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AC-33.91-1 - HIRF | Regulatory Compliance | Calibration
AC-33.91-1 - HIRF
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Date: 12/9/10 Initiated By: ANE-111 AC No: 33.91-1 Change:
Subject: Engine System and Component Tests
1. Purpose. This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with the engine component and systems test requirements under Title 14 of the Code of Federal Regulations (14 CFR), part 33, specifically § 33.91, paragraphs (a) and (b). 2. Applicability. a. The guidance provided in this AC is directed to the engine manufacturer, modifier, or foreign regulatory authority. b. This material is neither mandatory nor regulatory in nature and does not constitute a regulation. The FAA will consider other methods of demonstrating compliance that an applicant may elect to present. Terms such as "should," "shall," "may," and "must" are used only in the sense of ensuring applicability of this particular method of compliance when the acceptable method of compliance in this document is used. While these guidelines are not mandatory, they are derived from extensive FAA and industry experience in determining compliance with the relevant regulations. On the other hand, if we become aware of circumstances that convince us that following this AC would not result in compliance with the applicable regulations, we will not be bound by the terms of this AC, and we may require additional substantiation as the basis for finding compliance. c. This material does not change, create any additional changes, authorize changes in, or permit deviations from existing regulatory requirements. 3. Applicable Regulation. 14 CFR part 33.91, Engine System and Component Tests, paragraphs (a) and (b). 4. Definitions. For the purpose of this AC, the following definitions apply: a. Component: Any individual device that is part of a specific engine system. Examples of engine components include, but are not limited to, fuel pump, oil pump, hydraulic pump, heat exchanger, hydromechanical fuel control, bleed air check valve, fuel shutoff valve, electronic
5. paragraphs (a) and (b). the test parameter ranges specified in these documents must be verified to ensure they cover the component throughout the engine operating environment. Successfully completing the applicable tests in accordance with the methods of compliance described in this AC. 2 . hydraulic.91. electrical. System: A combination of inter-related components arranged to perform a specific function. the latest revision of documents referenced in Table 1 should be applied unless otherwise identified in the approved test plan. b. accessory drive gearbox. air bleed (e. when operated at the limits of engine environmental and operating conditions. may be an acceptable showing of compliance to § 33. however. Testing under § 33. Table 1 below provides a summary of the testing we have found sufficient to meet the requirements of § 33. not all test categories will apply to all types of components or systems. exciters. or similar engine type functions. The intent of § 33.91. speed. Specific test procedures or limits should be developed when the test parameter ranges or procedures specified in the referenced documents are not sufficient to cover the engine operating environment. Other types of components may also be affected. Table 1 of reference 1 provides guidance on when a test category would generally apply to a particular component or system.12/9/10 AC 33. Examples of engine systems are lubrication (e.87 (or other part 33 requirements) is not sufficient to cover the extreme conditions that can be encountered in service. and torque sensors. General. However. b..91. secondary/cooling/anti-ice). including limits specified in the engine Installation Manual. See Appendix 1 of this AC. paragraphs (a) and (b) is generally conducted when endurance testing under § 33. main engine oil). Test Categories. such as the temperature. paragraphs (a) and (b). 6.. a. intended aircraft installation. ignitors. engine model. The applicable environmental conditions will vary with the type of component. The identified tests are only required when the engine certification program content does not expose the component to the extreme conditions defined for that engine type design.g. etc.91-1 engine control device. Also.g. engine parameter sensors. This requires that an individual component or complete system be tested under a variety of conditions.91 compliance. and corresponding operating conditions and limitations. The identified test procedures cover many components and systems. paragraphs (a) and (b) is to demonstrate by test that engine components and systems will perform satisfactorily in service. pressure. and other test categories that are not listed may apply. The references in Table 1 generally provide acceptable guidance for the noted test categories.91. but some may be internally mounted. These components are generally mounted externally on the engine case. paragraphs 1-4 provide an additional perspective on general historical § 33. reference 1.
28(b)(2) and AC 33.3 ARP5757. 21 and 22 20 21 22 DO-160 Sections 16. 20.67 for requirements.4 DO-160 Section 8 DO-160 Section 7 ARP5757. Section 5. See Notes 2 and 3 See Notes 2 and 3 See Notes 2 and 3. See Notes 2 and 3 See Note 1 See Note 1 13 14 15 Fungus Resistance Temperature & Altitude Temperature Variation DO-160 Section 13 DO-160 Section 4 DO-160 Section 5 16 17 18 19 Explosive Atmosphere Humidity Waterproofness Environmental Limits  Lightning  Electromagnetic Interference (EMI)  High Intensity Radiated Fields (HIRF) Power Input & Voltage Spike Proof Pressure Burst Pressure DO-160 Section 9 DO-160 Section 6 DO-160 Section 10 DO-160 Sections 15.7 DO-160 Section 12 DO-160 Section 11 DO-160 Section 14 ARP5757.21 ARP5757 Sec 5.22 3 .12/9/10 AC 33.11 AC 20-147 Comment See Note 1 See Note 1 See Note 1 See Note 1 See Notes 2 and 3 See Notes 2 and 3 See Note 1 See Notes 2 and 3 See Notes 2 and 3 See Notes 2 and 3 Refer to § 33. (Also refer to § 33.2 ARP5757 Sec 5.28 for additional information about environmental limits requirements for engine control system components (see Note 4). 19. Section 5.91-1 TABLE 1 Test No.28-1 (Chapter 7-3.28(b) and AC 33.a. Refer to § 33. Section 5.1 ARP5757 Sec 5.68 for requirements and AC 20-147 for guidance. 17 and 18 ARP5757 Sec 5. 1 2 3 4 5 6 7 8 9 10 11 12 Test Category High Temperature Low Temperature Room Temperature Contaminated Fluids Vibration Operational Shock & Crash Safety Sustained Acceleration Sand & Dust Fluids Susceptibility Salt Fog Fuel System Icing Induction Icing Acceptable Test Procedures ARP5757 Sec 5.(1) See Notes 2 and 3 See Notes 2 and 3 See Notes 2 and 3 Refer to § 33.
which could lead to component malfunction or failure. Section 26 Note 1: See reference 1 in Appendix 1 of this AC (SAE ARP5757).28 for requirements. (5) Vibration: To verify that exposure to the declared vibration environment does not cause structural failure.17-1 for guidance Refer to § 33. Note 4: Section 33.91 with respect to certain environmental limits demonstration requirements.23 AC 33. (4) Fluid Contamination: To verify the component can function properly in a contaminated fluid environment. titled “Turbine Engine Vibration”). See AC 33. and that the component functions properly in that environment. and to identify any damage that could be caused by exposure to minimum temperatures that may lead to component malfunction or failure. 4 .28-2 for guidance on FADEC overheat testing. Vibration (see AC 33. Section 5. Note 3: Reference 3 (AC 21-16) provides information concerning the use of reference 2 for type certification purposes. (3) Room Temperature: To identify any component damage caused by extended operation at room temperature. and to identify any damage that could be caused by exposure to maximum temperatures that may lead to component malfunction or failure.28-1 and AC 33. (2) Low Temperature: To verify that the component can function properly in its minimum temperature environment.63. c. The declared vibration environment is that environment utilized for compliance with § 33. See Note 1 25 Specialized Tests  Electronic Engine Control Overheat AC 33. Note 2: See reference 2 in Appendix 1 of this AC (RTCA DO-160). 23 Pressure Cycling 24 Fire Protection Acceptable Test Procedures ARP5757.17 for requirements and AC 33.91-1 TABLE 1 (continued) Test Test Category No.28(b)(2) refers to § 33. or other known engine vibration environment if more severe.17-1 Comment See Note 1 Refer to § 33.28-1 and AC 33.28-2 26 Containnment ARP5757.12/9/10 AC 33.63-1. Test Category Descriptions: (1) High Temperature: To verify that the component can function as intended in its maximum temperature environment.
and Turbofan Engine Induction System Icing and Ice Ingestion” for more information about icing requirements and methods of compliance. Refer to § 33.68 and AC 20-147. The crash safety test is to verify that certain equipment will not detach from its mountings during an emergency maneuver in a manner that results in a hazardous engine effect. 5 . (12) Induction Icing: To verify the component can function properly when the engine inlet is exposed to icing conditions. (15) Thermal Cycle: To verify the component operates properly when exposed to temperature variations between the high and low extremes during flight operations. Turboprob. titled “Turbojet. (7) Sustained Acceleration: To verify the component can function properly when exposed to the expected acceleration forces associated with aircraft operations. and to identify any damage caused by exposure to those forces.12/9/10 AC 33. (13) Fungus: To verify the component materials of construction do not support the growth of fungi. Refer to § 33. (14) Temperature & Altitude: To verify that the component operates properly throughout the engine operating envelope. (8) Sand & Dust: To verify the component can function properly after exposure to a sand and dust environment. and to identify any damage caused by that exposure which could lead to a malfunction or failure. (16) Explosion Proof: To verify the component cannot be the source of ignition for an explosion of flammable fluids or vapors in the surrounding atmosphere.67 for test conditions. (9) Fluid Susceptibility: To verify the component can function properly after exposure to common aviation fluids. (11) Fuel System Icing: To verify the fuel system components operate properly when exposed to fuel icing conditions.91-1 (6) Operational Shock & Crash Safety: The operational shock test is to verify the component can function properly when exposed to the shock/impact load conditions experienced during normal aircraft operations. and to identify any damage caused by that exposure which could lead to a malfunction or failure. and to identify any damage caused by that exposure that could lead to a malfunction or failure. (10) Salt Spray: To verify the component can function properly after exposure to a salt spray environment.
(21) Proof Pressure: To verify that the component can withstand the maximum working pressure (with margin) without damage or leakage. titled “Fire Prevention” for more information about fire protection requirements and methods of compliance. except as noted in reference 2. EMI and HIRF effects. a. Refer to § 33. 7.2.12/9/10 AC 33. (20) Power Input/Voltage Spike: To verify the component can function properly over the full range of declared electrical power inputs. Conduct of Tests.17-1. (25) Specialized Tests (Electronic Engine Control Overheat): To verify the electronic elements of the engine control system do not cause an unsafe condition when exposed to operating temperatures exceeding specified limits. section 3. b. the test article should be connected and oriented (mechanically and electrically) in a similar manner (or functional equivalent) as it would be if installed on the engine. (24) Fire Protection: To demonstrate that the design and construction methods used minimize the occurrence and spread of fire. Order of Tests: Tests may be conducted in any order and on any test article. Connection and Orientation of Components under Test: Generally. (23) Pressure Cycling: To verify the component can withstand the expected operational internal operational fluid pressure cycles without structural failure during the expected life of the component.17 and AC 33. 6 .91-1 (17) Humidity: To verify the component operates properly when exposed to a high humidity atmosphere. (18) Waterproofness: To verify the component operates properly after exposure to water spray or condensation. (19) Lightning/EMI/HIRF: To verify the component can adequately withstand the effects of prescribed lightning. and remains in a serviceable condition. and to identify any damage caused by the exposure that could lead to malfunction or failure. (22) Burst Pressure: To verify the component can withstand the maximum possible pressure (with margin). without fracture or burst.
f. to assure that the required limit values are actually attained during the test. and must be within calibration. d. section 3. Test Equipment Calibration: All equipment used in these tests should be identified by make. e. model. You may need to adjust the selected parameter values based on test equipment accuracy. for that particular test category. required test parameter values are either a minimum for high limits (for example. all calibrations should be traceable to recognized standards. Your approved test plan for each component under test must specify the required post-test actions and detailed pass/fail criteria. serial number. Conformity Requirements: The cognizant engine and/or aircraft certification office will determine the conformity requirements for test articles. are equaled or exceeded in a combined test procedure (also see reference 2.12/9/10 AC 33. as appropriate. reveals no impending failures or damage which could impair the components’ ability to function in a safe manner.91-1 c. (3) Successful post-test completion of the applicable Production Acceptance Test (PAT) sections to serviceable or ultimate limits. 7 .3). software version. paragraphs (a) and (b) tests are summarized below: (1) The component meets its design specification performance standards during operational testing and at the conclusion of the test. (4) Post-test inspection or disassembly (if required by the test plan). As applicable. Note: The provisions above are applicable for most components.91 tests. or a maximum for low limits (for example. 8. Pass/Fail Criteria: The pass/fail criteria for most § 33. Other Considerations.91. Test Parameter Tolerance: Unless otherwise specified in your approved test plan. This information should be included in the test plan and final report. low temperature endurance test). (2) No functional changes occur during the test resulting in significant engine events affecting safety or operability of the engine. calibration expiration date. Combining Tests: Test procedures may be combined if you can demonstrate that the severity of all applicable conditions specified in the individual procedures. high temperature endurance test). You should develop a comprehensive conformity plan for engine type certification projects that require § 33. a.
Aircraft Installation: Testing under § 33.91-1 b. Test Set Up: Normally tests associated with § 33. (2) The engine and installation operating conditions and environment are similar or within the original design scope demonstrated by the original test. so that no significant new data or analysis is required to show similarity. (5) You cannot show § 33. (3) The data from the original compliance finding is adequate to show compliance. and the operating characteristics and environment of the new component relative to the previously approved component. by using test data from a previous engine type certification program. Other components or systems may have other aircraft interface considerations.91 compliance by similarity.g. 8 . provided that the requirements for that test category can be achieved. c. material properties. in some cases you may be able to show § 33. Similarity is normally shown through a relatively simple and direct comparison of the design features.91 compliance are conducted as bench or rig tests. temperatures/pressures/flows) should be considered in test plan development. such as geometry. certain components or systems may best be tested on an engine.g.. For example. paragraphs (a) and (b) should consider aircraft interfaces where appropriate. lightning and EMI testing for electronic control components generally require that representive aircraft harnessing be installed to have a valid test. DO-160). (4) We will not generally conclude that you have shown § 33. limiting stress locations.12/9/10 AC 33. Compliance by Similarity: Each category in this AC is defined as a test to be passed. etc. stress levels. However. the expected installed environment (e. Similarly. However.. d. You may use it to the extent that similarity exists between the component previously tested and your new component.19.91 compliance through showing similarity to a previously approved similarity finding.91 compliance through similarity if your claim is based solely on the use of previously successful design practices or field service histories on similar engine models or components. operating characteristics. Some guidelines are: (1) The new design must be within the scope of the previously approved design in all significant aspects. (6) Compliance may be based on test data collected using earlier version of the industry standard documents referred to in this AC (e. Similarity must be shown to the original test data that demonstrated direct compliance. if that test data shows compliance to the current guidance. function. manufacturing processes.
91-1 9. (10) Test pass/fail criteria. b. (6) Conformity requirements.12/9/10 AC 33. (11) Data recording methods. The certification test plan should contain. Certification test plans should include the following information: (1) Applicable regulation(s) and purpose of test. as a minimum. to denote features of interest). and should be FAA approved before conducting the test. (5) Installation drawing(s) or sketches (for example. (7) Definition and range of component operating and environmental parameters. (3) Part and serial number(s). Engine and Propeller Directorate Aircraft Certification Service 9 . Test Plans. and (12) Deliverable test data. a. to describe installation in an engine). Francis A Favara. (9) Test methods and procedures. (4) Part detail drawing(s) or sketches (for example. the information noted above. A copy of the approved test plan should be available at the test facility at the time of test. (2) Component name(s) and operational description. (8) Test equipment requirements (calibration and set-up). Manager.
DO-160. FAA AC 21-16. SAE Aerospace. RTCA Inc.. Inc.12/9/10 AC 33. Document No. Document RTCA/DO-160. Document No. 2. Environmental Conditions and Test Procedures for Airborne Equipment. Aerospace Recommended Practice. RTCA. Environmental Conditions and Test Procedures for Airborne Equipment. 10 . 3. Guidelines for Engine Component Tests.91-1 Appendix 1 REFERENCES 1. ARP5757.
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