Appendix 2 APPENDIX 2. RECIPROCATING ENGINE MODEL DESCRIPTION PURPOSE. This appendix outlines the reciprocating engine model descriptive information that should be submitted in order to establish those features of the engine that are involved in the certification and safe operation of the engine.
DISCUSSION. The applicant should submit, where applicable, the following information, plus any additional information which, in the applicant's opinion, is essential to the certification anc safe operation of the engine.
a. Applicant's name.
b. Engine model, cylinder arrangement, number of cylinders, valve arrangement, cycle used, and type of cooling, etc.
Performance ratings as defined in FAR Part 1 (See Table 1 of this appendix).
d. Performance charts consistent with the ratings.
e. Design structural loading envelope for mounting attachments and maximum allowable loads.
zero "g" conditions. Maximum time the engine may be operated under negative and Maximum permissible temperature limits and cooling criteria for engine components and accessories.
(1) Type and location of thermocouples used for cooling test.
(2) Description of temperature sensing provisions.
h. Maximum carburetor air inlet duct attachment loads.
(1) Shear load.
(2) Loads normal to mounting surfaces.
(3) Overhang moment.
i. Lubrication system.
(1) Oil grade, type, and specification.
(2) Oil consumption rate (normal and maximum).
(3) Oil inlet pressure limits.
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(4) Oil system vent pressure limits.
(5) Oil inlet and scavenge temperature limits.
(6) Inlet oil flow rate.
(7) Usable oil capacity, if oil tank is part of engine.
(8) Maximum heat rejection to oil, including turbosuperchargers.
(9) Oil pump outlet pressure limits for normal operation and idle, if oil tank is not part of engine.
(10) Oil filter provisions and requirements.
(11) Oil pressure limits for propeller governing engine oil passages.
j. Fuel system.
(1) Grade, type, and specification.
(2) Fuel inlet pressure limits.
(3) Inlet fuel flow rate (maximum).
(4) Method of providing for carburetor icing precautions.
(5) Fuel filter provisions and requirements.
k. Maximum permissible exhaust attachment loads.
(1) Shear loads.
(2) Loads normal to mounting surfaces.
(3) Overhang moment.
1. Accessory attachments. For each aircraft accessory drive, give the following information:
(1) Type of drive and mounting arrangement.
(2) Direction of rotation.
(3) Static torque (maximum limit).
(4) Continuous torque (limit).
(5) Drive speed ratio with crankshaft.
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(6) Maximum overhang moment.
(7) Vibration limits (if applicable).
m • Output shaft.
(1) Maximum steady state allowable torque, or power limits, of the output shaft.
(2) Maximum allowable transient power output torque.
(3) Maximum bending load limits on the output shaft.
(4) The type and dimensions of the output shaft, direction of rotation, speed ratio with crankshaft, and nominal speed.
n• Describe all instrumentation in detail. Describe provisions for connecting permanent and optional instrumentation, including provisions for trend or condition monitoring equipment.
›. Give model designation, setting numbers, or other ertinent identifying information relative to the engine accessories or controls and special equipment, such as:
(1) Carburetor, injectors, and subsystems.
(2) Ignition system.
(3) Spark plugs.
(4) Safety devices.
(5) Other accessories or components to be furnished as part of, or with the engine.
(6) Optional accessories available with the engine for mounting on, or for use with the engine.
p• Performance data should be presented in the form of suitable curves in order to portray the relationship of the various parameters of a minimum engine of the model, including the effects of varying ambient temperature and altitude. The maximum, or limiting air intake temperature(s), should be specified together, with all other engine performance limitations.
(1) For engines incorporating manual mixture controls, performance charts should include recommended data on rich and lean operation.
(2) For enqines to be used with variable pitch propellers and in helicopters, performance charts should include manirold Par 2
Appendix 2 pressure variations, starting from several representative full throttle points, in the engine operating speed range.
(3) For all engines, include altitude performance charts.
q. The applicant should include, in the engine description, an installation drawing of the engine showing all the dimensions and details necessary for proper installation of the engine in an aircraft, including mounting, mounting provisions, and accessory and component installation/removal envelopes.
I • Radiated electromagnetic interference (EMI/HERF) protection requirements of the engine.
s. Lightning protection requirements of the engine.
t. Any additional information to adequately describe the operational and installation limitations of the engine.
U • Engine requirements for any externally supplied electricity.
v. Weight:
(1) Dry weight of complete engine, with all required equipment and no residual fuel or oil.
(2) Weights of optional external equipment and accessories.
(3) Estimated weight or residual fuel and lube oil.
(4) Center of gravity location of engine (dry).
W. Mass moment of inertia of rotating system - frictional horsepower.
(1) Estimated effective mass moment of inertia of those engine rotating components involved in starting.
(2) Estimated mass moment of inertia of main engine rotating component assemblies.
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Appendix 2 TABLE 1. PERFORMANCE RATINGS AT STANDARD SEA LEVEL CONDITIONS RATINGS Shaft Speed Cylinder Manifold Horse- I.p.m. Head & Base Pressure power (max) Temperature Limit (min- in. Hg.
rated) (max) Takeoff Wet Takeoff DrY Maximum Continuous Idle Par 2 5 (and 6)
Appendix 3 APPENDIX 3. INDEX OF INCORPORATED GUIDANCE MATERIAL AND REFERENCES Incorporated Guidance Material and References Related FAR AC 20.18A 'Qualification Testing of Turbojet 33.87, 33.97 Engine Thrust Reversers, 3/16/66 AC 20.26 "Turbine and Compressor Rotors Type 33.27 Certification Substantiation Procedures, 7/22/64 AC 20.73 "Aircraft Ice Protection," 4/21/71 33.68 AC 20-135 ¿Powerplant Installation and 33.68 Propulsion System Component Fire Protection Test Methods, Standards and Criteria, 2/6/90 AC 21.1B "Production Certificates," 5/10/76 33.7 AC 21.6A 'Production Under Type Certificate 33.7 Only,i 7/1/82 AC 21.23 "Airworthiness Certification of 21.29 Civil Aircraft, Engines, Propellers, and Related Products Imported to the United States,i 7/7/87 AC 21.303-1A ¿'Certification Procedures for 21.303, Products and Parts, 8/10/72 21.19, 21.113 AC 23.909-1 "Installation of Turbochargers in 33.51 Small Airplanes With Reciprocating Engines," 2/3/86 AC 33.1B Turbine Engine Foreign Object 33.77 Ingestion and Rotor Blade Containment Type Certification Procedures, 4/22/70 AC 33.3 'Turbine and Compressor Rotors Type 33.14, Certification Substantiation 33.27, 33.88 Procedures,i 9/9/68 AC 33.4 'Design Considerations Concerning 33.15, the Use of Titanium in Aircraft 33.17, 33.19 Turbine Engines," 7/28/83 AC 33.5 'Turbine Engine Rotor Blade 33.19, 33.94 Containment/Durabilit, 11/7/89 1
Appendix 3 APPENDIX 3. INDEX OF INCORPORATED GUIDANCE MATERIAL AND REFERENCES Incorporated Guidance Material and References Related FAR AC 33.47-1 ¿Detonation Testing in 33.47 Reciprocating Aircraft Engines,i 6/27/88 AC 33.65-1 "Surge and Stall Characteristics of 33.65, 33.73 Aircraft Turbine Engines, 12/6/85 AC 43.17 "Methods, Techniques, and Practices 43.3, 45.13 Acceptable to the Administrator Governing the Installation, Removal, or Change of Identification Data and Identification Plates," 9/5/79 AC 91.33A 'Use of Alternate Grades of 33.7 Aviation Gasoline for Grade 80/87 and Use of Automotive Gasoline," 7/84 FAA Order "Type Certification," 6/85 21.21;
(Handbook) 21.29, 21.41 8110.4 FAA Order Production Approval and 21.33 8120.2A Surveillance Procedures, Rev.
3/12/87 FAA Order NE "Evaluation and Approval 21.33 CD 8110.1A Responsibilities for Manufacturer's Material and/or Process Specifications Specified in the Type Design," 5/28/86 FAA Order NE 'Confirmation of Satisfactory 21.33 CD 8110.2A Conformity Inspection, 8/7/86 FAA Policy "Turbine and Compressor Rotor 33.27 мето Integrity Substantiation," 2/9/59 FAA 'Standard Fire Test Apparatus and 33.17 Powerplant Procedure (for Flexible Hose Engineering Assemblies), Rev. 3/78 Report No. 3A FAA Report ¿Ignition and Propagation Rates for 33.17 FAA-RD-75- Flames in a Fuel Mist, 10/75 155 2
Appendix 3 APPENDIX 3. INDEX OF INCORPORATED GUIDANCE MATERIAL AND REFERENCES Incorporated Guidance Material and References Related FAR FAA Report Titanium Combustion in Turbine 33.17 FAA-RD-79-51 Engines,i 7/79 JAR-E, "Titanium Fires" 33.17 Section 2, Paragraph ACJ E 530 (c) {RICA DO- {33.28} 160B} {RTCA DO-178} {33.28} SAE AIR 1377A Fire Test Equipment for Flexible 33.17 Hose and Tube Assemblies," 1/80 SAE ARP 1507 Helicopter Engine/Airframe 33.5 Interface Document and Checklisti 9/85 SAE ARP 926A "Fault/Failure Analysis Procedure," 33.75 Rev. 11/15/79 SAE AS 1055B Fire Testing of Flexible Hose, 33.17 Tube Assemblies, Coils, Fittings, and Similar System Components,i Rev. 3/1/78 {SAE {33.28} Committee Report No.
AE4EL} SAE Paper No '¿Ignition of Aircraft Fluids on 33.17 690436 High Temperature Engine Surfaces,i William T. Westfield, 4/21/69 *** NOTE: {33.28} is pending.
3 (and 4)
Appendix 4 APPENDIX 4. GLOSSARY OF ACRONYMS AND ABBREVIATIONS Advisory Circular ACO Aircraft Certification Office AIR Aerospace Information Report (SAE) Auxiliary Power Unit Aerospace Recommended Practice (SAE) Aerospace Standard (SAE) Before Top Center British Thermal Unit Civil Aviation Regulations (predecessor of FAR) CRes Corrosion Resistant DE Engine front face inlet equivalent diameter DER Designated Engineering Representative Nacelle inlet lip stagnation point equivalent diameter Nacelle inlet throat equivalent diameter Engine Certification Office Engine Electronic Control Electromagnetic Compatibility Electromagnetic Interference FAA Federal Aviation Administration FAR Federal Aviation Regulations "ft.," "'" Feet (measurement) Gravitational constant HERF High Energy Radiated Fields hr. Hour (time) 1
Appendix 4 APPENDIX 4. GLOSSARY OF ACRONYMS AND ABBREVIATIONS HSI Hot Surface Ignition "in.," "''" Inch (measurement) in. Hg Inches of Mercury JAR-E Joint Airworthiness Requirements-Engines (European) JP Jet Propellant (turbine) fuel lbs. Pounds (force or mass) LCF Low Cycle Fatigue max. Maximum min. Minimum o'ng. mom. Overhang moment °c Degrees Celsius OEI One-Engine-Inoperative Degrees Fahrenheit
p.s.i./psi Pounds per Square Inch
r.p.m./rpm Revolutions Per Minute S.L. Sea Level SAE Society of Automotive Engineers SHP Shaft Horse Power TC Type Certificate TCDS Type Certificate Data Sheet TIA Type Inspection Authorization *** 2 *S.U. G.P. 0.: 1993-343-120:85955