[Code of Federal Regulations] [Title 14, Volume 2] [Revised as of January 1, 2008] From the U.S. Government Printing Office via GPO Access [CITE: 14CFR60 App C] [Page 175-242] TITLE 14--AERONAUTICS AND SPACE CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) PART 60_FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE--Table of Contents Sec. Appendix C to Part 60--Qualification Performance Standards for Helicopter Full Flight Simulators ________________________________________________________________________ Begin Information This appendix establishes the standards for Helicopter Full Flight Simulator (FFS) evaluation and qualification. The Flight Standards Service, National Simulator Program Manager (NSPM), is responsible for the development, application, and implementation of the standards contained within this appendix. The procedures and criteria specified in this appendix will be used by the NSPM, or a person assigned by the NSPM, when conducting helicopter FFS evaluations. Table of Contents 1. Introduction. 2. Applicability (Sec. 60.1) and (Sec. 60.2). 3. Definitions (Sec. 60.3). 4. Qualification Performance Standards (Sec. 60.4). 5. Quality Management System (Sec. 60.5). 6. Sponsor Qualification Requirements (Sec. 60.7). 7. Additional Responsibilities of the Sponsor (Sec. 60.9). 8. FSTD Use (Sec. 60.11). 9. Simulator Objective Data Requirements (Sec. 60.13). 10. Special Equipment and Personnel Requirements for Qualification of the Simulator (Sec. 60.14). 11. Initial (and Upgrade) Qualification Requirements (Sec. 60.15). 12. Additional Qualifications for a Currently Qualified Simulator (Sec. 60.16). 13. Previously Qualified Simulators (Sec. 60.17). 14. Inspection, Continuing Qualification Evaluation, and Maintenance Requirements (Sec. 60.19). 15. Logging Simulator Discrepancies (Sec. 60.20). 16. Interim Qualification of Simulators for New Helicopter Types or Models (Sec. 60.21). 17. Modifications to Simulators (Sec. 60.23). 18. Operations with Missing, Malfunctioning, or Inoperative Components (Sec. 60.25). 19. Automatic Loss of Qualification and Procedures for Restoration of Qualification (Sec. 60.27). 20. Other Losses of Qualification and Procedures for Restoration of Qualification (Sec. 60.29). 21. Record Keeping and Reporting (Sec. 60.31). 22. Applications, Logbooks, Reports, and Records: Fraud, Falsification, or Incorrect Statements (Sec. 60.33). 23. [Reserved] 24. [Reserved] [[Page 176]] 25. FSTD Qualification on the Basis of a Bilateral Aviation Safety Agreement (BASA) (Sec. 60.37). Attachment 1 to Appendix C to Part 60--General Simulator Requirements. Attachment 2 to Appendix C to Part 60--Simulator Objective Tests. Attachment 3 to Appendix C to Part 60--Simulator Subjective Evaluation. Attachment 4 to Appendix C to Part 60--Sample Documents. End Information ________________________________________________________________________ 1. Introduction ________________________________________________________________________ Begin Information a. This appendix contains background information as well as regulatory and informative material as described later in this section. To assist the reader in determining what areas are required and what areas are permissive, the text in this appendix is divided into two sections: ``QPS Requirements'' and ``Information.'' The QPS Requirements sections contain details regarding compliance with the part 60 rule language. These details are regulatory, but are found only in this appendix. The Information sections contain material that is advisory in nature, and designed to give the user general information about the regulation. b. Related Reading References. (1) 14 CFR part 60. (2) 14 CFR part 61. (3) 14 CFR part 63. (4) 14 CFR part 119. (5) 14 CFR part 121. (6) 14 CFR part 125. (7) 14 CFR part 135. (8) 14 CFR part 141. (9) 14 CFR part 142. (10) AC 120-35B, Line Operational Simulations: Line-Oriented Flight Training, Special Purpose Operational Training, Line Operational Evaluation. (11) AC 120-57A, Surface Movement Guidance and Control System (SMGS). (12) AC 150/5300-13, Airport Design. (13) AC 150/5340-1G, Standards for Airport Markings. (14) AC 150/5340-4C, Installation Details for Runway Centerline Touchdown Zone Lighting Systems. (15) AC 150/5340-19, Taxiway Centerline Lighting System. (16) AC 150/5340-24, Runway and Taxiway Edge Lighting System. (17) AC 150/5345-28D, Precision Approach Path Indicator (PAPI) Systems. (18) AC 150/5390-2B, Heliport Design. (19) International Air Transport Association document, ``Flight Simulator Design and Performance Data Requirements,'' as amended. (20) AC 29-2B, Flight Test Guide for Certification of Transport Category Rotorcraft. (21) AC 27-1A, Flight Test Guide for Certification of Normal Category Rotorcraft. (22) International Civil Aviation Organization (ICAO) Manual of Criteria for the Qualification of Flight Simulators, as amended. (23) Airplane Flight Simulator Evaluation Handbook, Volume I, as amended and Volume II, as amended, The Royal Aeronautical Society, London, UK. (24) FAA Publication FAA-S-8081 series (Practical Test Standards for Airline Transport Pilot Certificate, Type Ratings, Commercial Pilot, and Instrument Ratings). (25) The FAA Aeronautical Information Manual (AIM). An electronic version of the AIM is on the internet at http://www.faa.gov/atpubs. End Information ________________________________________________________________________ 2. Applicability (Sec. Sec. 60.1 & 60.2) ________________________________________________________________________ Begin Information There is no additional regulatory or informational material that applies to Sec. 60.1, Applicability, or to Sec. 60.2, Applicability of sponsor rules to person who are not sponsors and who are engaged in certain unauthorized activities. End Information ________________________________________________________________________ 3. Definitions (Sec. 60.3) ________________________________________________________________________ Begin Information See appendix F for a list of definitions and abbreviations from part 1 and part 60, including the appropriate appendices of part 60. End Information ________________________________________________________________________ 4. Qualification Performance Standards (Sec. 60.4) ________________________________________________________________________ Begin Information There is no additional regulatory or informational material that applies to Sec. 60.4, Qualification Performance Standards. End Information ________________________________________________________________________ 5. Quality Management System (Sec. 60.5) ________________________________________________________________________ [[Page 177]] Begin Information See appendix E for additional regulatory and informational material regarding Quality Management Systems. End Information ________________________________________________________________________ 6. Sponsor Qualification Requirements (Sec. 60.7) ________________________________________________________________________ Begin Information a. The intent of the language in Sec. 60.7(b) is to have a specific FFS, identified by the sponsor, used at least once in an FAA-approved flight training program for the helicopter simulated during the 12-month period described. The identification of the specific FFS may change from one 12-month period to the next 12-month period as long as that sponsor sponsors and uses at least one FFS at least once during the prescribed period. There is no minimum number of hours or minimum FFS periods required. b. The following examples describe acceptable operational practices: (1) Example One. (a) A sponsor is sponsoring a single, specific FFS for its own use, in its own facility or elsewhere--this single FFS forms the basis for the sponsorship. The sponsor uses that FFS at least once in each 12- month period in that sponsor's FAA-approved flight training program for the helicopter simulated. This 12-month period is established according to the following schedule: (i) If the FFS was qualified prior to October 30, 2007 the 12-month period begins on the date of the first continuing qualification evaluation conducted in accordance with Sec. 60.19 after October 30, 2007 and continues for each subsequent 12-month period; (ii) A device qualified on or after October 30, 2007 will be required to undergo an initial or upgrade evaluation in accordance with Sec. 60.15. Once the initial or upgrade evaluation is complete, the first continuing qualification evaluation will be conducted within 6 months. The 12 month continuing qualification evaluation cycle begins on that date and continues for each subsequent 12-month period. (b) There is no minimum number of hours of FFS use required. (c) The identification of the specific FFS may change from one 12- month period to the next 12-month period as long as that sponsor sponsors and uses at least one FFS at least once during the prescribed period. (2) Example Two. (a) A sponsor sponsors an additional number of FFSs, in its facility or elsewhere. Each additionally sponsored FFS must be-- (i) Used by the sponsor in the sponsor's FAA-approved flight training program for the helicopter simulated (as described in Sec. 60.7(d)(1)); OR (ii) Used by another FAA certificate holder in that other certificate holder's FAA-approved flight training program for the helicopter simulated (as described in Sec. 60.7(d)(1)). This 12-month period is established in the same manner as in example one. OR (iii) Provided a statement each year from a qualified pilot (after having flown the helicopter, not the subject FFS or another FFS, during the preceding 12-month period) stating that the subject FFS's performance and handling qualities represent the helicopter (as described in Sec. 60.7(d)(2)). This statement is provided at least once in each 12-month period established in the same manner as in example one. (b) There is no minimum number of hours of FFS use required. (3) Example Three. (a) A sponsor in New York (in this example, a Part 142 certificate holder) establishes ``satellite'' training centers in Chicago and Moscow. (b) The satellite function means that the Chicago and Moscow centers must operate under the New York center's certificate (in accordance with all of the New York center's practices, procedures, and policies; e.g., instructor and/or technician training/checking requirements, record keeping, QMS program). (c) All of the FFSs in the Chicago and Moscow centers could be dry- leased (i.e., the certificate holder does not have and use FAA-approved flight training programs for the FFSs in the Chicago and Moscow centers) because -- (i) Each FFS in the Chicago center and each FFS in the Moscow center is used at least once each 12-month period by another FAA certificate holder in that other certificate holder's FAA-approved flight training program for the helicopter (as described in Sec. 60.7(d)(1)); OR (ii) A statement is obtained from a qualified pilot (having flown the helicopter, not the subject FFS or another FFS during the preceding 12-month period) stating that the performance and handling qualities of each FFS in the Chicago and Moscow centers represents the helicopter (as described in Sec. 60.7(d)(2)). End Information ________________________________________________________________________ 7. Additional Responsibilities of the Sponsor (Sec. 60.9) ________________________________________________________________________ [[Page 178]] Begin Information The phrase ``as soon as practicable'' in Sec. 60.9(a) means without unnecessarily disrupting or delaying beyond a reasonable time the training, evaluation, or experience being conducted in the FSTD. End Information ________________________________________________________________________ 8. FSTD Use (Sec. 60.11) ________________________________________________________________________ Begin Information There is no additional regulatory or informational material that applies to Sec. 60.11, FSTD Use. End Information ________________________________________________________________________ 9. Simulator Objective Data Requirements (Sec. 60.13) ________________________________________________________________________ Begin QPS Requirements a. Flight test data used to validate FFS performance and handling qualities must have been gathered in accordance with a flight test program containing the following: (1) A flight test plan consisting of: (a) The maneuvers and procedures required for aircraft certification and simulation programming and validation. (b) For each maneuver or procedure-- (i) The procedures and control input the flight test pilot and/or engineer used. (ii) The atmospheric and environmental conditions. (iii) The initial flight conditions. (iv) The helicopter configuration, including weight and center of gravity. (v) The data to be gathered. (vi) All other information necessary to recreate the flight test conditions in the FFS. (2) Appropriately qualified flight test personnel. (3) An understanding of the accuracy of the data to be gathered using appropriate alternative data sources, procedures, and instrumentation that is traceable to a recognized standard as described in Attachment 2, Table C2D. (4) Appropriate and sufficient data acquisition equipment or system(s), including appropriate data reduction and analysis methods and techniques, as would be acceptable to the FAA's Aircraft Certification Service. b. The data, regardless of source, must be presented: (1) in a format that supports the FFS validation process; (2) in a manner that is clearly readable and annotated correctly and completely; (3) with resolution sufficient to determine compliance with the tolerances set forth in Attachment 2, Table C2A of this appendix. (4) with any necessary instructions or other details provided, such as yaw damper or throttle position; and (5) without alteration, adjustments, or bias; however the data may be re-scaled, digitized, or otherwise manipulated to fit the desired presentation. c. After completion of any additional flight test, a flight test report must be submitted in support of the validation data. The report must contain sufficient data and rationale to support qualification of the FFS at the level requested. d. As required by Sec. 60.13(f), the sponsor must notify the NSPM when it becomes aware that an addition to, an amendment to, or a revision of data that may relate to FFS performance or handling characteristics is available. The data referred to in this paragraph are those data that are used to validate the performance, handling qualities, or other characteristics of the aircraft, including data related to any relevant changes occurring after the type certificate was issued. This notification must be made within 10 working days. End QPS Requirements ________________________________________________________________________ Begin Information e. The FFS sponsor is encouraged to maintain a liaison with the manufacturer of the aircraft being simulated (or with the holder of the aircraft type certificate for the aircraft being simulated if the manufacturer is no longer in business), and, if appropriate, with the person having supplied the aircraft data package for the FFS in order to facilitate the notification required by Sec. 60.13(f). f. It is the intent of the NSPM that for new aircraft entering service, at a point well in advance of preparation of the Qualification Test Guide (QTG), the sponsor should submit to the NSPM for approval, a descriptive document (a validation data roadmap) containing the plan for acquiring the validation data, including data sources. This document should clearly identify sources of data for all required tests, a description of the validity of these data for a specific engine type and thrust rating configuration, and the revision levels of all avionics affecting the performance or flying qualities of the aircraft. Additionally, this document should provide other information, such as the rationale or explanation for cases where data or data parameters are missing, instances where engineering simulation data are used or where flight test methods require further explanations. It should also provide a brief narrative describing the cause and effect of any deviation [[Page 179]] from data requirements. The aircraft manufacturer may provide this document. g. There is no requirement for any flight test data supplier to submit a flight test plan or program prior to gathering flight test data. However, the NSPM notes that inexperienced data gatherers often provide data that is irrelevant, improperly marked, or lacking adequate justification for selection. Other problems include inadequate information regarding initial conditions or test maneuvers. The NSPM has been forced to refuse these data submissions as validation data for an FFS evaluation. It is for this reason that the NSPM recommends that any data supplier not previously experienced in this area review the data necessary for programming and for validating the performance of the FFS, and discuss the flight test plan anticipated for acquiring such data with the NSPM well in advance of commencing the flight tests. h. In those cases where the objective test results authorize a ``snapshot test'' or a ``series of snapshot test'' results in lieu of a time-history result, Attachment 2 requires the sponsor or other data provider to ensure that a steady state condition exists at the instant of time captured by the ``snapshot.'' This is often verified by showing that a steady state condition existed from some period of time during which the snapshot is taken. The time period most frequently used is 5 seconds prior through 2 seconds following the instant of time captured by the snapshot. This paragraph is primarily addressing the source data and the method by which the data provider ensures that the steady state condition for the snapshot is representative. i. The NSPM will consider, on a case-by-case basis, whether or not to approve supplemental validation data derived from flight data recording systems such as a Quick Access Recorder or Flight Data Recorder. End Information ________________________________________________________________________ 10. Special Equipment and Personnel Requirements for Qualification of the Simulator (Sec. 60.14) ________________________________________________________________________ Begin Information a. In the event that the NSPM determines that special equipment or specifically qualified persons will be required to conduct an evaluation, the NSPM will make every attempt to notify the sponsor at least one (1) week, but in no case less than 72 hours, in advance of the evaluation. Examples of special equipment include spot photometers, flight control measurement devices, and sound analyzers. Examples of specially qualified personnel include individuals specifically qualified to install or use any special equipment when its use is required. b. Examples of a special evaluation include an evaluation conducted after an FFS is moved, at the request of the TPAA, or as a result of comments received from FFS that raise questions regarding the continued qualification or use of the FFS. End Information ________________________________________________________________________ 11. Initial (and Upgrade) Qualification Requirements (Sec. 60.15) ________________________________________________________________________ Begin QPS Requirements a. In order to be qualified at a particular qualification level, the FFS must: (1) Meet the general requirements listed in Attachment 1; (2) Meet the objective testing requirements listed in Attachment 2; and (3) Satisfactorily accomplish the subjective tests listed in Attachment 3. b. The request described in Sec. 60.15(a) must include all of the following: (1) A statement that the FFS meets all of the applicable provisions of this part and all applicable provisions of the QPS. (2) A confirmation that the sponsor will forward to the NSPM the statement described in Sec. 60.15(b) in such time as to be received no later than 5 business days prior to the scheduled evaluation and may be forwarded to the NSPM via traditional or electronic means. (3) A qualification test guide (QTG), acceptable to the NSPM, that includes all of the following: (i) Objective data obtained from aircraft testing or another approved source. (ii) Correlating objective test results obtained from the performance of the FFS as prescribed in the applicable QPS. (iii) The result of FFS subjective tests prescribed in the applicable QPS. (iv) A description of the equipment necessary to perform the evaluation for initial qualification and the continuing qualification evaluations. c. The QTG described in paragraph (a)(3) of this section, must provide the documented proof of compliance with the simulator objective tests in Attachment 2, Table C2A of this appendix. d. The QTG is prepared and submitted by the sponsor, or the sponsor's agent on behalf of the sponsor, to the NSPM for review and approval, and must include, for each objective test: (1) Parameters, tolerances, and flight conditions; (2) Pertinent and complete instructions for the conduct of automatic and manual tests; [[Page 180]] (3) A means of comparing the FFS test results to the objective data; (4) Any other information as necessary, to assist in the evaluation of the test results; (5) Other information appropriate to the qualification level of the FFS. e. The QTG described in paragraphs (a)(3) and (b) of this section, must include the following: (1) A QTG cover page with sponsor and FAA approval signature blocks (see Attachment 4, Figure C4C, for a sample QTG cover page). (2) A continuing qualification evaluation schedule requirements page. This page will be used by the NSPM to establish and record the frequency with which continuing qualification evaluations must be conducted and any subsequent changes that may be determined by the NSPM in accordance with Sec. 60.19. See Attachment 4, Figure C4G, for a sample Continuing Qualification Evaluation Requirements page. (3) An FFS information page that provides the information listed in this paragraph (see Attachment 4, Figure C4B, for a sample FFS information page). For convertible FFSs, the sponsor must submit a separate page for each configuration of the FFS. (a) The sponsor's FFS identification number or code. (b) The helicopter model and series being simulated. (c) The aerodynamic data revision number or reference. (d) The engine model(s) and its data revision number or reference. (e) The flight control data revision number or reference. (f) The flight management system identification and revision level. (g) The FFS model and manufacturer. (h) The date of FFS manufacture. (i) The FFS computer identification. (j) The visual system model and manufacturer, including display type. (k) The motion system type and manufacturer, including degrees of freedom. (4) A Table of Contents. (5) A log of revisions and a list of effective pages. (6) List of all relevant data references. (7) A glossary of terms and symbols used (including sign conventions and units). (8) Statements of compliance and capability (SOCs) with certain requirements. SOCs must provide references to the sources of information that show the capability of the FFS to comply with the requirements. SOCs must also provide a rationale explaining how the referenced material is used, the mathematical equations and parameter values used, and the conclusions reached. Refer to the ``Additional Details'' column in Attachment 1, Table C1A, ``Simulator Standards,'' or in the ``Test Details'' column in Attachment 2, Table C2A, ``Simulator Objective Tests,'' to see when SOCs are required. (9) Recording procedures or equipment required to accomplish the objective tests. (10) The following information for each objective test designated in Attachment 2, Table C2A, as applicable to the qualification level sought: (a) Name of the test. (b) Objective of the test. (c) Initial conditions. (d) Manual test procedures. (e) Automatic test procedures (if applicable). (f) Method for evaluating FFS objective test results. (g) List of all relevant parameters driven or constrained during the automatically conducted test(s). (h) List of all relevant parameters driven or constrained during the manually conducted test(s). (i) Tolerances for relevant parameters. (j) Source of Validation Data (document and page number). (k) Copy of the Validation Data (if located in a separate binder, a cross reference for the identification and page number for pertinent data location must be provided). (l) Simulator Objective Test Results as obtained by the sponsor. Each test result must reflect the date completed and must be clearly labeled as a product of the device being tested. f. A convertible FFS is addressed as a separate FFS for each model and series helicopter to which it will be converted and for the FAA qualification level sought. If a sponsor seeks qualification for two or more models of a helicopter type using a convertible FFS, the sponsor must submit a QTG for each helicopter model, or a supplemented QTG for each helicopter model. The NSPM will conduct evaluations for each helicopter model. g. Form and manner of presentation of objective test results in the QTG: (1) The sponsor's FFS test results must be recorded in a manner acceptable to the NSPM, that allows easy comparison of the FFS test results to the validation data (e.g., use of a multi-channel recorder, line printer, cross plotting, overlays, transparencies). (2) FFS results must be labeled using terminology common to helicopter parameters as opposed to computer software identifications. (3) Validation data documents included in a QTG may be photographically reduced only if such reduction will not alter the graphic scaling or cause difficulties in scale interpretation or resolution. (4) Scaling on graphical presentations must provide the resolution necessary to evaluate the parameters shown in Attachment 2, Table C2A of this appendix. [[Page 181]] (5) Tests involving time histories, data sheets (or transparencies thereof) and FFS test results must be clearly marked with appropriate reference points to ensure an accurate comparison between the FFS and the helicopter with respect to time. Time histories recorded via a line printer are to be clearly identified for cross plotting on the helicopter data. Over-plots must not obscure the reference data. h. The sponsor may elect to complete the QTG objective and subjective tests at the manufacturer's facility or at the sponsor's training facility. If the tests are conducted at the manufacturer's facility, the sponsor must repeat at least one-third of the tests at the sponsor's training facility in order to substantiate FFS performance. The QTG must be clearly annotated to indicate when and where each test was accomplished. Tests conducted at the manufacturer's facility and at the sponsor's training facility must be conducted after the FFS is assembled with systems and sub-systems functional and operating in an interactive manner. The test results must be submitted to the NSPM. i. The sponsor must maintain a copy of the MQTG at the FFS location. j. All FFSs for which the initial qualification is conducted after October 30, 2013 must have an electronic MQTG (eMQTG) including all objective data obtained from helicopter testing, or another approved source (reformatted or digitized), together with correlating objective test results obtained from the performance of the FFS (reformatted or digitized) as prescribed in this appendix. The eMQTG must also contain the general FFS performance or demonstration results (reformatted or digitized) prescribed in this appendix, and a description of the equipment necessary to perform the initial qualification evaluation and the continuing qualification evaluations. The eMQTG must include the original validation data used to validate FFS performance and handling qualities in either the original digitized format from the data supplier or an electronic scan of the original time-history plots that were provided by the data supplier. A copy of the eMQTG must be provided to the NSPM. k. All other FFSs not covered in subparagraph ``j'' must have an electronic copy of the MQTG by October 30, 2013. A copy of the eMQTG must be provided to the NSPM. This may be provided by an electronic scan presented in a Portable Document File (PDF), or similar format acceptable to the NSPM. End QPS Requirements ________________________________________________________________________ Begin Information l. Only those FFSs that are sponsored by a certificate holder as defined in appendix F will be evaluated by the NSPM. However, other FFS evaluations may be conducted on a case-by-case basis as the Administrator deems appropriate, but only in accordance with applicable agreements. m. The NSPM will conduct an evaluation for each configuration, and each FFS must be evaluated as completely as possible. To ensure a thorough and uniform evaluation, each FFS is subjected to the general simulator requirements in Attachment 1, the objective tests listed in Attachment 2, and the subjective tests listed in Attachment 3 of this appendix. The evaluations described herein will include, but not necessarily be limited to the following: (1) Helicopter responses, including longitudinal and lateral- directional control responses (see Attachment 2 of this appendix); (2) Performance in authorized portions of the simulated helicopter's operating envelope, to include tasks evaluated by the NSPM in the areas of surface operations, takeoff, climb, cruise, descent, approach, and landing as well as abnormal and emergency operations (see Attachment 2 of this appendix); (3) Control checks (see Attachment 1 and Attachment 2 of this appendix); (4) Cockpit configuration (see Attachment 1 of this appendix); (5) Pilot, flight engineer, and instructor station functions checks (see Attachment 1 and Attachment 3 of this appendix); (6) Helicopter systems and sub-systems (as appropriate) as compared to the helicopter simulated (see Attachment 1 and Attachment 3 of this appendix); (7) FFS systems and sub-systems, including force cueing (motion), visual, and aural (sound) systems, as appropriate (see Attachment 1 and Attachment 2 of this appendix); and (8) Certain additional requirements, depending upon the qualification level sought, including equipment or circumstances that may become hazardous to the occupants. The sponsor may be subject to Occupational Safety and Health Administration requirements. n. The NSPM administers the objective and subjective tests, which includes an examination of functions. The tests include a qualitative assessment of the FFS by an NSP pilot. The NSP evaluation team leader may assign other qualified personnel to assist in accomplishing the functions examination and/or the objective and subjective tests performed during an evaluation when required. (1) Objective tests provide a basis for measuring and evaluating FFS performance and determining compliance with the requirements of this part. (2) Subjective tests provide a basis for: (a) Evaluating the capability of the FFS to perform over a typical utilization period; [[Page 182]] (b) Determining that the FFS satisfactorily simulates each required task; (c) Verifying correct operation of the FFS controls, instruments, and systems; and (d) Demonstrating compliance with the requirements of this part. o. The tolerances for the test parameters listed in Attachment 2 of this appendix reflect the range of tolerances acceptable to the NSPM for FFS validation and are not to be confused with design tolerances specified for FFS manufacture. In making decisions regarding tests and test results, the NSPM relies on the use of operational and engineering judgment in the application of data (including consideration of the way in which the flight test was flown and way the data was gathered and applied) data presentations, and the applicable tolerances for each test. p. In addition to the scheduled continuing qualification evaluation, each FFS is subject to evaluations conducted by the NSPM at any time without prior notification to the sponsor. Such evaluations would be accomplished in a normal manner (i.e., requiring exclusive use of the FFS for the conduct of objective and subjective tests and an examination of functions) if the FFS is not being used for flight crewmember training, testing, or checking. However, if the FFS were being used, the evaluation would be conducted in a non-exclusive manner. This non- exclusive evaluation will be conducted by the FFS evaluator accompanying the check airman, instructor, Aircrew Program Designee (APD), or FAA inspector aboard the FFS along with the student(s) and observing the operation of the FFS during the training, testing, or checking activities. q. Problems with objective test results are handled as follows: (1) If a problem with an objective test result is detected by the NSP evaluation team during an evaluation, the test may be repeated or the QTG may be amended. (2) If it is determined that the results of an objective test do not support the level requested but do support a lower level, the NSPM may qualify the FFS at that lower level. For example, if a Level D evaluation is requested and the FFS fails to meet sound test tolerances, it could be qualified at Level C. r. After an FFS is successfully evaluated, the NSPM issues a statement of qualification (SOQ) to the sponsor. The NSPM recommends the FFS to the TPAA, who will approve the FFS for use in a flight training program. The SOQ will be issued at the satisfactory conclusion of the initial or continuing qualification. However, it is the sponsor's responsibility to obtain TPAA approval prior to using the FSTD in an FAA-approved flight training program. s. Under normal circumstances, the NSPM establishes a date for the initial or upgrade evaluation within ten (10) working days after determining that a complete QTG is acceptable. Unusual circumstances may warrant establishing an evaluation date before this determination is made. A sponsor may schedule an evaluation date as early as 6 months in advance. However, there may be a delay of 45 days or more in rescheduling and completing the evaluation if the sponsor is unable to meet the scheduled date. See Attachment 4, Figure C4A, Sample Request for Initial, Upgrade, or Reinstatement Evaluation. t. The numbering system used for objective test results in the QTG should closely follow the numbering system set out in Attachment 2, FFS Objective Tests, Table C2A. u. Contact the NSPM or visit the NSPM Web site for additional information regarding the preferred qualifications of pilots used to meet the requirements of Sec. 60.15(d). v. Examples of the exclusions for which the FFS might not have been subjectively tested by the sponsor or the NSPM and for which qualification might not be sought or granted, as described in Sec. 60.15(g)(6), include takeoffs and landing from slopes and pinnacles. End Information ________________________________________________________________________ 12. Additional Qualifications for a Currently Qualified Simulator (Sec. 60.16) There is no additional regulatory or informational material that applies to Sec. 60.16, Additional Qualifications for a Currently Qualified FFS. 13. Previously Qualified Simulators (Sec. 60.17) ________________________________________________________________________ Begin QPS Requirements a. In instances where a sponsor plans to remove a FFS from active status for a period of less than two years, the following procedures apply: (1) The NSPM must be notified in writing and the notification must include an estimate of the period that the FFS will be inactive; (2) Continuing Qualification evaluations will not be scheduled during the inactive period; (3) The NSPM will remove the FFS from the list of qualified FSTDs on a mutually established date not later than the date on which the first missed continuing qualification evaluation would have been scheduled; (4) Before the FFS is restored to qualified status, it must be evaluated by the NSPM. The evaluation content and the time required to accomplish the evaluation is based on the number of continuing qualification evaluations and sponsor-conducted quarterly [[Page 183]] inspections missed during the period of inactivity. (5) The sponsor must notify the NSPM of any changes to the original scheduled time out of service; b. Simulators qualified prior to October 30, 2007, are not required to meet the general simulation requirements, the objective test requirements, and the subjective test requirements of attachments 1, 2, and 3, respectively, of this appendix. c. [Reserved] End QPS Requirements ________________________________________________________________________ Begin Information d. Other certificate holders or persons desiring to use an FFS may contract with FFS sponsors to use FFSs previously qualified at a particular level for a helicopter type and approved for use within an FAA-approved flight training program. Such FFSs are not required to undergo an additional qualification process, except as described in Sec. 60.16. e. Each FFS user must obtain approval from the appropriate TPAA to use any FFS in an FAA-approved flight training program. f. The intent of the requirement listed in Sec. 60.17(b), for each FFS to have a Statement of Qualification within 6 years, is to have the availability of that statement (including the configuration list and the limitations to authorizations) to provide a complete picture of the FFS inventory regulated by the FAA. The issuance of the statement will not require any additional evaluation or require any adjustment to the evaluation basis for the FFS. g. Downgrading of an FFS is a permanent change in qualification level and will necessitate the issuance of a revised Statement of Qualification to reflect the revised qualification level, as appropriate. If a temporary restriction is placed on an FFS because of a missing, malfunctioning, or inoperative component or on-going repairs, the restriction is not a permanent change in qualification level. Instead, the restriction is temporary and is removed when the reason for the restriction has been resolved. h. It is not the intent of the NSPM to discourage the improvement of existing simulation (e.g., the ``updating'' of a visual system to a newer model, or the replacement of the IOS with a more capable unit) by requiring the ``updated'' device to meet the qualification standards current at the time of the update. Depending on the extent of the update, the NSPM may require that the updated device be evaluated and may require that an evaluation include all or a portion of the elements of an initial evaluation. However, the standards against which the device would be evaluated are those that are found in the MQTG for that device. i. The NSPM will determine the evaluation criteria for an FSTD that has been removed from active status. The criteria will be based on the number of continuing qualification evaluations and quarterly inspections missed during the period of inactivity. For example, if the FFS were out of service for a 1 year period, it would be necessary to complete the entire QTG, since all of the quarterly evaluations would have been missed. The NSPM will also consider how the FFS was stored, whether parts were removed from the FFS and whether the FFS was disassembled. j. The FFS will normally be requalified using the FAA-approved MQTG and the criteria that was in effect prior to its removal from qualification. However, inactive periods of 2 years or more will require requalification under the standards in effect and current at the time of requalification. End Information ________________________________________________________________________ 14. Inspection, Continuing Qualification Evaluation, and Maintenance Requirements (Sec. 60.19) ________________________________________________________________________ Begin QPS Requirements a. The sponsor must conduct a minimum of four evenly spaced inspections throughout the year. The objective test sequence and content of each inspection must be developed by the sponsor and must be acceptable to the NSPM. b. The description of the functional preflight inspection must be contained in the sponsor's QMS. c. Record ``functional preflight'' in the FFS discrepancy log book or other acceptable location, including any item found to be missing, malfunctioning, or inoperative. End QPS Requirements ________________________________________________________________________ Begin Information d. The sponsor's test sequence and the content of each quarterly inspection required in Sec. 60.19(a)(1) should include a balance and a mix from the objective test requirement areas listed as follows: (1) Performance. (2) Handling qualities. (3) Motion system (where appropriate). (4) Visual system (where appropriate). (5) Sound system (where appropriate). (6) Other FFS systems. e. If the NSP evaluator plans to accomplish specific tests during a normal continuing qualification evaluation that requires the use of special equipment or technicians, the sponsor will be notified as far in advance of the evaluation as practical; but not less than 72 hours. Examples of such [[Page 184]] tests include latencies, control dynamics, sounds and vibrations, motion, and/or some visual system tests. f. The continuing qualification evaluations, described in Sec. 60.19(b), will normally require 4 hours of FFS time. However, flexibility is necessary to address abnormal situations or situations involving aircraft with additional levels of complexity (e.g., computer controlled aircraft). The sponsor should anticipate that some tests may require additional time. The continuing qualification evaluations will consist of the following: (1) Review of the results of the quarterly inspections conducted by the sponsor since the last scheduled continuing qualification evaluation. (2) A selection of approximately 8 to 15 objective tests from the MQTG that provide an adequate opportunity to evaluate the performance of the FFS. The tests chosen will be performed either automatically or manually and should be able to be conducted within approximately one- third (1/3) of the allotted FFS time. (3) A subjective evaluation of the FFS to perform a representative sampling of the tasks set out in attachment 3 of this appendix. This portion of the evaluation should take approximately two-thirds (2/3) of the allotted FFS time. (4) An examination of the functions of the FFS may include the motion system, visual system, sound system, instructor operating station, and the normal functions and simulated malfunctions of the simulated helicopter systems. This examination is normally accomplished simultaneously with the subjective evaluation requirements. g. The requirement established in Sec. 60.19(b)(4) regarding the frequency of NSPM-conducted continuing qualification evaluations for each FFS is typically 12 months. However, the establishment and satisfactory implementation of an approved QMS for a sponsor will provide a basis for adjusting the frequency of evaluations to exceed 12- month intervals. End Information ________________________________________________________________________ 15. Logging Simulator Discrepancies (Sec. 60.20) There is no additional regulatory or informational material that applies to Sec. 60.20. Logging FFS Discrepancies. 16. Interim Qualification of Simulators for New Helicopter Types or Models (Sec. 60.21) There is no additional regulatory or informational material that applies to Sec. 60.21, Interim Qualification of FFSs for New Helicopter Types or Models. 17. Modifications to Simulators (Sec. 60.23) ________________________________________________________________________ Begin QPS Requirements a. The notification described in Sec. 60.23(c)(2) must include a complete description of the planned modification, with a description of the operational and engineering effect the proposed modification will have on the operation of the FFS and the results that are expected with the modification incorporated. b. Prior to using the modified FFS: (1) All the applicable objective tests completed with the modification incorporated, including any necessary updates to the MQTG (e.g., accomplishment of FSTD Directives) must be acceptable to the NSPM; and (2) The sponsor must provide the NSPM with a statement signed by the MR that the factors listed in Sec. 60.15(b) are addressed by the appropriate personnel as described in that section. End QPS Requirements ________________________________________________________________________ Begin Information FSTD Directives are considered modifications of an FFS. See Attachment 4 for a sample index of effective FSTD Directives. End Information ________________________________________________________________________ 18. Operation with Missing, Malfunctioning, or Inoperative Components (Sec. 60.25) ________________________________________________________________________ Begin Information a. The sponsor's responsibility with respect to Sec. 60.25(a) is satisfied when the sponsor fairly and accurately advises the user of the current status of an FFS, including any missing, malfunctioning, or inoperative (MMI) component(s). b. If the 29th or 30th day of the 30-day period described in Sec. 60.25(b) is on a Saturday, a Sunday, or a holiday, the FAA will extend the deadline until the next business day. c. In accordance with the authorization described in Sec. 60.25(b), the sponsor may develop a discrepancy prioritizing system to accomplish repairs based on the level of impact on the capability of the FFS. Repairs having a larger impact on FFS capability to provide the required training, evaluation, or flight experience will have a higher priority for repair or replacement. End Information ________________________________________________________________________ [[Page 185]] 19. Automatic Loss of Qualification and Procedures for Restoration of Qualification (Sec. 60.27) Begin Information If the sponsor provides a plan for how the FFS will be maintained during its out-of-service period (e.g., periodic exercise of mechanical, hydraulic, and electrical systems; routine replacement of hydraulic fluid; control of the environmental factors in which the FFS is to be maintained) there is a greater likelihood that the NSPM will be able to determine the amount of testing required for requalification. End Information ________________________________________________________________________ 20. Other Losses of Qualification and Procedures for Restoration of Qualification (Sec. 60.29) ________________________________________________________________________ Begin Information If the sponsor provides a plan for how the FFS will be maintained during its out-of-service period (e.g., periodic exercise of mechanical, hydraulic, and electrical systems; routine replacement of hydraulic fluid; control of the environmental factors in which the FFS is to be maintained) there is a greater likelihood that the NSPM will be able to determine the amount of testing required for requalification. End Information ________________________________________________________________________ 21. Recordkeeping and Reporting (Sec. 60.31) ________________________________________________________________________ Begin QPS Requirements a. FSTD modifications can include hardware or software changes. For FSTD modifications involving software programming changes, the record required by Sec. 60.31(a)(2) must consist of the name of the aircraft system software, aerodynamic model, or engine model change, the date of the change, a summary of the change, and the reason for the change. b. If a coded form for record keeping is used, it must provide for the preservation and retrieval of information with appropriate security or controls to prevent the inappropriate alteration of such records after the fact. End QPS Requirements ________________________________________________________________________ 22. Applications, Logbooks, Reports, and Records: Fraud, Falsification, or Incorrect Statements (Sec. 60.33) There are no additional QPS requirements or informational material that apply to Sec. 60.33, Applications, Logbooks, Reports, and Records: Fraud, Falsification, or Incorrect Statements. 23. [Reserved] 24. [Reserved] 25. FSTD Qualification on the Basis of a Bilateral Aviation Safety Agreement (BASA) (Sec. 60.37) There are no additional QPS requirements or informational material that apply to Sec. 60.37, FSTD Qualification on the Basis of a Bilateral Aviation Safety Agreement (BASA). Attachment 1 to Appendix C to Part 60--General Simulator Requirements ________________________________________________________________________ Begin QPS Requirements 1. Requirements. a. Certain requirements included in this appendix must be supported with a Statement of Compliance and Capability (SOC), which may include objective and subjective tests. The SOC will confirm that the requirement was satisfied, and describe how the requirement was met, such as gear modeling approach or coefficient of friction sources. The requirements for SOCs and tests are indicated in the ``General Simulator Requirements'' column in Table C1A of this appendix. b. Table C1A describes the requirements for the indicated level of FFS. Many devices include operational systems or functions that exceed the requirements outlined in this section. However, all systems will be tested and evaluated in accordance with this appendix to ensure proper operation. End QPS Requirements ________________________________________________________________________ Begin Information 2. Discussion. a. This attachment describes the general simulator requirements for qualifying a helicopter FFS. The sponsor should also consult the objective tests in Attachment 2 and the examination of functions and subjective tests listed in Attachment 3 to determine the complete requirements for a specific level simulator. b. The material contained in this attachment is divided into the following categories: [[Page 186]] (1) General cockpit configuration. (2) Simulator programming. (3) Equipment operation. (4) Equipment and facilities for instructor/evaluator functions. (5) Motion system. (6) Visual system. (7) Sound system. c. Table C1A provides the standards for the General Simulator Requirements. End Information ________________________________________________________________________ Table C1A-- Minimum Simulator Requirements ---------------------------------------------------------------------------------------------------------------- QPS requirements Simulator levels --------------------------------------------------------------------------------- Information Notes No. General simulator requirements A B C D ---------------------------------------------------------------------------------------------------------------- 1. General Cockpit Configuration ---------------------------------------------------------------------------------------------------------------- 1.a............ The simulator must have a cockpit ..... X X X For simulator purposes, the that is a replica of the cockpit consists of all that helicopter simulated with space forward of a cross controls, equipment, observable section of the fuselage at cockpit indicators, circuit the most extreme aft setting breakers, and bulkheads properly of the pilots' seats located, functionally accurate and including addiitonal, replicating the helicopter. The required flight crewmember direction of movement of controls duty stations and those and switches must be identical to required bulkheads aft of the that in the helicopter. Pilot pilot seats. For seats must afford the capability clarification, bulkheads for the occupant to be able to containing only items such as achieve the design ``eye landing gear pin storage position'' established for the compartments, fire axes or helicopter being simulated. extinguishers, spare light Equipment for the operation of the bulbs, aircraft documents cockpit windows must be included, pouches etc., are not but the actual windows need not be considered essential and may operable. Fire axes, be omitted. extinguishers, spare light bulbs, etc., must be available in the FFS but may be relocated to a suitable location as near as practical to the original position. Fire axes, landing gear pins, and any similar purpose instruments need only be represented in silhouette. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 1.b............ Those circuit breakers that affect ..... X X X procedures and/or result in observable cockpit indications must be properly located and functionally accurate. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 2. Programming ---------------------------------------------------------------------------------------------------------------- 2.a............ A flight dynamics model that ..... X X X accounts for various combinations of drag and thrust normally encountered in flight must correspond to actual flight conditions, including the effect of change in helicopter attitude, thrust, drag, altitude, temperature, gross weight, moments of inertia, center of gravity location, and configuration. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 2.b............ The simulator must have the ..... X X X computer capacity, accuracy, resolution, and dynamic response needed to meet the qualification level sought. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 2.c............ Ground handling and aerodynamic programming must include the following: ---------------------------------------------------------------------------------------------------------------- 2.c.1.......... Ground effect...................... ..... X X X Applicable areas include flare and touchdown from a running landing as well as for in- ground-effect (IGE) hover. A reasonable simulation of ground effect includes modeling of lift, drag, pitching moment, trim, and power while in ground effect. Level B does not require hover programming. An SOC is required. ---------------------------------------------------------------------------------------------------------------- [[Page 187]] 2.c.2.......... Ground reaction.................... ..... X X X Reaction of the helicopter upon contact with the landing surface during landing, (e.g., strut deflection, tire or skid friction, side forces) and may differ with changes in gross weight, airspeed, rate of descent on touchdown, and slide slip. Level B does not require hover programming. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 2.c.3.......... Ground handling characteristics. ..... X X X Control inputs required during operations in crosswind, during braking and deceleration, and for turning radius. ---------------------------------------------------------------------------------------------------------------- 2.d............ The simulator must provide for ..... ..... X X This may include an automated manual and automatic testing of system, which could be used simulator hardware and software for conducting at least a programming to determine portion of the QTG tests. compliance with simulator Automatic ``flagging'' of out- objective tests as prescribed in of-tolerance situations is Attachment 2. encouraged. An SOC is required................. ---------------------------------------------------------------------------------------------------------------- 2.e............ Relative responses of the motion ..... ..... ..... ..... The intent is to verify that system, visual system, and cockpit the simulator provides instruments, measured by latency instrument, motion, and tests or transport delay tests. visual cues that are like the Motion onset should occur before helicopter responses within the start of the visual scene the stated time delays. For change (the start of the scan of helicopter response, the first video field containing acceleration in the different information) but must appropriate corresponding occur before the end of the scan rotational axis is preferred. of that video field. Instrument response may not occur prior to motion onset. Test results must be within the following limits: ---------------------------------------------------------------------------------------------------------------- 2.e.1.......... Response must be within 150 ..... X milliseconds of the helicopter response. Objective Tests are required. See Attachment 2 for Transport Delay and Latency Tests. ---------------------------------------------------------------------------------------------------------------- 2.e.2.......... Response must be within 100 ..... ..... X X milliseconds of the helicopter response. Objective Tests are required. See Attachment 2 for Transport Delay and Latency Tests. ---------------------------------------------------------------------------------------------------------------- 2.f............ The simulator must accurately ..... ..... X X .............................. reproduce the following runway conditions: (1) Dry; (2) Wet; (3) Icy; (4) Patchy Wet (5) Patchy Icy An SOC is required. Objective tests are required for dry, wet, and icy runway conditions. Subjective tests are required for patchy wet, patchy icy, and wet on rubber residue in touchdown zone conditions. ---------------------------------------------------------------------------------------------------------------- 2.g............ The simulator must simulate: ..... ..... X X Simulator pitch, side loading, (1) Brake and tire failure dynamics and directional control (including antiskid failure).. characteristics should be (2) Decreased brake efficiency due representative of the to high brake temperatures, if helicopter. applicable.. An SOC is required. ---------------------------------------------------------------------------------------------------------------- [[Page 188]] 2.h............ The modeling in the simulator must ..... ..... X X See Attachment 2 for further include: information on ground effect. (1) Ground effect,................. (2) Effects of airframe icing (if applicable),. (3) Aerodynamic interference effects between the rotor wake and fuselage,. (4) Influence of the rotor on control and stabilization systems, and. (5) Representations of nonlinearities due to sideslip.. An SOC is required and must include references to computations of aeroelastic representations and of nonlinearities due to sideslip. An SOC and a demonstration of icing effects (if applicable) are required. ---------------------------------------------------------------------------------------------------------------- 2.i............ The simulator must provide for ..... X X X realistic mass properties, including gross weight, center of gravity, and moments of inertia as a function of payload and fuel loading. An SOC is required and must include a range of tabulated target values to enable a subjective test of the mass properties model to be conducted from the instructor's station. ---------------------------------------------------------------------------------------------------------------- 3. Equipment Operation ---------------------------------------------------------------------------------------------------------------- 3.a............ All relevant instrument indications ..... X X X involved in the simulation of the helicopter must automatically respond to control movement or external disturbances to the simulated helicopter; e.g., turbulence or windshear. Numerical values must be presented in the appropriate units. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 3.b............ Communications, navigation, ..... X X X See Attachment 3 for further caution, and warning equipment information regarding long- must be installed and operate range navigation equipment. within the tolerances applicable for the helicopter being simulated. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 3.c............ Simulated airplane systems must ..... X X X operate as the helicopter systems would operate under normal, abnormal, and emergency operating conditions on the ground and in flight. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 3.d............ The simulator must provide pilot ..... X X X controls with control forces and control travel that correspond to the simulated helicopter. The simulator must also react in the same manner as in the helicopter under the same flight conditions. An objective test is required. ---------------------------------------------------------------------------------------------------------------- 4. Instructor / Evaluator Facilities ---------------------------------------------------------------------------------------------------------------- 4.a............ In addition to the flight ..... X X X The NSPM will consider crewmember stations, the simulator alternatives to this standard must have at least two suitable for additional seats based on seats for the instructor/check unique cockpit airman and FAA inspector. These configurations. seats must provide adequate vision to the pilot's panel and forward windows. All seats other than flight crew seats need not represent those found in the helicopter but must be adequately secured to the floor and equipped with similar positive restraint devices. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- [[Page 189]] 4.b............ The simulator must have controls ..... X X X that enable the instructor/ evaluator to control all required system variables and insert all abnormal or emergency conditions into the simulated helicopter systems as described in the sponsor's FAA-approved training program, or as described in the relevant operating manual as appropriate. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 4.c............ The simulator must have instructor ..... X X X controls for environmental conditions including wind speed and direction. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 4.d............ The simulator must provide the ..... ..... X X For example, another aircraft instructor or evaluator the the crossing the active runway ability to present ground and air and converging airborne hazards. traffic. ---------------------------------------------------------------------------------------------------------------- A subjective test is required. 5. Motion System ---------------------------------------------------------------------------------------------------------------- 5.a............ The simulator must have motion ..... X X X For example, touchdown cues (force) cues perceptible to the should be a function of the pilot that are representative of rate of descent (RoD) of the the motion in a helicopter. simulated helicopter. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 5.b............ The simulator must have a motion ..... X (force cueing) system with a minimum of three degrees of freedom (at least pitch, roll, and heave). An SOC is required. ---------------------------------------------------------------------------------------------------------------- 5.c............ The simulator must have a motion ..... ..... X X (force cueing) system that produces cues at least equivalent to those of a six-degrees-of- freedom, synergistic platform motion system (i.e., pitch, roll, yaw, heave, sway, and surge). An SOC is required. ---------------------------------------------------------------------------------------------------------------- 5.d............ The simulator must provide for the ..... X X X recording of the motion system response time. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 5.e............ The simulator must provide motion ..... ..... ..... ..... effects programming to include the following: (1) Runway rumble, oleo ..... X X X deflections, effects of ground speed, uneven runway, characteristics. (2) Buffets due to transverse flow effects.. (3) Buffet during extension and retraction of landing gear.. (4) Buffet due to retreating blade stall.. (5) Buffet due to settling with power.. (6) Representative cues resulting from touchdown.. (7) Rotor vibrations............... A subjective test is required for each. ------------------------------------------------------------------------------------------------ (8) Tire failure dynamics. ..... ..... X X (9) Engine malfunction and engine damage. (10) Airframe ground strike........ A subjective test is required for each. ------------------------------------------------------------------------------------------------ (11) Motion vibrations that result ..... ..... ..... X For air turbulence, general from atmospheric disturbances. purpose disturbance models that approximate demonstrable flight test data are acceptable. 5.f............ The simulator must provide ..... ..... ..... X The simulator should be characteristic motion vibrations programmed and instrumented that result from operation of the in such a manner that the helicopter, (for example, characteristic buffet modes retreating blade stall, extended can be measured and compared landing gear, settling with power) to helicopter data. in so far as vibration marks an event or helicopter state, which can be sensed in the cockpit. A subjective test is required. [[Page 190]] An objective test is required. ---------------------------------------------------------------------------------------------------------------- 6. Visual System ---------------------------------------------------------------------------------------------------------------- 6.a............ The simulator must have a visual ..... X X X system providing an out-of-the- cockpit view. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.b............ The simulator must provide a ..... X continuous minimum collimated field of view of 75[deg] horizontally and 30[deg] vertically per pilot seat. Both pilot seat visual systems must be operable simultaneously. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 6.c............ The simulator must provide a ..... ..... X ..... Optimization of the visual continuous minimum collimated field of view may be visual field of view of 150[deg] considered with respect to horizontally and 40[deg] the specific helicopter vertically per pilot seat. Both cockpit cut-off angle. pilot seat visual systems must be operable simultaneously. Horizontal field of view is centered on the zero degree azimuth line relative to the aircraft fuselange. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 6.d............ The simulator must provide a ..... ..... ..... X Optimization of the visual continuous minimum collimated field of view may be visual field of view of 180[deg] considered with respect to horizontally and 60[deg] the specific airplane cockpit vertically per pilot seat. Both cut-off angle. pilot seat visual systems must be operable simultaneously. Horizontal field of view is centered on the zero degree azimuth line relative to the aircraft fuselage. An SOC is required. An objective test is required. ---------------------------------------------------------------------------------------------------------------- 6.e............ The visual system must be free from ..... X X X Non-realistic cues might optical discontinuities and include image ``swimming'' artifacts that create non- and image ``roll-off,'' that realistic cues. may lead a pilot to make incorrect assessments of speed, acceleration and/or situational awareness. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.f............ The simulator must have operational ..... X X X landing lights for night scenes. Where used, dusk (or twilight) scenes require operational landing lights. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.g............ The simulator must have instructor ..... X X X controls for the following: (1) Cloudbase...................... (2) Visibility in statute miles (kilometers) and runway visual range (RVR) in ft. (meters).. (3) Airport or landing area selection.. (4) Airport or landing area lighting.. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.h............ Each airport scene displayed must ..... X X X include the following: 1. Airport runways and taxiways. 2. Runway definition: a. Runway surface and markings. b. Lighting for the runway in use, including runway threshold, edge, centerline, touchdown zone, VASI (or PAPI), and approach lighting of appropriate colors, as appropriate. c. Taxiway lights. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.i............ The distances at which runway ..... X X X features are visible, as measured from runway threshold to a helicopter aligned with the runway on an extended 3[deg] glide slope must not be less than listed below: [[Page 191]] 1. Runway definition, strobe lights, approach lights, runway edge white lights and VASI or PAPI system lights from 5 statute miles (8 km) of the runway threshold. 2. Runway centerline lights and taxiway definition from 3 statute miles (4.8 km). 3. Threshold lights and touchdown zone lights from 2 statute miles (3.2 km). 4. Runway markings within range of landing lights for night scenes and as required by three (3) arc- minutes resolution on day scenes. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.j............ The simulator must provide visual ..... X X X system compatibility with dynamic response programming. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.k............ The simulator must show that the ..... X X X The test should be conducted segment of the ground visible from in the landing configuration, the simulator cockpit is the same trimmed for appropriate as from the airplane cockpit airspeed, at 100 ft (30m) (within established tolerances) above the touchdown zone, on when at the correct airspeed, in glide slope with an RVR value the landing configuration, at a set at 1,200 ft (350m). This main wheel height of 100 feet (30 will show the modeling meters) above the touchdown zone. accuracy of RVR, glideslope, Data submitted must include at and localizer for a given least the following: weight, configuration and (1) Static helicopter dimensions as speed within the helicopter's follows:. operational envelope for a (i) Horizontal and vertical normal appraoch and landing. distance from main landing gear If non-homogenous fog is (MLG) or landing skids to used, the vertical variation glideslope reception antenna.. in horizontal visibility (ii) Horizontal and vertical should be described and be distance from MLG or skids to included in the slant range pilot's eyepoint.. visibility calculation used (iii) Static cockpit cutoff angle.. in the computations. (2) Approach data as follows:...... (i) Identification of runway....... (ii) Horizontal distance from runway threshold to glideslope intercept with runway.. (iii) Glideslope angle............. (iv) Helicopter pitch angle on approach.. (3) Helicopter data for manual testing:. (i) Gross weight................... (ii) Helicopter configuration...... (iii) Approach airspeed............ The QTG must contain appropriate calculations and a drawing showing the pertinent data used to establish the helicopter location and the segment of the ground that is visible considering the helicopter attitude (cockpit cut- off angle) and a runway visual range of 1,200 feet or 350 meters. Simulator performance must be measured against the QTG calculations. Sponsors must provide this data for each simulator (regardless of previous qualification standards) to qualify the simulator for all precision instrument approaches. At the near end of the visual ground segment, lights and ground objects computed to be visible from the helicopter cockpit must be visible in the FFS. The far end of the visual ground segment must be at the computed end of the segment 20% of the computed visible segment distance. An SOC is required. An objective test is required. ---------------------------------------------------------------------------------------------------------------- 6.1............ The simulator must provide visual ..... X cues necessary to assess rate of change of height, height AGL, as well as translational displacement and rates during takeoffs and landings. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- [[Page 192]] 6.m............ The simulator must have night and ..... ..... X X Examples of general terrain dusk (or twilight) visual scene characteristics are fields, capability, including general roads, and bodies of water. terrain characteristics and significant landmarks, free from apparent quantization. Dusk (or twilight) scene must enable identification of a visible horizon and general terrain characteristics.. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.n............ The simulator must provide visual ..... ..... X X cues necessary to assess rate of change of height, height AGL, as well as translational displacement and rates during takeoff, low altitude/low airspeed maneuvering, hover, and landing. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.o............ The simulator must provide for ..... X X X Visual attitude vs. simulator accurate portrayal of the visual attitude is a comparison of environment relating to the pitch and roll of the horizon simulator attitude. as displayed in the visual scene compared to the display on the attitude indicator. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.p............ The simulator must provide for ..... ..... X X quick confirmation of visual system color, RVR, focus, and intensity. An SOC is required. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.q............ The simulator must provide a ..... ..... X X minimum of three airport scenes including the following: 1. Surfaces on runways, taxiways, and ramps. 2. Lighting of approriate color for all runways, including runway threshold, edge, centerline, VASI (or PAPI), and approach lighting for the runway in use. 3. Airport taxiway lighting. 4. Ramps and buildings that correspond to the sponsor's Line Oriented scenarios, as appropriate. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.r............ The simulator must be capable of ..... ..... X X producing at least 10 levels of occulting.. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.s............ The fog simulator must be able to ..... ..... X X provide weather representations including the following: (1) Variable cloud density. (2) Partial obscuration of ground scenes; i.e., the effect of a scattered to broken cloud deck. (3) Gradual breakout. (4) Patchy fog. (5) The effect of fog on airport lighting The weather representations must be provided at and below an altitude of 2,000 ft (610 m) height above the airport and within a radius of 10 miles (16 km) from the airport. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- [[Page 193]] 6.t............ Night Visual Scenes. The simulator ..... X X X must provide night visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Night scenes, as a minimum, must provide presentations of sufficient surfaces with appropriate textural cues that include self-illuminated objects such as road networks, ramp lighting, and airport signage, to conduct a visual approach, a landing, and airport movement (taxi). Scenes must include a definable horizon and typical terrain characteristics such as fields, roads and bodies of water and surfaces illuminated by airplane landing lights. ---------------------------------------------------------------------------------------------------------------- 6.u............ Dusk (Twilight) Visual Scenes. The ..... ..... X X simulator must provide dusk (or twilight) visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Dusk (or twilight) scenes, as a minimum, must provide full color presentations of reduced ambient intensity, sufficient surfaces with appropriate textural cues that include self-illuminated objects such as road networks, ramp lighting and airport signage, to conduct a visual approach, landing and airport movement (taxi). Scenes must include a definable horizon and typical terrain characteristics such as fields, roads and bodies of water and surfaces illuminated by representative aircraft lighting (e.g., landing lights). If provided, directional horizon lighting must have correct orientation and be consistent with surface shading effects. Total scene content must be comparable in detail to that produced by 10,000 visible textured surfaces and 15,000 visible lights with sufficient system capacity to display 16 simultaneously moving objects. An SOC is required. ---------------------------------------------------------------------------------------------------------------- 6.v............ Night, Dusk (Twilight), and ..... ..... ..... X Daylight Visual Scenes. The simulator must have night, dusk (twilight), and daylight visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Any ambient lighting must not ``washout'' the displayed visual scene. Total scene content must be comparable in detail to that produced by 10,000 visible textured surfaces and 6,000 visible lights with sufficient system capacity to display 16 simultaneously moving objects. The visual display must be free of apparent quantization and other distracting visual effects while the simulator is in motion. Note: These requirements are applicable to any level of simulator equipped with a daylight visual system. An SOC is required. A subjective test is required. Objective tests are required. ---------------------------------------------------------------------------------------------------------------- 6.w............ The simulator must provide ..... ..... ..... X For example: short runways, operational visual scenes that landing approaches over portray physical relationships water, uphill or downhill known to cause landing illusions runways, rising terrain on to pilots. the approach path, unique topographic features. [[Page 194]] A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.x............ The simulator must provide special ..... ..... ..... X weather representations of light, medium, and heavy precipitation near a thunderstorm on takeoff and during approach and landing. Representations need only be presented at and below an altitude of 2,000 ft. (610 m) above the airport surface and within 10 miles (16 km) of the airport. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.y............ The simulator must present visual ..... ..... ..... X The NSPM will consider scenes of wet and snow-covered suitable alternative effects. runways, including runway lighting reflections for wet conditions, partially obsecured lights for snow conditions. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 6.z............ The simulator must present ..... ..... ..... X realistic color and directionality of all airport lighting. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 7. Sound System ---------------------------------------------------------------------------------------------------------------- 7.a............ The simulator must provide cockpit ..... X X X sounds that result from pilot actions that correspond to those that occur in the helicopter. ---------------------------------------------------------------------------------------------------------------- 7.b............ Volume control, if installed, must ..... X X X have an indication of the sound level setting. ---------------------------------------------------------------------------------------------------------------- 7.c............ The simulator must accurately ..... ..... X X simulate the sound of precipitation, windshield wipers, and other significant helicopter noises perceptible to the pilot during normal and abnormal operations, and include the sound of a crash (when the simulator is landed in an unusual attitude or in excess of the structural gear limitations); normal engine sounds; and the sounds of gear extension and retraction. An SOC is required. A subjective test is required. ---------------------------------------------------------------------------------------------------------------- 7.d............ The simulator must provide ..... ..... ..... X realistic amplitude and frequency of cockpit noises and sounds. Simulator performance must be recorded, compared to amplitude and frequency of the same sounds recorded in the helicopter, and made a part of the QTG. ---------------------------------------------------------------------------------------------------------------- Attachment 2 to Appendix C to Part 60--Simulator Objective Tests ________________________________________________________________________ Begin Information 1. Discussion. (a) If relevant winds are present in the objective data, the wind vector (magnitude and direction) should be clearly noted as part of the data presentation, expressed in conventional terminology, and related to the runway being used for the test. (b) The NSPM will not evaluate any simulator unless the required SOC indicates that the motion system is designed and manufactured to safely operate within the simulator's maximum excursion, acceleration, and velocity capabilities (see Motion System in the following table). End Information ________________________________________________________________________ Begin QPS Requirements 1. Test requirements. a. The ground and flight tests required for qualification are listed in Table of C2A, FFS Objective Tests. Computer generated simulator test results must be provided for each [[Page 195]] test except where an alternative test is specifically authorized by the NSPM. If a flight condition or operating condition is required for the test but does not apply to the helicopter being simulated or to the qualification level sought, it may be disregarded (e.g., an engine out missed approach for a single-engine helicopter, or a hover test for a Level B simulator). Each test result is compared against the validation data described in Sec. 60.13 and in this appendix. Although use of a driver program designed to automatically accomplish the tests is encouraged for all simulators and required for Level C and Level D simulators, each test must be able to be accomplished manually while recording all appropriate parameters. The results must be produced on an appropriate recording device acceptable to the NSPM and must include simulator number, date, time, conditions, tolerances, and appropriate dependent variables portrayed in comparison to the validation data. Time histories are required unless otherwise indicated in Table C2A. All results must be labeled using the tolerances and units given. b. Table C2A sets out the test results required, including the parameters, tolerances, and flight conditions for simulator validation. Tolerances are provided for the listed tests because mathematical modeling and acquisition/development of reference data are often inexact. All tolerances listed in the following tables are applied to simulator performance. When two tolerance values are given for a parameter, the less restrictive may be used unless otherwise indicated. c. Certain tests included in this attachment must be supported with a Statement of Compliance and Capability (SOC). In Table C2A, requirements for SOCs are indicated in the ``Test Details'' column. d. When operational or engineering judgment is used in making assessments for flight test data applications for simulator validity, such judgment must not be limited to a single parameter. For example, data that exhibit rapid variations of the measured parameters may require interpolations or a ``best fit'' data selection. All relevant parameters related to a given maneuver or flight condition must be provided to allow overall interpretation. When it is difficult or impossible to match simulator to helicopter data throughout a time history, differences must be justified by providing a comparison of other related variables for the condition being assessed. e. It is not acceptable to program the FFS so that the mathematical modeling is correct only at the validation test points. Unless noted otherwise, simulator tests must represent helicopter performance and handling qualities at operating weights and centers of gravity (CG) typical of normal operation. If a test is supported by helicopter data at one extreme weight or CG, another test supported by helicopter data at mid-conditions or as close as possible to the other extreme must be included, except as may be authorized by the NSPM. Certain tests that are relevant only at one extreme CG or weight condition need not be repeated at the other extreme. Tests of handling qualities must include validation of augmentation devices. f. When comparing the parameters listed to those of the helicopter, sufficient data must also be provided to verify the correct flight condition and helicopter configuration changes. For example, to show that control force is within 0.5 pound (0.22 daN) in a static stability test, data to show the correct airspeed, power, thrust or torque, helicopter configuration, altitude, and other appropriate datum identification parameters must also be given. If comparing short period dynamics, normal acceleration may be used to establish a match to the helicopter, but airspeed, altitude, control input, helicopter configuration, and other appropriate data must also be given. All airspeed values must be properly annotated (e.g., indicated versus calibrated). In addition, the same variables must be used for comparison (e.g., compare inches to inches rather than inches to centimeters). g. The QTG provided by the sponsor must clearly describe how the simulator will be set up and operated for each test. Each simulator subsystem may be tested independently, but overall integrated testing of the simulator must be accomplished to assure that the total simulator system meets the prescribed standards. A manual test procedure with explicit and detailed steps for completing each test must also be provided. h. In those cases where the objective test results authorize a ``snapshot test'' or ``a series of snapshot test'' results in lieu of a time-history result, the sponsor or other data provider must ensure that a steady state condition exists at the instant of time captured by the ``snapshot.'' i. For previously qualified simulators, the tests and tolerances of this attachment may be used in subsequent continuing qualification evaluations for any given test if the sponsor has submitted a proposed MQTG revision to the NSPM and has received NSPM approval. j. Motion System Tests: (a) The minimum excursions, accelerations, and velocities for pitch, roll, and yaw must be measurable about a single, common reference point and must be achieved by driving one degree of freedom at a time. (b) The minimum excursions, accelerations, and velocities for heave, sway, and surge may be measured about different but identifiable reference points and must also be achieved by driving one degree of freedom at a time. [[Page 196]] k. Tests of handling qualities must include validation of augmentation devices. FFSs for highly augmented helicopters will be validated both in the unaugmented configuration (or failure state with the maximum permitted degradation in handling qualities) and the augmented configuration. Where various levels of handling qualities result from failure states, validation of the effect of the failure is necessary. For those performance and static handling qualities tests where the primary concern is control position in the unaugmented configuration, unaugmented data are not required if the design of the system precludes any affect on control position. In those instances where the unaugmented helicopter response is divergent and non- repeatable, it may not be feasible to meet the specified tolerances. Alternative requirements for testing will be mutually agreed upon by the sponsor and the NSPM on a case-by-case basis. l. Some tests will not be required for helicopters using helicopter hardware in the simulator cockpit (e.g., ``helicopter modular controller''). These exceptions are noted in Table C2A of this attachment. However, in these cases, the sponsor must provide a statement that the helicopter hardware meets the appropriate manufacturer's specifications and the sponsor must have supporting information to that fact available for NSPM review. m. For objective test purposes, ``Near maximum'' gross weight is a weight chosen by the sponsor or data provider that is not less than the basic operating weight (BOW) of the helicopter being simulated plus 80% of the difference between the maximum certificated gross weight (either takeoff weight or landing weight, as appropriate for the test) and the BOW. ``Light'' gross weight is a weight chosen by the sponsor or data provider that is not more than 120% of the BOW of the helicopter being simulated or as limited by the minimum practical operating weight of the test helicopter. ``Medium'' gross weight is a weight chosen by the sponsor or data provider that is approximately 10% of the average of the numerical values of the BOW and the maximum certificated gross weight. (Note: BOW is the empty weight of the aircraft plus the weight of the following: normal oil quantity; lavatory servicing fluid; potable water; required crewmembers and their baggage; and emergency equipment. (References: Advisory Circular 120-27, ``Aircraft Weight and Balance;'' and FAA-H-8083-1, ``Aircraft Weight and Balance Handbook.''). End QPS Requirements ________________________________________________________________________ Begin QPS Requirements [[Page 197]] Table C2A--Full Flight Simulator (FFS) Objective Tests -------------------------------------------------------------------------------------------------------------------------------------------------------- << < -------------------------------------------------------------------------------------------------------------------------------------------------------- Test Simulator level -------------------------------- Tolerance(s) Flight condition Test details ---------------------------- Notes No. Title A B C D -------------------------------------------------------------------------------------------------------------------------------------------------------- 1. Performance -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a......... Engine Assessment. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a.1....... Start Operations. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a.1.a..... Engine start and Light Off Time -- Ground with the Record each X X X acceleration 10% or Used and Not from the 1 sec., the start Torque -- steady state 5%, Rotor Speed idle and from -- idle to 3%, Fuel Flow -- operating RPM. 10%, Gas Generator Speed -- 5%, Power Turbine Speed -- 5%, Gas Turbine Temp. -- 30 [deg]C. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a.1.b..... Steady State Idle Torque -- steady state RPM conditions. 3%, Rotor Speed idle and -- conditions.. 1.5%, Fuel Flow May be a series -- tests.. 5%, Gas Generator Speed -- 2%, Power Turbine Speed -- 2%, Turbine Gas Temp. -- 20 [deg]C. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a.2....... Power Turbine 10% of response to total change of trim system power turbine actuation in speed. both directions. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.a.3....... Engine and Rotor Torque -- using a step 5%, Rotor Speed input to the -- 1.5%. collective. May be conducted concurrently with climb and descent performance tests. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 198]] 1.b......... Surface Operations. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.b.1....... Minimum Radius 3 ft. used, brake (0.9m) or 20% of force must be helicopter turn matched to the radius. helicopter flight test value. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.b.2....... Rate of Turn vs. 10% or or Nosewheel 2[deg]/ sec. Turn Rate. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.b.3....... Taxi............. Pitch Angle -- Ground.......... Record results X X X 1.5[deg], position and Torque -- during ground 3%, Longitudinal taxi for a Control Position specific ground -- speed and 5%, Lateral direction, and Control Position density -- 5%, Dirrectional Control Position. -------------------------------------------------------------------------------------------------------------------------------------------------------- 5%, Collective Control Position -- 5%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.b.4....... Brake 10% of time and distance. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.c......... Takeoff . -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 199]] 1.c.1....... All Engines...... Airspeed -- and Initial of takeoff 3 kt, Altitude -- Segment of flight path as 20 ft helicopter (6.1m), Torque -- model simulated 3%, Rotor takeoff for Speed -- takeoff from a 1.5%, Vertical hover for Level Velocity -- C and D). For 100 fpm criteria apply (0.50m/sec) or only to those 10%, Pitch segments at Attitude -- airspeeds above 1.5[deg], translational Bank Attitude -- lift. Results 2[deg], recorded from Heading -- of the takeoff 2[deg], to at least 200 Longitudinal ft (61m) AGL. Control Position -- 10%, Lateral Control Position -- 10%, Directional Control Position -- 10%, Collective Control Position -- 10%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.c.2....... One Engine Airspeed -- and Initial flight path as 3 kt, Altitude -- Segment of appropriate to 20 ft model (6.1m), Torque -- simulated. 3%, Rotor recorded from Speed -- of the takeoff 1.5%, Vertical to at least 200 Velocity -- ft (61m) AGL. 100 fpm (0.50m/sec) or 10%, Pitch Attitude -- 1.5[deg], Bank Attitude -- 2[deg], Heading -- 2[deg], Longitudinal Control Position -- 10%, Lateral Control Position -- 10%, Directional Control Position -- 10%, Collective Control Position -- 10%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.d......... Hover. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 200]] Performance...... Torque -- (IGE); and Out for light and 3%, Pitch of Ground heavy gross Attitude -- Effect (OGE). weights. May be 1.5[deg], snapshot tests. Bank Attitude -- 1.5[deg], Longitudinal Control Position -- 5%, Lateral Control Position -- 5%, Directional Control Position -- 5%, Collective Control Position -- 5%,. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.e......... Vertical Climb. -------------------------------------------------------------------------------------------------------------------------------------------------------- Performance...... Vertical Velocity From OGE Hover.. Record results X X -- heavy gross 100 fpm (0.50 m/ weights. May be sec) or snapshot tests. 10%, Directional Control Position -- 5%, Collective Control Position -- 5%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.f......... Level Flight. -------------------------------------------------------------------------------------------------------------------------------------------------------- Performance and Torque -- (Augmentation for two gross Control 3%, Pitch On and Off). weight and CG Positions. Attitude -- combinations 1.5[deg], trim speeds Sideslip Angle -- throughout the 2[deg], envelope. May Longitudinal be a series of Control Position snapshot tests. -- 5%, Lateral Control Position -- 5%, Directional Control Position -- 5%, Collective Control Position -- 5%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.g......... Climb. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 201]] Performance and Vertical Velocity All engines Record results X X X Trimmed Flight -- engine weight and CG Positions. 100 fpm (6.1m/ inoperative; combinations. sec) or System(s) On presented must 10%, Pitch and Off. be for normal Attitude -- climb power 1.5[deg], be a series of Sideslip Angle -- snapshot tests. 2[deg], Longitudinal Control Position -- 5%, Lateral Control Position -- 5%, Directional Control Position -- 5%, Collective Control Position -- 5%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.h......... Descent. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.h.1....... Descent Torque -- fpm rate of recorded for Trimmed Flight 3%, Pitch descent (RoD) two gross Control Attitude -- at normal weight and CG Positions. 1.5[deg], Augmentation May be a series Sideslip Angle -- System(s) On of snapshot 2[deg], Longitudinal Control Position -- 5%, Lateral Control Position -- 5%, Directional Control Position -- 5%, Collective Control Position -- 5%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.h.2....... Autorotation Torque -- Augmentation for two gross Trimmed Flight 3%, Pitch System(s) On weight Control Attitude -- and Off. conditions. Positions. 1.5[deg], recorded for Sideslip Angle -- normal 2[deg], (Rotor speed Longitudinal tolerance Control Position applies only if -- control 5%, Lateral position is Control Position full down.) May -- snapshot tests. 5%, Directional Control Position -- 5%, Collective Control Position -- 5% Vertical Velocity 100 fpm or 19%, Rotor Speed 1.5%. 1.i......... Autorotation. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 202]] Entry............ Rotor Speed-- Cruise or Climb. Record results ..... X X 3% Pitch throttle Attitude idle. If the 2[deg]Roll cruise Attitude-- selected, 3[deg] Yaw comparison must Attitude-- maximum range 5[deg] Airspeed-- airspeed. If 5 kts. condition is Vertical selected, Velocity-- be made for the 200 fpm (1.00 m/ maximum rate of sec) or 10%. climb airspeed at or near maximum continuous power. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.j......... Landing. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 203]] 1.j.1....... All Engines...... Airspeed-- of the approach 3 kts., and landing Altitude-- appropriate to 20 ft. (6.1m), the helicopter Torque-- (running 3%, Rotor Speed-- landing for 1.5%, approach to a Pitch Attitude-- hover for Level 1.5[deg], Level B, the Bank Attitude-- criteria apply 1.5[deg], segments at Heading-- effective 2[deg], translational Longitudinal lift. Control Position-- 10%, Lateral Control Position-- 10%, Directional Control Position-- 10%, Collective Control Position-- 10%. -------------------------------------------------------------------------------------------------------------------------------------------------------- 1.j.2....... One Engine Airspeed-- for both 3 kts., Category A and Altitude-- approaches and 20 ft. (6.1m), landing as Torque-- helicopter 3%, Rotor Speed-- model 1.5%, Level B, the Pitch Attitude-- criteria apply 1.5[deg], segments at Bank Attitude-- airspeeds above 1.5[deg], translational Heading-- 2[deg], Longitudinal Control Position-- 10%, Lateral Control Position-- 10%, Directional Control Position-- 10%, Collective Control Position--