AC 20-167B Appendix B B.8.2 Confirm that landing rollout information, if provided in the display, is sufficiently visible to the pilot and does not cause over-control or oscillations in acquiring and maintaining the required ground track.
B.8.3 For EFVS approach systems, assess the transition to natural vision and compatibility of the guidance when following the HUD/EFVS approach system flight cues.
B.8.4 The EFVS landing system should be evaluated to ensure that the system provides:
• A smooth transition through flare to landing;
• Approach, flare, and landing at a normal sink rate for the aircraft;
• Have display characteristics, dynamics, and cues that are suitable for manual control of the aircraft to touchdown in the touchdown zone of the runway of intended landing and during rollout;
• Touchdown within the touchdown zone and that the lateral touchdown performance should be demonstrated to be no worse than that achieved in visual landings for the specific aircraft;
• Prompt and predictable correction of any lateral deviation away from the runway centerline to smoothly intercept the centerline;
• Touchdowns with a bank angle that is not hazardous to the airplane;
• Demonstrated performance of the installed EFVS landing system at the representative RVR/visibility, as described in this document, will determine any additional limitations (for example, crosswind and offset);
• A normal de-rotation rate;
• Satisfactory and smooth control of the airplane from touchdown to a safe taxi speed; and
• Satisfactory and smooth control of the path of the airplane along the runway centerline through rollout to a safe taxi speed.
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AC 20-167B Appendix B B.9 Rejected Landing.
Confirm that at any time during the EFVS operation, a rejected landing can be safely conducted in all configurations to be approved.
B.10 Pilot Monitoring (PM) Display Steps.
B.10.1 Display Location.
B.10.1.1 EFVS Approach Systems.
A PM display is not required by the FAA for operations within the United States. However, if one is installed, the applicant should assess the ergonomic aspects of the image on the copilot’s EFVS approach system monitor.
B.10.1.2 EFVS Landing System.
Section 91.176(a) requires a PM display. Under §§ 23.2500, 23.2610,
25.1321, 27.1321, 29.1321, verify that the display’s location meets the certification requirement and any symbology displayed does not adversely obscure the sensor imagery of the runway environment.
B.10.2 Verify satisfactory display of imagery in all lighting and environmental conditions and that dimming controls of the display are adequate.
B.10.3 If the display has dual purposes, verify that the means of switching the display to the EFVS approach system monitor and back is satisfactory and clearly evident.
B.10.4 Verify no unacceptable flicker and/or jitter in the display.
B.10.5 Verify that no objectionable glare or reflections are generated by the display or are visible in the display.
B.10.6 Verify that the co-pilot’s use of the EFVS approach system monitor does not require undue head/body movement away from their normal scan pattern or their normal seated position.
B.10.7 If the PM display is a HUD or equivalent display, verify that the PM display provides a conformal image with the visual scene over the range of aircraft attitudes and wind conditions for each mode of operation.
B.10.8 The PM display should be shown to be acceptable for the pilot monitoring to see and identify visual references and verify that all visual requirements for the approach and/or landing are satisfied.
B-8
AC 20-167B Appendix B B.11 Failure Cases.
Failure cases to support the FHA should be assessed and tested as required, for example, uncommanded full image brightness, misaligned image, frozen image, etc.
during the approach testing specified in this appendix.
B.12 Ice Protection System Evaluation.
B.12.1 If the EFVS approach system sensor installation has ice protection capability, the EFVS image should be evaluated with the ice protection on and off in representative environmental conditions.
B.12.2 Icing of the sensor fairing/radome should be appropriately assessed in accordance with the approved flight envelope.
B.13 Flight Test Evaluation Matrix.
The flight test evaluation matrix is a table of recommended aspects of the EFVS installation that should be evaluated during the flight test program. The applicant should propose a flight test evaluation matrix that is suitable for the applicant’s specific EFVS installation. As a starting point, Table B-1 contains the recommended minimum flight test evaluation matrix for all EFVS installations. Table B-2 contains the recommended minimum supplemental test evaluations specific to EFVS landing systems.
B-9
AC 20-167B Appendix B Table B-1. EFVS Flight Test Evaluation Matrix
A Confirm flightcrew workload is not adversely affected by the EFVS installation.
B Verify no adverse physiological effects from using the EFVS (for example, fatigue, eye strain).
C Verify EFVS symbology is visible within pilot field of view (FOV). (When viewed by both eyes from any off-center position within eye box, non-uniformities should not produce perceivable differences in binocular view.)
D Verify no unacceptable jitter or flicker of EFVS symbology/image.
E Verify that the EFVS image does not have noise, local disturbances or artifacts that distract from the use of the system.
F If HUD symbology has been modified to accommodate the EFVS image, assess HUD guidance and ensure that introduction of EFVS does not induce lag in control symbols inducing p ilot induced oscillation (PIO).
G Verify the system is not adversely affected by aircraft maneuvering or changes in attitudes encountered during the referenced environmental conditions.
H Ensure that the required flight and navigation functions applicable for the phase of flight being evaluated are clearly displayed on the HUD with no unacceptable occlusions during testing.
I Verify that the total data presented by the EFVS imagery and HUD symbology does not over clutter the HUD combiner display area.
J Assess the degree of obscuration of the pilot’s outside view or field of view through the flightdeck window as a result of EFVS imagery and HUD symbology.
K Confirm the pilot’s ability to detect hazards, maneuver, avoid traffic, terrain or other obstacles, is not impaired or degraded by the display of EFVS imagery.
L Confirm that there is no discrepancy between the conformal HUD symbols, sensor image, and the outside view through the flightcrew’s windows.
M Verify that outside visibility as viewed through combiner sensor imagery is adequately aligned and conformal to the external scene and HUD symbology.
N Confirm that the EFVS imagery does not obscure the desired imagery of the scene, impair the pilot’s ability to detect and identify visual references, mask flight hazards, or distract the pilot.
O Assess the ease of operating the HUD with the sensor image displayed, during aircraft maneuvers and change in attitude encountered in normal operations.
P Determine whether there is any glare or reflection that could interfere with the EFVS image either in day or night lighting conditions.
Q Determine if any impairment is experienced in the ability to use the display due to visible external surfaces within the HUD.
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AC 20-167B Appendix B
R Determine whether the sensor image displayed on the HUD combiner objectionably impairs the pilot compartment view.
S Assess impact of water droplets running across the sensor window to ensure that it does not distract the pilot or degrade their task performance or safety.
T Verify that the enhanced flight visibility provided by the EFVS is greater than the instrument approach procedure minimums and required visual references are clearly identifiable with the EFVS at DA/DH or MDA.
U Confirm that the EFVS image is suitable and performs its intended function.
V Confirm that the sensor image on the pilot monitor display (if installed) is useable and performs its intended function.
W Evaluate the EFVS approach system image during the takeoff roll and throughout the climb segment against the attributes listed in the attached fight test evaluation matrix.
X During vertical and lateral guidance maneuvers, evaluate the EFVS image against the attributes listed in the pilot evaluation matrix.
Z Evaluate the EFVS using all available HUD modes and/or declutter options as appropriate for the phase of flight and condition.
B-11
AC 20-167B Appendix B Table B-2. EFVS Landing System Supplemental Flight Test Evaluation Matrix
A Confirm that the EFVS provides the correct and appropriate visual cues for the pilot to perform the required stabilized approach from the DA/DH.
B Confirm that approach speed can be controlled within +10/-5kts, both with and without autothrottle if fitted, up to the point where the throttles are retarded for landing.
C Confirm that the EFVS provides the correct visual cues for the pilot to perform a smooth transition through flare to landing.
D Confirm that the EFVS provides the correct visual cues for the pilot to perform a flare and landing with a normal sink rate.
E Confirm that the EFVS provides the correct visual cues to always allow a consistent touchdown in the defined touchdown zone.
F Confirm that the EFVS provides the correct visual cues to allow a consistent touchdown with a bank angle that is not hazardous to the airplane.
G Confirm that the EFVS provides the correct visual cues to allow normal derotation rate.
H Confirm that EFVS provides the correct visual cues to allow satisfactory and smooth control of the airplane from touchdown to a safe taxi speed.
I Confirm that the EFVS provides the correct visual cues to allow prompt and predictable correction of any lateral deviation away from the runway centerline to smoothly intercept the centerline.
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AC 20-167B Appendix C APPENDIX C. DETERMINING QUANTIFIED VISUAL ADVANTAGE C.1 Introduction.
Demonstrating a quantified visual advantage is not required for the installed EFVS to be approved. However, any operator that uses the installed EFVS to dispatch the aircraft in accordance with § 121.613, § 125.361, or § 135.219, or to commence an instrument approach under § 121.561, § 125.325, § 125.381, or § 135.225 requires an operational approval from the FAA’s Flight Standards Service. For the operator to receive the required operational approval, the applicant must demonstrate and document a quantifiable measure of the EFVS visual advantage performance.
C.2 Quantified Visual Advantage Test Plan.
For determination of visual advantage, a data set demonstrating in-flight the relationship between slant range flight visibility and slant range enhanced flight visibility (visual advantage) with the reported visibility should be created and analyzed.
C.2.1 RTCA DO-390/EUROCAE ED-291, Test Procedures for Quantitative Visual Advantage.
Provides an industry consensus methodology for testing and documenting the quantitative visual advantage provided by the installed EFVS. The methodology in DO- 390/ED-291 has been deemed to be acceptable to FAA Flight Standards for the purposes of documenting the performance of the installed EFVS and supporting applications for operational approvals.
C.2.2 Alternate Methods.
An applicant may propose alternate methods of measuring and documenting the quantified visual advantage of the system. Should the applicant propose an alternate method to test the visual advantage for the installed EFVS, it is recommended that the applicant coordinate with the FAA’s Flight Standards Service to ensure that the results of the proposed quantitative visual advantage testing will be sufficient to support an operator’s application for operational approvals.
C-1
AC 20-167B Appendix D APPENDIX D. SA MPLE AIRPLANE FLIGHT MANUAL (AFM) SUPPLEMENT D.1 Introduction.
Appendix D presents a sample below for the AFM supplement for Supplemental Type Certificate (STC) installations. This example may not be entirely applicable to airplane manufacturers when EVS, CVS, or EFVS are approved with the type certificate. The AIR certification branch will assist the applicant in developing an appropriate RFMS.
Installation Center/Repair Station Model XXX EVS/EFVS 123 Fourth Street Vision System Anytown, USA
FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
ABC MODEL XXX YYY VISION SYSTEM AIRPLANE MAKE:
AIRPLANE MODEL:
AIRPLANE SERIAL NO.:
REGISTRATION NO.:
This document must be carried in the airplane at all times. It describes the operating procedures for the ABC Model XXX YYY vision system when it has been installed in accordance with <manufacturer's installation manual number and date>.
For airplanes with an FAA-approved airplane flight manual, this document serves as the FAA Approved ABC Model XXX YYY Flight Manual Supplement. For airplanes that do not have an FAA-approved flight manual, this document serves as the FAA Approved ABC Model XXX YYY Supplemental Flight Manual.
The information contained herein supplements or supersedes the basic airplane flight manual dated <insert date> only in those areas listed herein. For limitations, procedures, and performance information not contained in this document, consult the basic airplane flight manual.
FAA-APPROVED ____________________ Title Office Federal Aviation Administration City, State D -1
AC 20-167B Appendix D APPENDIX D. SAMPLE AIRPLANE FLIGHT MANUAL (Continued) Installation Center/Repair Station Model XXX EVS/EFVS 123 Fourth Street Vision System Anytown, USA Table of Contents
SectionPage
1 General.............................................< > 2 Limitations........................................< > 3 Emergency/Abnormal Procedures....< > 4 Normal Procedures...........................< > 5 Performance......................................< > 6 Weight and Balance..........................< > 7 System Description...........................< > FAA Approved Page <> of <> Date: ________ D-2
AC 20-167B Appendix D APPENDIX D. SAMPLE AIRPLANE FLIGHT MANUAL (Continued) Installation Center/Repair Station Model XXX EVS/EFVS 123 Fourth Street Vision System Anytown, USA SECTION 1 - GENERAL <Include the appropriate statement to describe the equipment capability:> EVS: The installed ABC Enhanced Vision System meets the regulatory requirements and performance criteria as described in AC 20-167B for <situation awareness>.
CVS: The installed ABC Combined Vision System meets the regulatory requirements and performance criteria as described in AC 20-167B for <situation awareness>.
EFVS Approach System: The demonstrated visual advantage of the installed <Manufacture, Model #> EFVS landing system meets applicable requirements as described in AC 20-167B for EFVS operations to 100 feet above the touchdown zone and is eligible for operational credit in accordance with the operator’s specific EFVS approvals.
Note: The <Manufacture, Model #> EFVS landing system does not provide a visual advantage when viewing LED lighting EFVS Landing System: The demonstrated visual advantage of the installed <Manufacture, Model #> EFVS landing system meets applicable requirements as described AC 20-167B for EFVS operations to touchdown and roll out and is eligible for operational credit in accordance with the operator’s specific EFVS approvals.
The maximum final approach offset angle satisfactorily demonstrated during certification flight test was <insert angle in degrees>.
Note: The <Manufacture, Model #> EFVS landing system does not provide a visual advantage when viewing LED lighting.
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AC 20-167B Appendix D APPENDIX D. SAMPLE AIRPLANE FLIGHT MANUAL (Continued) SECTION 2 - LIMITATIONS
1. The system must utilize software version <insert version identification>.
2. A valid and compatible database must be installed and contain current data.
3. <Specify any additional limitations applicable to the particular installation.> FAA-Approved Page <> of <> Date: ________ SECTION 3 - EMERGENCY/ABNORMAL PROCEDURES
EMERGENCY PROCEDURES No Change
ABNORMAL PROCEDURES
1. If ABC Model XXX YYY vision system information is not available or is invalid, utilize remaining operational navigation equipment as appropriate.
2. If “Loss of Integrity Monitoring” message is displayed, revert to an alternate means of navigation appropriate to the route and phase of flight, or periodically cross-check the global positioning system (GPS) guidance to other, approved means of navigation.
SECTION 4 - NORMAL PROCEDURES
1. Normal operating procedures are outlined in the ABC Model XXX YYY Pilot's Guide.
2. System Annunciators <applicable to installations with external annunciators>.
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AC 20-167B Appendix D APPENDIX D. SAMPLE AIRPLANE FLIGHT MANUAL (Continued)
3. System Switches <applicable to installations with external switches>.
4. Pilot's Display <describe the pilot's display(s)>.
5. Flight Director/Autopilot Coupled Operation <describe any procedures for integrated flight director and/or autopilot system(s)>.
6. <Include any other normal operating procedures as necessary.> FAA-Approved Page <> of <> Date: ________ SECTION 5 - PERFORMANCE No Change SECTION 6 - WEIGHT AND BALANCE <Refer to revised weight and balance data, if applicable.> SECTION 7 - SYSTEM DESCRIPTION <Provide a brief description of the system, its operation, installation, etc.> FAA-Approved Page <> of <> Date: ________ D-5