Advisory U.S. Department of Transportation Circular Federal Aviation Administration Date: 06/22/2011 AC No: 21-16GSubject: RTCA Document DO-160 versions D, E, F, and G, “Environmental Conditions Initiated by: AIR-100 and Test Procedures for Airborne Equipment”
1. What is the purpose of this Advisory Circular?
a. This advisory circular (AC) identifies RTCA Document No. (RTCA/DO)-160 versions D, E, F, and G, Environmental Conditions and Test Procedures for Airborne Equipment, dated July 27, 1997, December 20, 2005, December 6, 2007, and December 8, 2010, respectively, as containing acceptable environmental qualifications to show compliance with certain airworthiness requirements. The FAA strongly encourages the use of RTCA/DO-160G for new articles.
b. Appendix 1 of this AC provides a summary of the changes from RTCA/DO-160C to RTCA/DO-160D, version D to E, version E to F, and F to G. The information in the table will assist you in determining if a particular version of RTCA/DO-160 is acceptable.
Note: When reference to RTCA/DO-160D is made in this AC, it includes Changes 1, 2, and 3, dated December 14, 2000, June 12, 2001, and December 5, 2002, respectively.
c. This AC is not mandatory and does not constitute a regulation. This AC describes a means, but not the only means, to comply with airworthiness requirements.
2. To whom does this AC apply? This AC applies to manufacturers and installers that use RTCA/DO-160 for environmental qualifications of their airborne equipment.
3. Cancellation. This AC cancels AC 21-16F, RTCA Document DO-160 versions D, E, and F, Environmental Conditions and Test Procedures for Airborne Equipment, dated November 19, 2009.
4. What is RTCA/DO-160?
a. RTCA/DO-160 (or its precursor, RTCA/DO-138) has been used as a standard for environmental testing since 1958. It defines standard environmental test conditions (categories) and applicable test procedures for airborne equipment.
b. The tests in RTCA/DO-160 provide a laboratory means of demonstrating the performance characteristics of airborne equipment in environmental conditions that may be encountered in operation of the equipment in aircraft. It is not the intent of RTCA/DO-160 to be used as a measure of service life of the airborne equipment subjected to these tests.
c. As the realities of equipment operation under actual environmental conditions are better understood and new needs arise within the aviation community, RTCA/DO-160 has been revised to address the emerging and improved test techniques. The categories that have been developed over time reflect a reasonably mature understanding as to the severity of the environmental stresses, the degrees of mitigation achievable in the design of an installation, and the robustness that must be designed into equipment in order to perform in the operating environment.
5. Related Documents.
a. Title 14 of the Code of Federal Regulations, (14 CFR) parts 21, 23, 25, 27, 29, 33, and
35.
b. AC 20-136, Protection of Aircraft Electrical/Electronic Systems Against the Indirect Effects of Lightning.
c. AC 20-158, The Certification of Aircraft Electrical and Electronic Systems for Operation in the High-Intensity Radiated Fields (HIRF) Environment.
d. AC 20-138, Airworthiness Approval of Positioning and Navigation Systems.
e. AC 33.17-1, Fire Prevention.
6. Using RTCA/DO-160 for Technical Standard Orders (TSOs).
a. If you are an applicant seeking a TSO authorization for airborne equipment, you may request a deviation, in accordance with the requirements of 14 CFR part 21 subpart O, to use the conditions and procedures in a different version of RTCA/DO-160 instead of the corresponding conditions and procedures specified in the applicable TSO. Although an applicant may request to use an earlier version of DO-160, we recommend that you use RTCA/DO-160G.
b. If the TSO does not specify the environmental qualification, the applicant may choose any environmental standard conditions and test procedures appropriate for their airborne equipment. Although an applicant may choose any environmental standard, we recommend that you use RTCA/DO-160G.
c. The table in Appendix 1 of this AC provides sufficient data for an applicant to use as a comparison between RTCA/DO-160D, E, F, and G. The FAA has determined that versions D, E, F, and G provide an equivalent level of safety (ELOS) when the applicable version is identified in the Environmental Qualification Form (EQF). If the installed electrical/electronic equipment must meet lightning requirements use RTCA/DO-160D or later per the latest revision of AC 20-136. However, if the installed equipment is expected to be subject to HIRF 2
requirements in §§ 23.1308, 25.1317, 27.1317, or 29.1317, use RTCA/DO-160F or G.
RTCA/DO-160E is also acceptable to meet the HIRF requirements for level B and C systems when using test levels defined in the appropriate regulations as discussed in AC 20-158.
d. If the version of RTCA/DO-160 specified in a TSO is version D or later, and an applicant wishes to use a version prior to RTCA/DO-160D, then the applicant must meet the requirements of paragraph 6a by comparing the specific procedure and category changes, section by section, between the two versions. The a pplicant must also address the differences between the two test results when providing an equivalent level of safety.
e. When a new application is based on the design of an existing approved article, the applicant may ask to use environmental test data from the existing article’s environmental qualification, based on similarity between the two articles. This request must be fully supported with a detailed similarity assessment comparing the changes from the earlier approved article to the article in the new application. The aircraft certification office (ACO) may accept the data if the similarity assessment clearly shows that the design changes will not adversely affect the environmental qualification.
f. When the equipment or its associated wiring has the likelihood to be located in areas close to global positioning system (GPS) antennas, we recommend you use DO-160F section 21 category P or DO-160G section 21 categories P or Q, to reduce potential RF noise in the GPS band. For additional guidance on GPS equipment, refer to the latest revision of AC 20-138.
7. Using RTCA/DO-160 for Installers.
a. If you are an applicant installing equipment, you may use RTCA/DO-160, any version, to support compliance with the appropriate airworthiness requirements except as identified in paragraphs 7c, 7f, 7g, and 7h. When possible, we recommend that you use RTCA/DO-160G as it provides the most clear and complete test procedures.
b. Use the EQF provided by the equipment manufacturer to compare against your specific installation requirements. The EQF provides information regarding which version of DO-160 was used, which environmental tests were conducted and the environmental category of the equipment being tested. If the EQF categories do not adequately address your installation, then you or the equipment manufacturer may need to re-qualify the equipment to meet the appropriate sections and category levels.
c. When installing equipment previously qualified to other environmental standards, such as Military Standard (MIL-STD) 810G, the equipment must comply with applicable airworthiness requirements. You may use DO-160G to do a comparison analysis to show that it provides an equivalent level of safety in the expected operating environment.
d. When a new application is based on the design of an existing approved article, the applicant may ask to use environmental test data from the existing article’s environmental qualification, based on similarity between the two articles. This request must be fully supported with a detailed similarity assessment comparing the changes from the earlier approved article to 3
the article in the new application. The ACO may accept the data if the similarity assessment clearly shows that the design changes will not adversely affect the environmental qualification.
e. Some of the environmental conditions and test procedures contained in RTCA/DO-160 such as waterproofness, sand and dust, or salt fog, may not be applicable to your installation based on intended location of the equipment. You must determine which sections and categories are applicable to your specific project.
f. When the equipment installation is required to meet the HIRF requirements in §§ 23.1308, 25.1317, 27.1317, or 29.1317, use RTCA/DO-160F or G. RTCA/DO-160E is also acceptable to meet the HIRF requirements for level B and C systems when using test levels defined in the appropriate regulations as discussed in AC 20-158. For additional guidance on HIRF, refer to the latest revision of AC 20-158.
g. When the electrical/electronic equipment installations are required to meet lightning requirements, use RTCA/DO-160D or later. For additional guidance on lightning, refer to the latest revision of AC 20-136.
h. RTCA/DO-160F, Section 26, Fire, Flammability, is not sufficient for 14 CFR parts 25 and 33. RTCA/DO-160G, Section 26, is sufficient for 14 CFR part 25 but not for 14 CFR part 33. Fire and flammability guidance for 14 CF R part 33 is provided in the latest revision of AC 33.17-1.
8. How To Get Related Documents.
a. Order copies of RTCA documents from RTCA, Inc, 1150 18th Street, NW, Suite 910, Washington, DC 20036-4007, telephone (202) 833-9339, fax (202) 833-9434. You can also order copies online at http://www.rtca.org.
b. Order copies of 14 CFR parts from the Superintendent of Documents, Government Printing Office, P.O. Box 979050, St. Louis, MO, 63197-9000. For general information, telephone (202) 512-1800 or fax (202) 512-2250. You can order copies from the Government Printing Office website at http://bookstore.gpo.gov. Select “Code of Federal Regulations.”
c. View a list of all ACs on the FAA’s Regulatory and Guidance Library at www.rgl.faa.gov or from the website at www.faa.gov/regulations_policies/advisory_circulars/.
David W. Hempe Manager, Aircraft Engineering Division 4
Appendix 1 Appendix 1
Summary of changes between DO-160D, E, F, and G RTCA/DO-160 will continue to be subject to revisions as needs arise in the aviation community. However, it is not always feasible for an applicant to use the more current revision. The following table is a summary of the changes made from RTCA/DO-160C to D, D to E, E to F, and F to G. Versions of RTCA/DO-160 prior to RTCA/DO-160D are also not included in this table. The information in the table should help you determine if your new article should be subject to a particular version of RTCA/DO-160.
DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G Section 1-Section 3:
Purpose and Applicability, Definitions of Terms, and Conditions of Tests Editorial and clarifications changes only.
Section 3: The requirement for cumulative testing of Temperature, Altitude, Humidity, and Vibration was removed, and clarification was added with respect to the use of multiple test articles.
Added section 2.9, Applicability of Test Results and section 3.9, EUT Configuration for Susceptibility Tests.
Section 2: Clarification added with respect to applicability of lesser categories when equipment is qualified to a more severe category.
Section 3: Reference to paragraph
21.5 was removed. Clarification added on the use of special purpose software to place the equipment in its most susceptible mode.
Requirement added for operation of equipment in its most susceptible mode for all environmental tests, not just susceptibility tests.
Section 4:
Temperature and Altitude Section 4.3 Equipment Categories added reference categories for in-flight loss of cooling test.
Section 4.5 Temperature Test was restructured to include subsection 4.5.2 Operating Low Temperature.
Section 4.5.3 Ground Survival High Temperature Test and Short Term Operating High Temperature Test clarified soak time upon reaching short time operating low and high temperature. Section 4.5.5, In-Flight Loss of Cooling Test Clarified paragraph 4.5.1, Note 2 and paragraph 4.5.3, Note 2.
1 Includes Changes 1, 2, and 3 to RTCA/DO-160D.
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G in the note clarified cooling source and power.
Section 5: Section 5.3 Test Procedures Section 5.2 Temperature Change Sections, 5.3.1h, 5.3.2h, and Paragraph 5.1 – Added note Temperature was revised to provide Rates added two temperature 5.3.3i, changed the clarifying test intent and humidity Variation provisions for collecting data during a single cycle of test and reduced data collection under certain test conditions.
shock tests, categories S1 and S2, and Sections 5.3.2 and 5.3.3 are the tests sections that accompany the newly added categories, respectively.
performance compliance timing to be in the second, or last cycle.
control. Paragraphs 5.3.1a and d – added clarification of temperature change procedure for Operating Low and Operating High Temperatures.
Section 6: Editorial changes were made Section 6.3 was modified to In paragraphs 6.3.1, 6.3.2, and Corrected terminology paragraph Humidity to eliminate redundant description of the test procedures. Velocity of air throughout the exposure area changed from “Shall not exceed 0.75 m/s” to “Between
0.5 and 1.7 m/s”. Alternative method was added to measure the water pH.
allow a + 4 percent tolerance to the relative humidity requirement.
6.3.3 changed step 2 to 38 degrees to agree with corresponding figure.
6.3, removed word hydroxide.
Section 7: Equipment category Fixed wing and helicopter Category definitions were Added in Section 7.2.1 “Unless Operational definitions were added for operational and crash safety test revised for clarification. Text otherwise stated in the EUT Shocks and fixed wing and helicopter requirements were made the description and centrifuge specification, the equipment shall be Crash Safety installations. Crash Safety levels were identified for helicopters (20g) and increased for fixed wing crash safety levels (20g). Shock pulse was changed from half sine to saw tooth. Half-sine shock pulse curve changed to reflect saw-tooth profile. Test levels were changed from DO- 160C based on empirical data.
same. definitions were revised in section 7.3.3 and figure 7.3, respectively, to reflect the correct setup direction for acceleration load.
operating, and its temperature stabilized. Apply to the test item three shocks having a terminal sawtooth wave shape with an acceleration peak value of six (6) g's in each orientation."
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G Section 8:
Vibration New section defining vibration requirements for helicopters was added.
Random vibration levels were changed by the addition of new curves. Tables and figures were modified to support changes in test levels.
Fixed Wing Zone 2 features two new test curves. High Level Short Duration Category Test was revised. Helicopter endurance test times were reduced and the unknown helicopter test procedure was reconfigured (Category U).
Unknown helicopter test procedure (Category U2) was added as an alternative to revision D.
Performance test times were reduced from 30 minutes to a minimum of 10 minutes.
Robust test equipment operating, not operating requirements were standardized to have equipment not operating during sinusoidal scans and operating during the robust test portion of the test, unless specified otherwise by the applicable equipment specifications.
Deleted in section 8.8 "Caution should be exercised regarding wear /damage occurring during the tests to DZUS (c) fasteners or other flexible mounting devices."
Editorial change "Repeat the sinusoidal scan of subparagraph
8.8.1.3.a."
Section 9: Fuel mixture calculation was Minor changes were made in the Environment definition and The environment descriptions are Explosion corrected for hexane explosive procedure to improve category definitions were improved and category description Proofness proofness test. Atmospheric repeatability. revised. Reference to 100/130 details are moved to the users guide.
test pressure requirements octane fuel was deleted from The sensor for determining the were clarified. figure 9-4. explosiveness of the environment is changed from a spark plug or glow plug to a pressure sensor or thermocouple. Also, the containment test was changed such that if the test case volume is greater than 1/50 of chamber volume an alternative to purging entire chamber would be to prove explosive mixture is correct after each case explosion.
Section 10: Test step that verifies absence Minor improvements to pre-heat Drip Rate was changed from In Figure 10-1, the 75 mm height of Waterproofness of water penetration into test unit and to reduce risk of 280 l/m2/hr to 140 l/m2/hr. water annotation is superseded by a unit following test was deleted thermal shock were made. new note that states the volume of because it was not consistent water emitted from the drip table with intent and purpose of test. must be pre and post calibrated and The test is intended to verify the level of water in the drip table performance of unit following noted.
exposure to this environment, not to verify the unit’s ability A-3
Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G to keep out water.
Section 11: Table 11-1 eliminated Updated list of fluids and added No changes were made. Added 2 new fluids - Cleaning fluid Fluids reference to fire inspection. - 1-2 Dichloroethlene; and Fire Susceptibility extinguishants and add additional de-icing fluid, propylene glycol. Aircraft fire extinguishants are gaseous and do not exist in liquid form under normal conditions. Deicing fluid added to reflect current industry practices.
extinguishant, Aqueous Film Forming Foam (ATTF) to fluids list.
Changed spray test to align with MIL STD 810G - spray 8 hours, followed by 16 hours of drying, repeated 3 times. Change operation of unit while wet after 24 hour spray to while wet at end of third 8-hour spray segment, and third change requirement of operation of unit at end of each fluid drying period from 2 hours to 30 minutes minimum or unit stabilized.
Section 12: Editorial and clarifications Sand and dust were separated Category definitions were Change sand composition particle Sand and Dust changes only. into two categories. Update the mixtures to current commercial available characteristics.
revised for clarification.
Additional sand concentrations were added.
Size distributions and sum of total percentages to 100% were adjusted in Section
12.3.2.
size to meet MIL STD 810G requirements.
Section 13: Section 13.5.7 was revised to Other causes of fungus other Magnesium sulfate was No changes were made.
Fungus eliminate 48 hour period after than nutrient materials and adjusted to align with other Resistance removal from chamber before performance test.
personnel safety caution were added.
Test failure criteria were clarified.
ingredients.
Section 14: Change functional test criteria. Title of section was changed Changed term Salt Spray to Add alternating periods of exposure Salt Fog Functional test may now be performed following 48 hour dry-out period.
from Salt Spray to Salt Fog.
Category T was added for severe salt atmosphere.
Salt Fog throughout this section.
and drying. Suppress the drying before power up for Category T.
Section 15:
Magnetic Effect Text was added to clarify source of referenced magnetic Section 15.3 was modified to provide a more detailed test A new Category Y was added for measurements made Added user’s guide and updated figure 15-1.
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G field. procedure than in previous versions, including a requirement to verify field uniformity if the compass must be moved to change the measurement distance to the EUT (equipment under test). The new Figure 15-1 provides a test setup diagram and gives notes on proper performance of the test.
immediately adjacent to the unit under test. Descriptions of each equipment category were added to Section 15.1 Purpose of Test along with discussion of how the test results are used to determine how close the EUT may be installed to a compass or compass sensor. Text allowing the measurements to be made with an uncompensated compass or equivalent magnetic sensor was also added.
Section 16: Change 2 to DO-160D, The entire section was re- More tests are required for Added alternate test "Z" for ac Power Input published June 12, 2001, revised Section 16, by including new tests, and modifications to existing testing, to address the issues of AC harmonic current content and variable frequency AC power systems.
ordered so that all the AC tests were in one subsection and all DC tests were in another subsection, making Section 16 easier to use and understand.
DO-160E also introduced some new tests, such as a DC content test for AC powered equipment, and a new subsection covering "Load Equipment Influence on Aircraft Electrical Power Systems."
both AC and DC powered equipment. A 270V DC bus generated from the A (WF) AC power bus was added as Category D. Discrete step test methods were defined for AM and FM modulation on AC systems. AM voltage modulation on AC buses was increased. Double interrupt test methods were added for DC equipment. Manual reset was explicitly not permitted after single and double power interrupts. The dwell at 28V between the short and the long dc voltage surge was removed.
Loss of phase testing was added for three phase. A Power Factor test designation was added for ac equipment.
DC current draw tests from inrush tests. Clarified peak current definition in inrush testing. Allow performance of emergency limits for Category A(CF) equipment to constitute performance of normal (part c.(1)) test conditions. Allow performance of emergency limits to constitute performance of normal (part b.(2)) test conditions. Added equipment with analog circuitry to be tested with the test conditions of Table 16-1 and Table 16-3.
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G AC equipment current were added. In-rush and current modulation test designations were added for both AC and DC equipment. Tolerances were added to most tests.
Category H, harmonic emissions, measurement methods were updated.
Section 17: Editorial changes were made No significant changes were Section 17.4 Test Procedures Editorial changes only.
Voltage Spike to support document consistency. Reference to "DC only" condition was eliminated thereby expanding applicability to both AC and DC systems. Figures were modified to accommodate the inclusion of AC power systems. Reference to negative pulse generation network was eliminated.
made. was modified to clarify application of positive and negative transients over the specified period of time. Test conditions were clarified when multiple power pins are present.
Section 18: DO-160C referenced Figures The equipment category New test for 270V dc input Changed secondary limit from a Audio Frequency 16-4 and 16-5 for DC ripple designators A and J were differential ripple to follow 1000W power limit to a 36A (pk- Conducted test requirements; these eliminated, and categories R and same curve as 28V Category pk) current limit. Added user’s Susceptibility- figures were moved to Section K were added. Z, but at 4 times the amplitude guide and moved appropriate Power Inputs 18 as Figures 18-2 and 18-3. was added. A common mode noise test has been added for 270V Category Z equipment.
For test equipment that generate a continuous linear frequency sweep, the minimum (i.e., fastest) sweep rate has been slowed to make swept testing equivalent to stepped testing, especially at resonances. An optional DC blocking network is added to the test setup figures to material to the guide. Corrected minor issues in existing figures.
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G prevent damage to the signal source.
Section 19: Category C was added to A second equipment category Clarification to existing Clarified that power leads are tested Induced Signal include test levels that are designator was added to indicate formula used to calculate test per section 18. Clarified radiating Susceptibility appropriate for installations with long wire runs or minimum wire separation.
The test levels for magnetic and electric fields induced into wiring were increased.
the AC power system operating frequency (Constant, Narrow Variable, or Wide Variable).
The frequency scan rate was changed to 30 steps per decade, with a 10-second dwell time at each frequency.
frequencies was made. wire orientation for “Magnetic Fields Induced Into the Equipment” test. Added “Electric Fields Induced Into the Equipment” test.
This test is similar to the existing “Magnetic Fields Induced Into the Equipment” test, using an opencircuit wire radiator. This change caused paragraph re-numbering within this section, including those paragraphs of existing tests.
Clarified source wire routing (spiral vs. parallel) relative to bundle under test.
Section 20: The revisions to Section 20, in A section providing guidance Test categories were reduced Indicated that section categories are Radio Frequency DO-160D Change No.1, and caution related to RF power and “alternative” modulations appropriate for Transmitting Susceptibility published December 2000, amplifier harmonics and their for Category R were Portable Electronic Device.
(Radiated and include a new, Mode-Tuned, potential to affect the test results eliminated. There is now only Clarified that power lines may, but Conducted) Reverberation Chamber Radiated RF Susceptibility test method. New categories (test levels) were also added to Section 20, including Category L, which requires Radiated RF Susceptibility testing (pulsed) as high as 7200 volts/meter.
An alternate procedure was added for mode-stirred radiated susceptibility tests.
The mode-stirred procedure was accepted as an alternate that may require lower-power was added, along with a revision that allows the use of an oscilloscope to measure Conducted Susceptibility test levels. The Mode-Tuned test method for Radiated Susceptibility was modified to allow for the option of using the received power on the monitor antenna to determine the test level, as opposed the E-field readings from a 3-axis sensor.
Flexibility in the number of tuner steps was also added, giving the user the choice of increasing the number of steps one test method for conducted susceptibility. Clarification has been added regarding the requirement to expose all apertures and openings of the EUT in anechoic chamber method. RTCA/DO-160F added requirements to test several additional dwell frequencies where the image frequencies for n =2 through
10. 160F removed the permissive language associated with these tests. It used to be “should” but 160F now uses “shall”.
are not required to, be routed with interconnect wiring, unless this conflicts with aircraft installation specifications. Indicated that the radiating antenna may be placed further than 1 meter from EUT.
Significant change to reverberation chamber testing made by replacing “Mode Tuning” test technique with “Mode Stirring” technique.
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Appendix 1 DO-160 Sections Changes from DO-160C to DO-160D1 Changes from DO-160D1 to DO-160E Changes from DO-160E to DO-160F Changes from DO-160F to DO-160G amplifiers. based on the need for greater field uniformity or a higher test level, or decreasing the number of tuner steps to decrease the test time.
Section 21:
Emission of Radio Frequency Energy Change Category Z requirements to reflect need for additional scrutiny in the VHF COM NAV and GPS frequencies.
All of the figures were cleaned up and made easier to read. The Radiated Emissions limits for Categories M and H were modified slightly so that the notches that occur in various frequency ranges now have sloped bottoms to match the rest of the limit. The frequency range of the first notch has also been changed for a more precise match with the communications/navigation frequency range that the notch protects.
The conducted emissions frequency range has been broadened to 150 kHz - 152 MHz, and the Radiated Emissions test frequency range has been narrowed to 100 MHz - 6 GHz. A new procedure for radiated emissions measurements in a reverberation chamber was added. In the anechoic chamber method, clarification has been added regarding the requirement to expose all apertures and openings of the EUT. A new limit category has been added, Category P, to provide added protection for certain receivers by use of even deeper notches than previously used.
Added optional in-line low noise preamp to diagrams in Fig. 21-11, Fig. 21-12, and Fig. 21-13 per description in Table 1, Note 1.
Corrected values at 152 MHZ notch points, 37.5dB in Fig. 21-8, 27.5 dB in Fig. 21-9, and 27.5 dB in Fig.
21-10. Added acronym definitions for GPS and GNSS at first occurrence of acronym in Section
21. Added verbiage in Section 21 User Guide discussing the use of equivalent dipole directivity in formula found in Section 21.6.3.i.
Revised Figure 21.6 and 21.11 to show bends in the cable bundle as it exits the EUT. Revised frequency ranges in Table 1: 100 kHz bandwidth upper frequency limits =
0.4 - 0.96 GHz and 1 MHz bandwidth lower frequency limits =
0.96 – 6.0 GHz. Revise Note 1 to Table 1 to eliminate the option to use an uncorrected 10 kHz bandwidth in the measurement of category M & H emission notches above 960 MHz. Substituted a new Note 1 which recommends use of a low noise preamplifier if necessary to achieve sufficiently low measurement noise floor in the notches. Added Category Q.
Revised Paragraph 21.2 to include A-8