendix. B # .35 Equivalent provisions to CAM 8 Appendix B Section .35 Protection are contained in FAR 23, paragraphs §23.561 Emergency Landing Conditions General; §23.785(h) Seats, berths, litters, safety belts and shoulder harnesses; §23.787 Baggage Compartments; and §23.831 Ventilation; 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 FAR §23.785 91.507 Pax Information Signs – Smoking, safety belts fastened Not Applicable – Less than 10 passenger seats 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(d) 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 fitted FAR §23.1305(c) FAR §23.1305(h) FAR §23.1305(f) FAR §23.699 N/A – Fixed Undercarriage FAR §23.1351 91.511 Night VFR Instruments and Equipment Operational requirement – Compliance as applicable 91.513 VFR Communication Equipment Operational requirement – Compliance as applicable 91.517 IFR Instruments and Equipment Not Applicable – Only approved for VFR Day & Night 91.519 IFR Communication and Navigation Equipment Not Applicable – Only approved for VFR Day & Night 91.523 Emergency Equipment: Not Applicable – Single-seat aircraft 91.529 ELT – TSO C126 406 MHz after 22/11/2007 Operational requirement – Compliance as applicable 91.531 Oxygen Indicators – Volume/Pressure/Delivery Operational requirement – Compliance as applicable 91.533 Oxygen for non-Pressurised Aircraft: Not fitted as standard 91.541 SSR Transponder and Altitude Reporting Equipment Operational requirement – Compliance as applicable 91.543 Altitude Alerting Device – Turbojet or Turbofan Not Applicable – Not turbo jet or turbofan powered 91.545 Assigned Altitude Indicator Not Applicable – Only approved for VFR Day & Night A.15 ELT Installation Requirements To be determined on an individual aircraft basis Civil Aviation Rules Part 137 – Subpart F – Instrument and Equipment PARA: REQUIREMENT: MEANS OF COMPLIANCE: 137.255 Seating and Restraints – Shoulder harness required Shoulder harness with inertial reel fitted as standard. (See AFM Section 7.25 “Pilot Compartment” and IPC Fig.11) 137.257 Additional Instruments – Slip indicator required To be determined on an individual aircraft basis 137.259 Additional equipment See Appendix D compliance statements Appendix B – Overload Weight Determination Design load factor is 3.8 – Maximum Recommended Weight Increase per CAR Part 137 Appendix B Fig.2 is 131% → For MCTOW of 3900 lb, Ag Operating Weight = 5109 lb. NOTES: 1. FAA TCDS A10SO states satisfactory operation in the Restricted Category has been demonstrated for the Models PA-36-285 and PA-36-300 at 4400 lb. [12.8% increase], and for the PA-36-385 at 4800 lb. [23% increase] at sea level under standard day conditions. TCDS Note 3 states “Further weight increases should not be accomplished in the field.” 2. On the basis of this limitation, the CAA would not accept any operation above this weight under Part 137 Appendix B unless the aircraft has demonstrated satisfactory operation at the higher weight as part of some Acceptable Technical Data substantiation program. Type Acceptance Report TAR 19/21B/27 – Piper PA-36 Rev.0 : 30 June 2020 8 Appendix D – Instruments and Equipment Airworthiness Design Standards D.1 Seating and Restraints – Ultimate fwd inertia load of 12g New shoulder harness/inertial reel by Pacific Scientific P/N 0101978-01 fitted and tested to meet the Australian forward load requirement of 25 g. (See Report VB-583) D.3 Hoppers and spray tanks – 12g fwd/1.5 rear/1.0 sideways Satisfactory by Inspection. (Hopper is located within the fuselage steel frame and mounted similarly fore and aft.) D.4 Hopper upper level contents – Indication, density allowance Hopper has viewing port visible in the cockpit D.5 Jettison gear – 80% of maximum load in 5 seconds – simple to operate, single action required Operational Requirement – Compliance as applicable D.6 Markings/Placards – hopper or tank maximum loadings – representative jettison times – pax location, flight limitations To be determined on an individual aircraft basis NOTES: 1. A Design Rule reference in the Means of Compliance column indicates the Design Rule was directly 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 91/137 operating requirements should be checked in each case. Attachments The following documents form attachments to this report: Piper Drawing 39012 – Piper PA-36-300 Three View Piper Drawing 76926 – Piper PA-36-375 Three View Copy of FAA Type Certificate Data Sheet Number A9SO Sign off …………………………………….. ……………………………............... David Gill Checked – Jason Ashworth Team Leader Airworthiness Acting Manager Airworthiness Appendix 1 List of Type Accepted Variants: Model: Applicant: CAA Work Request: Date Granted: PA-36 Series Kairanga Aviation Ltd 19/21B/27 30 June 2020 Type Acceptance Report Rev.0 : 30 June 2020 TAR 19/21B/27 – Piper PA-36 9 Three-view Drawing – Piper PA-36-375