(B) Width (in.) - (C) Height (in.) -
(xii) Weight (Dry) Lb. (Note any unusual inclusions or exclusions).
(xiii) Center of Gravity.
(A) Relative to specific longitudinal reference in inches.
(B) Relative to engine center line in inches.
(xiv) Propeller or Power Shaft. Type and size.
Crankshaft Dampers. Number, order, location, and type.
(xvi) Note List. Listing of note numbers applicable to model group, listed under data column for that group.
(xvii) Legend. Explanation of symbols.
(A) "- _" indicates "same as preceding model."
(B) "_" indicates "does not apply."
(xviii) Certification Basis.
(A) FAR (CAR), Special Conditions, and Exemptions, as appropriate, effectivity covering type certification of engine.
(B) Engine model and date of type certification application.
(C) Date of type certification.
(D) Date specific models canceled.
(xvix) Production basis. Production certificate number or other production means.
(6) Basic Data. (Notes Section). Variations are so numerous in engine type, and in conditions relative to similar types, that close uniformity in the use of notes for all engines appears impractical. Uniformity for uniformity's sake might well impair the accurate presentation of technical information. The first six notes are assigned to common conditions or parameters and for uniformity should be used solely for these subjects. The remaining notes and contents may be selected according to the data Chap 2 10 Par 7
to be presented. The following examples of engine data sheet notes are presented accordingly.
(i) Common Note Headings Peculiar to All Engines.
NOTE 1. Engine ratings are based on calibrated stand performance, under the conditions specified by the engine type certificate holder. For example:
- Static sea level standard day conditions (59 °F and
29.92" Hg) •
- No customer bleed, no duct losses, no external power extraction.
- Exhaust configuration (as specified by the engine type certificate holder).
NOTE 2. Maximum permissible temperatures or temperature limits.
Maximum Cylinder Head Cylinder Oil inlet Recip. Base (Type Thermocouple) °F. (°C.) °F. (°C.)
Turbine exhaust gas or turbine inlet Temperatures measured by - thermocouples at Models Models Takeoff (5 minutes) °F. (°C.) °F. (°C.)
Maximum continuous °F. (°C.) °F. (°C.)
Maximum transient for °F. (°C.) °F. (°C.)
accel. ( ) sec.
Maximum transient for °F. (°C.) °F. (°C.)
starting ( ) sec.
Other temperature °F. (°C.) °F. (°C.)
limits as applicable NOTE 3. Shaft (or Fan) speed limits.
NOTE 4. Shaft torque limits (or EPR thrust limits).
NOTE 5. Fuel and Oil pressure limits.
Chap 2 Par 11
NOTE 6. Accessory drive or mounting provisions.
Rotatn Speed MaxTorg O'ng ACC. Engine Models Facing Ratio (in.-lb.) Mom.
Drive RJ 123 RJC123 Dr Pad to Eng Cont. St. in-lb Strtr * cC \:1 (#) Strtr ** cC (# ) Gen ** C (#) Alt * * cC (#) VacPmp * * C etc. etc. etc.
(# ) FuelPmp etc. etc. etc.
(#) Tach etc. etc.
(# ) PrpGOv etc.
(#) "*" - Standard "#" - Drive source "**" - Optional "P" - Pneumatic "C" - Clockwise "GP" - Gas Producer rotor "CC" - Counterclockwise "PT" - Power Turbine rotor "-" means "does not apply" "--" means "same as previous modeli NOTE 7. Model description - similarities, differences, and special characteristics.
RJ123 - Basic Model - Brief Description.
RJC123 - Similar to RJ123 Except List major differences.
NOTE 8. The following accessories are provided as part of the engine (or are optional) and comply with the aircraft installation requirements for (make/model) aircraft.
Compliance findings need to be determined, or delegated, by the appropriate FAA Aircraft (or Engine) Certification Office (ACO/ECO).
(ії) Uncommon Notes Peculiar to Reciprocating Engines.
NOTE 9. Thrust - tractor or pusher.
Chap 2 12 Par 7
NOTE 10. Horizontal or vertical installation - helicopter information.
NOTE 11. Center of gravity tabulation (if not shown in body of data sheet).
NOTE 12. Vibration damper provision limitations.
NOTE 13. Manufacturers bulletins and instructions covering matters of special interest.
NOTE 14. Special ratings.
NOTE 15. Military models note.
NOTE 16. Special equipment.
NOTE 17. Approved propellers - models.
NOTE 18. Other applicable notes.
(iii) Uncommon Notes Peculiar to All Turbine Engines.
NOTE 9. Rotational velocities at standard and overspeed, alternate ratings, etc.
NOTE 10. Bleed air extraction.
NOTE 11. Alternate fuel information.
NOTE 12. Fuel or oil additives.
NOTE 13. Anti-icing, de-icing equipment, requirements.
NOTE 14. Power ratings for non-standard conditions.
NOTE 15. Rotor disk integrity and rotor blade containment (where special provisions apply).
NOTE 16. Operational torques, power settings, and other special limits.
NOTE 17. Engine mount system.
NOTE 18. Power boost, injection.
NOTE 19. Other applicable notes for special equipment, or relating to specific or unique engine installation requirements, such as inlet foreign object protection, lightning protection, HERF protection, thrust reversers, Chap 2 Par 7 13
criticality level of software for engine controls, and other electrical/electronic systems, emissions standards, extended range operations, etc.
(iv) Notes Peculiar to Turboprop Engines.
NOTE 20. Approved Propellers - Models (when available).
NOTE 21. Engine - Controls.
NOTE 22. Equivalent shaft horsepower - Jet thrust, 1b./2.5 + SHP.
(V) Other Notes Peculiar to Special Conditions Assigned.
TCDS (For Obsolete Engines). (Reference FAR Sections 21.15, 21.21, 21.31, and 33.5): _When an engine model has become obsolete; e.g., if the type certificate holder does not intend to manufacture it, or any of its component parts; approval under the type certificate may be canceled upon request. After cancellation, it is no longer necessary for the [former] type certificate holder to maintain up-to-date type design and type certificate data. The TCDS of the engine will be revised to reflect the change in certification status and, when all models listed under one type certificate have been canceled, the data sheet will be transferred to a combined listing of obsolete engines. The operation of obsolete engines still in service is eligible to be continued under the status of the approval in it to end ly the toma, type to hen effect at the time the certificate was canceled. If reinstatement of the type certificate is desired by the former type certificate holder for the purpose of resuming active engine production, a new application for type certificate, to be based on current FAR, is needed.
8. DATA REQUIRED. (Reference FAR Sections 21.15, 21.21, 21.29,
21.31, 21.41, and FAR Part 33).
FAA Form 8110-12. "Application for Type Certificate" (OMB 04-R0078) is the form referred to in Section 21.15(a).
should be submitted to the FAA Aircraft Certification Office (ACO), of the region in which the applicant is geographically located.
b. Preliminary Data. Certain technical data are needed to make the initial evaluation of conformity with the specific design requirements and the establishment of detailed qualification testing to be prescribed, in accordance with FAR Part 33.
data most useful for these purposes include a preliminary type design description, technical design data, which are required under Sections 21.21(b) and 21.29(a) (2), together with other useful background information. To facilitate this evaluation of Chap 2 14 far 7
engine design features, the preliminary data may be submitted along with the application for a type certificate. The following preliminary data are suggested:
(1) A preliminary model description, specification, or equivalent, containing at least sufficient information to permit the establishment of the basis for engine certification.
(2) Drawings showing external views and cross-sections of selected components, reflecting unique and typical detailed features.
(3) A review of significant development history, emphasizing the extent of development experience with the engine, with particular emphasis on unique or complex features, or their combinations not used up to now in aircraft engines.
Proposals for substantiating compliance with the requirements of FAR Part 33 for U.S. applicants' engines and Section 21.29 for import engines, by means of technical analyses or testing. Test proposals are desired appreciably before the proposed starting date of the test, in sufficient detail to serve as a guide for testing, whereupon they may be incorporated in the lype Inspection Authorization (TIA). Reference [Handbook] FAA Order 8110.4 for more detailed information on TIAs, including test article pre- and post-test conformity inspection and schedule requirements.
c. Final Type Design and Type Certificate Data for U.S.
Manufactured Engines. Acceptable type design and type certificated data, test reports, and computations data, required under Section 21.21(b), cover the engine design that completed the prescribed qualification testing. Acceptable data are described as follows:
(1) Type Design Data. (Reference Section 21.31).
(i) Engine Model Description. The final model description should provide data and information that is all officially verified, to replace the preliminary model description.
(Reference Appendixes 1 and 2).
(ii) Engine Parts Drawings, Material, and Process Specifications. Acceptable data will show the configuration of the type design that successfully complied with the required tests and inspections. A numerically arranged drawing list that shows the latest design change identification is recommended to accompany the drawings. Drawings should be sufficiently detailed to identify and completely describe the design features; supply information on dimensions, materials, and processes necessary to define the structural strength of the product; part and serial number locations; and any other data necessary to allow, by Chap 2 Par 8 15
comparison, the determination of the airworthiness of later products of the same type.
(2) Type Certificate Data. (Reference Sections 21.21(b),
21.41, and Part 33).
(i) Test Reports and Computations. Test reports and computations to substantiate compliance with the applicable requirements of Part 33. A test report should cover, but not be limited, to the following:
(A) Test equipment. A complete description with photographs, or reference to a previous report in which the same equipment was used; the manner of engine mounting in the test equipment; and the calibration status of instruments.
(B) Test procedure. The name of the test, part of the test sequence, or the FAR; the chronological log of testing; delays in tests and their causes; stops for minor corrections and servicing engine; and time required for starts.
(C) Test data. Graphs showing variations in rest dhe enduran data; conth operating conditions during the endurance test; log sheets calibration curves for calibration test data; method used in correcting test data to standard atmospheric conditions (Reference Sections 33.45 and 33.85(a)) and substantiation of any correction factors used.
NOTE: All data should be legible, accurate, and when plotted, use scales which are easily read and interpolated.
(D) of parts before assembly and after disassembly, prior to cleaning for dimensional inspection. Describe test results with beforeand after-test tables of dimensions of major parts of the engine that are likely to incur wear, or change of dimension.
photographs and descriptions of excessively worn parts. Discuss any unusual wear, burning, overheating, part failure or impending failure, and occurrence of heavy deposits on parts. Indicate the condition of mating, sealing, and friction surfaces; e.g., airo11 seals, each engine case, valve faces, piston rings, oil seals, curvic couplings, etc. Indicate the results of visual, X-ray, magnetic, fluorescent particle, or other inspections of major (E) Laboratory analyses. Analyses of the types and grades of fuel, lubricants, and hydraulic fluids used in the test. Identify the specification to which the fluids conform.
Describe the condition of the lubricant and hydraulic fluids after the test.
Chap 2 16 Par 8
(ii) Instruction Manual (s). (Reference Section The manual (s) cover information for installing, operating, and continued airworthiness of the engine. Installation and operating manual data that have been substantiated, FAA approved, and are specifically required for engine approval in aircraft, should be so indicated. For convenience, such data may appropriately be contained in a separate portion of the manual(s).
Type Design and Type Certificate Data for Import Engines.
Certain technical data are required under Section 21.29(a) for import engines when a U.S. type certificate has been applied for.
The requirements for such import engines are based on reciprocal airworthiness agreements between the U.S. and the country of manufacture involved, as indicated by Section 21.29. The airworthiness bases, and the exact extent and type of technical data to be supplied the FAA, for showing compliance with the FAA requirements, may vary in accordance with specific agreements between the Administrator and the Airworthiness Authority of the country of manufacture; but includes the usual application and preliminary data already covered, and usually the following:
(1) Type Design Data. Engine model description as discussed above in paragraph c(1) of this section.
(2) Type Certificate Data.
(i) Certification compliance table.
(ii) Engine manuals, in the English language, described above in paragraph c(2) (ii) of this section.
Additionally, if not included in the manuals, engine installation and general arrangement drawings are to be submitted.
(iii) Statement of compliance by the Airworthiness Authority of the country of manufacture, with the applicable airworthiness requirements.
Hate nes or iport engine, imediately before "To be considered eligible for installation on U.S. registered aircraft, each engine to be exported to the United States shall be accompanied by a certificate of airworthiness for export, or certifying statement endorsed by the exporting civil airworthiness authority which contains the following language:
(a) This engine conforms to its United States type design (Type Certificate No.-----) and is in a condition for safe operation.
Chap 2 Par 17
(b) This engine has been subjected, by the manufacturer, to a final operational check and is in a proper state of airworthiness. Reference FAR Section 21.500 which provides for the airworthiness acceptance of aircraft engines manufactured outside the U.S., for which a U.S.
type certificate has been issued.
Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of civil Aircrait, Engines, Propellers, and Related Products Imported into the United States.
9. INSTALLATION CONSIDERATIONS OF ENGINES. (FAR Section 21.21).
General. An engine type certificate may be obtained upon completion of examination of the type design, completing all engine tests, and applying all applicable provisions of FAR Part 33 and Section 21.21. while it is desirable that the engine applicant cater to all possible aircraft installation characteristics, this is not a requirement for engine certification. This does not obviate the desirability of intimately interrelated installation requirements being introduced into an engine certification program when the aircraft characteristics are known in sufficient time to do so.
b. New Engine. New engines being developed concurrently with new aircraft may be expected to originally meet the applicable aircraft installation requirements. Otherwise, interrelated installation requirements may be met by either engine design changes, or installation features. Such considerations are often specifically related to the engine-aircraft or engine-propeller combination under consideration and require evaluation either apart from or, at times, after engine certification may have been accomplished. . While the aircraft applicant is responsible for showing compliance with the aircraft installation requirements, there are occasions when the engine applicant's substantiation data may be utilized for this purpose. It is recommended, therefore, that at the initial engine type board meeting, the engine applicant establish the extent to which he plans to provide substantiation data for the installation. It then becomes desirable that such data be submitted with the engine type certificate data, for later coordination among FAA ACOs.
c. Engine Changes. The foregoing procedure is for new engine models. Refer to the next section for procedures in handling certain design changes to engines that may require changes to the installation. When components of the installation are provided as Chap 2 18 Par 8
part of the engine type certification design (e.g., pumps, reversers, coolers, etc.), the engine TCDS should reflect this.
10. ENGINE CHANGES WHICH AFFECT INSTALLATIONS. (FAR Sections
21.19 and 21.97).
This section discusses changes in design to certificated engine components whereby the engine operating limits, engine installation details, or aircraft performance characteristics may possibly be significantly altered and require reinvestigation of the aircraft approval. Such malor endine chanqes are to be landled in accordance with Sections 21.19 and 21.97 for engine approval.
Extensive changes may result in engine model redesignation, and major changes of a lesser but significant degree may require revisions to the limitation affecting data in TCDSs, operating manuals and/or engine manuals. It is cautioned that seemingly slight changes in engine components may, at times, adversely affect aircraft performance and installation limitations. Some changes that have resulted in certain problems for various engines involve engine fuel metering, surge bleed, and variable geometry control components.
engines and for general use, that are considered to possibly affect aircraft installations, the degree of compatibility with existing aircraft installation is first established. This involves coordination by the FAA and the engine manufacturer with the responsible aircraft type certificate holder. Suggested procedures are discussed in paragraph 10c below.
(2) If engine interchangeability is adversely affected for existing installations, it is desirable that either the engine or aircraft manufacturer initiate remedial modifications, rather than establishing and qualifying a new model of engine. Proposed engine type design changes should be thoroughly reviewed prior to approval, to ensure they are compatible with the aircraft installations in which the engine is being used, as all engines of the same model designation should be interchangeable in the aircraft.
for effects on engine interchangeability in existing aircraft, it is suggested that the engine manufacturer coordinate the changes To assist the FAA in evaluating engine type design changes with affected aircraft manufacturers. It is further suggested that the engine manufacturer establish a written procedure whereby they will notify the FAA engine controlling office of the results, after the completed coordination of each affected engine change.
Accomplishment of these steps should reasonably assure thorough evaluation of each design and expedite its approval on the aircraft. If any doubt remains concerning the compatibility Chap 2 Par 9 19
status of an engine change, its status should be resolved between the FAA engine and aircraft controlling offices.
11. OFFICIAL ENGINE TESTS. (FAR Section 21.33 and Part 33).
Official engine certification tests are to be conducted, in accordance with the authorization directed to the applicant.
The tests required for engine certification are as prescribed by pertinent sections of Part 33. The authorization may be a letter or a TIA, in accordance with FAA Order 8120.2A, 'Production Approval and Surveillance Procedures," and "TC Handbook," FAA Order 110.'. Reference these documents and other applicable local FAA Orders, such as NE CD 8110.2A, ¿Confirmation of Satisfactory Conformity Inspection, and NE CD 8110.1A, Evaluation and Approval Responsibilities for Manufacturer's Material and/or Process Specifications Specified in the Type Design, when requesting participation of representatives from other than the cognizant FAA engineering office.
b. Witnessing of tests by FAA representatives, as prescribed in Section 21.33, is accomplished, at least, for the engine calibration, endurance, and operation tests; and the teardown inspection following these tests. FAA representatives may also such specialized tests as vibration measurement, detonation, rotor integrity, rotor blade containment, icing, and ingestion tests. The engine manufacturer's designated engineering representative (DER) should witness all certification testing and subsequent parts improvement tests conducted by the manufacturer, for the purpose of authenticating the tests and the results. FAA, or delegated designees, must have made a determination prior to testing that engines, parts, and/or components to be tested conform to the appropriate design data.
relating to official tests: The test authorization identifies the following details
(1) The engine to be tested and the specific tests, with the schedule of runs and test limits to be employed.
(2) The test equipment, instrumentation (type and accuracy), and facilities (rigs, cells) to be utilized.
(3) The test witnessing desired.
(4) Inspections to be conducted, covering both the engine and the test equipment, as appropriate.
d. For all official FAA tests, test rigs and cells should be inspected for configuration; and data acquisition systems instrumentation for location and calibration.
Chap 2 20 Par 10
12. APPROVAL OF ENGINE PARTS AND MATERIALS. (FAR Sections 21.19,
21.113, 21.303, and FAR Part 33).
General. All engine parts and materials which have met the design and test requirements of Part 33, for engine type certification, are eligible to be approved parts.
b. Changes by Type Certificate Holder. Changes to the type design of the engine may be made by approval granted to the type certificate holder, when he meets the requirements prescribed under Part 33, and Part 21, Subpart D, discussed in paragraph 13 below.
As indicated for major changes, the parts should undergo testing similar to the original substantiation, unless alternate acceptable substantiation is provided. Minor changes do not usually require testing for their substantiation. Experience has indicated that the cumulative effects of both major and minor especially when groups of new changes are incorporated in production engines, may have significant adverse effects on safety or durability.
(2) Therefore, retesting of engines with all recent design changes appears desirable, when incorporating a design change or group of design changes, in order to assess these eiiects; and may include development, endurance, vibration, anc fatigue testing. Submittal of description data is needed for FAA approval, or for DER approval when appropriately authorized.
c. Replacement or Modification Parts Produced by Other Than the Engine Type Certificate Holder. Design approvals of these parts may be granted as either identical parts to those in the engine type design, or as modifications to the type design.
Acceptable means of compliance with Section 21.303 for processing these replacement parts are contained in AC 21.303-1.
(1) When the applicant desires to substantiate parts embodying extensive new design, complete type design data is required, as prescribed in Section 21.19, in the manner applicable to new applications for type certificates.
(2) When the applicant desires to substantiate parts embodying major type design changes, not great enough to require a new application for type certificate, a supplemental type certificate, as prescribed in Section 21.113, may be issued.
13. PROCESSING CHANGES IN TYPE DESIGN. (FAR Part 21, Subparts D and E).
a. Minor Changes. Section 21.95 applies to the approval of minor changes in type design. such changes normally require only a drawing comparison to substantiate their airworthiness. Typical Chap 2 Par 12 21