Appendix E E-6 E.10.2 Verify satisfactory display of imagery in all lighting and environmental conditions and that dimming controls of the display are adequate.
E.10.3 If the display has dual purposes, verify the means of switching the display to being the EFVS Landing System monitor and back is satisfactory and clearly evident.
E.10.4 Verify that the pilot monitoring use of the PM display monitor does not require undue head/body movement away from his/her normal scan pattern or his/her normal seated position.
E.10.5 Verify 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. The PM’s display should be shown to be acceptable for the pilot monitoring to see and identify visual references and to verify that all visual requirements for the approach and landing are satisfied.
E.11 Failure Cases.
Failure cases to support the FHA shall be assessed and tested as required (e.g., uncommanded full image brightness, misaligned image, frozen image, failed image, etc.) during the approaches required in this appendix.
E.12 Ice Protection System Evaluation.
E.12.1 If the EFVS Landing System sensor installation has ice protection/de-misting capability, the EFVS Landing System image should be evaluated with the ice protection/de-misting on and off in representative environmental conditions.
E.12.2 Icing of the sensor fairing should be appropriately assessed in accordance with the aircraft’s certified flight envelope.
E.13 Evaluation Matrix Table 7 below is the test evaluation matrix that should be used to support the testing described above. Additional evaluation points may be added to the test program depending on particular features and intended functions of the actual system being certified.
Table 7. EFVS Landing System Evaluation Matrix EFVS Landing System Evaluation Matrix A Confirm that crew workload is not adversely affected by the HUD/EFVS Landing System installation.
Appendix E E-7 EFVS Landing System Evaluation Matrix B Verify no adverse physiological effects from using the HUD/EFVS Landing System
(e.g. fatigue, eye strain).
C Verify HUD/EFVS Landing System symbology is visible within pilot Field of View (FOV). (When viewed by both eyes from any off-center position within eye box, nonuniformities shall not produce perceivable differences in binocular view.)
D Verify no jitter or flicker of HUD/EFVS Landing System symbology/image.
E Verify that the EFVS Landing System 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 Landing System image, assess HUD guidance and ensure that introduction of EFVS Landing System does not induce lag in control symbols inducing 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 Landing System imagery and HUD symbology does not over clutter the HUD combiner display area.
J Assess the degree of obscuration of the pilots outside view or field of view through the cockpit window as a result of EFVS Landing System imagery and HUD symbology.
K Confirm that the pilot’s ability to detect hazards, maneuver, avoid traffic, terrain, or other obstacles, is not impaired or degraded by the display of EFVS Landing System imagery.
L Confirm that there is no discrepancy between the conformal HUD symbols, sensor image and the outside view through the windshield.
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 Landing System 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.
Appendix E E-8 EFVS Landing System Evaluation Matrix P Determine whether there is any glare or reflection that could interfere with the EFVS Landing System image external surfaces within the HUD.
Q Determine if any impairment is experienced in the ability to use the display due to visible external surfaces within the HUD.
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 his/her task performance or safety.
T Verify identification of approach lights, runway threshold, touchdown zone etc. as per 14 CFR § 91.176(a)(3).
U Confirm that the HUD EFVS image is suitable and performs its intended function.
V Confirm the sensor image on the copilot’s display is useable and performs its intended function.
W Evaluate the EFVS image during the takeoff roll and throughout the climb segment, against the attributes listed in evaluation EFVS Landing System Evaluation Matrix.
X During vertical and lateral guidance maneuvers evaluate the EFVS image against the attributes listed in the EFVS Landing System Evaluation Matrix.
Y Confirm that the EFVS provides the correct and appropriate visual cues for the pilot to perform the required stabilized approach from the DA(H).
Z Confirm that approach speed can be controlled within +10/-5kts, both with and without auto-throttle if fitted, up to the point where the throttles are retarded for landing.
AA Confirm that the EFVS provides the correct visual cues for the pilot to perform a smooth transition through flare to landing.
AB Confirm that the EFVS provides the correct visual cues for the pilot to perform a flare and landing with a normal sink rate.
AC Confirm that the EFVS provides the correct visual cues to always allow a consistent touchdown in the defined touchdown zone.
AD 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.
AE Confirm that the EFVS provides the correct the correct visual cues to allow normal
Appendix E E-9 EFVS Landing System Evaluation Matrix derotation.
AF Confirm that EFVS provides the correct visual cues to allow satisfactory and smooth control of the airplane from touchdown to a safe taxi speed.
AG 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.
AH Confirm that the EFVS provides the correct visual cues to allow satisfactory and smooth control of the path of airplane along the runway centerline through rollout to a safe taxi speed before reaching the stop at the end of the runway.
Appendix F F-1 APPENDIX F. SAMPLE AIRPLANE FLIGHT MANUAL (AFM) SUPPLEMENT Note: Appendix F presents a sample for the AFM supplement for STC installations.
This example may not be entirely applicable to airplane manufacturers when SVS, EVS, CVS, or EFVS are approved with the type certificate. The ACO will assist the applicant in developing an appropriate Rotorcraft Flight Manual Supplement (RFMS).
Installation Center/Repair Station Model XXX EVS/SVS/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 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
Appendix F F-2 SAMPLE AIRPLANE FLIGHT MANUAL (Continued)
Installation Center/Repair Station Model XXX EVS/SVS/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: ________
Appendix F F-3 SAMPLE AIRPLANE FLIGHT MANUAL (Continued)
Installation Center/Repair Station Model XXX EVS/SVS/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 with AC 20-167A performance criteria for <situation awareness>.
SVS: The installed ABC Synthetic Vision System meets with AC 20-167A performance criteria for <situation awareness>.
EFVS Approach System: The demonstrated performance of the installed EFVS Approach System meets the criteria of AC 20-167A for EFVS operations conducted in accordance with 14 CFR § 91.176(b).
During certification flight test, the maximum final approach course offset angle at which the installed EFVS was demonstrated to be used in lieu of natural vision to descend below DA/DH or MDA and complete a landing in accordance with 14 CFR § 91.176(b) was <insert angle in degrees>.
<For aircraft that are to be operated under 14 CFR part 121, 125, or 135 should include the statement below that describes the performance of the EFVS Approach system demonstrated during the certification test program.> The installed EFVS Approach System demonstrated satisfactory approaches in the weather conditions listed below:
<Insert summary statement describing the sensor performance and the lowest visibilities and applicable environmental conditions for which the EFVS Approach System has demonstrated satisfactory landing in accordance with 14 CFR § 91.176 (b).>
EFVS Landing System: The demonstrated performance of the installed EFVS Landing System meets the criteria of AC 20-167A for EFVS operations conducted in accordance with 14 CFR § 91.176(a) in visibility conditions sufficient to safely complete the rollout without EFVS function. The demonstrated performance of the installed EFVS also meets the criteria of AC 20-167A for EFVS operations to 100 feet above the TDZE conducted in accordance with 14 CFR § 91.176(b).
Appendix F F-4 The maximum final approach offset angle satisfactorily demonstrated during certification flight test was <insert angle in degrees>.
The installed EFVS Landing System demonstrated satisfactory landings in the weather conditions listed below:
<Insert summary statement describing the sensor performance and the lowest visibilities and applicable environmental conditions for which the EFVS Landing System has demonstrated satisfactory landing in accordance with 14 CFR § 91.176 (a).>
SECTION 2 - LIMITATIONS
1. The ABC Model XXX YYY Quick Reference Guide, P/N <insert part number>, dated <insert date> (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
2. The system must utilize software version <insert version identification>.
3. A valid and compatible database must be installed and contain current data.
4. <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 invalid, utilize remaining operational navigation equipment as appropriate.
Appendix F F-5
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 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>.
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: ________
Appendix F F-6
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: ________
Appendix G G-1 APPENDIX G. INSTALLATION OF ENHANCED VISION SYSTEM AND OR/SYNTHETIC
VISION SYSTEM ON ROTORCRAFT G.1 General.
This appendix provides guidelines for the installation of EVS and/or SVS installed in Rotorcraft as non-required safety enhancing equipment. To promote standardization installation of non-required safety enhancing equipment, a policy memo was published to address a means of compliance for the installation of non-required safety enhancing equipment. Contact the appropriate FAA office responsible for rotorcraft standards for guidance. Also refer to AC 27-1B and AC 29-2C for certification guidance.
G.2 Applicability.
There are unique aspects to rotorcraft that do not apply to fixed wing aircraft.
Rotorcraft typically operate at altitudes much closer to the ground and obstacles than fixed-wing aircraft. Additionally, they are inherently unstable and, without a stabilization system, require hands-on control at all times accompanied by constant visual scans to keep them oriented correctly. There are advantages and disadvantages to presenting EVS or SVS information to the pilot. Particular issues of concern are the compelling nature of the display used in a VFR see-and-avoid environment, the presentation of misleading information relating to aircraft location relative to hazards (particularly in night operations), and the installation of EVS/SVS/CVS displays that interact with automated flight control systems and flight guidance systems.
G.3 Airworthiness Approval.
For rotorcraft, the FAA has determined that installation of EVS/SVS/CVS on a primary flight display, either ADI or NAV display, requires ACO involvement through the STC process, under FAA Order 8900.1, Volume 4, Chapter 9 “Selected Field Approvals,” Figure 4-68, Major Alterations Job Aid. Installations on a primary flight display will involve human factors evaluations and flight test evaluations.
G.4 Design Considerations.
The FHA developed for the system should define the hazards of presenting misleading information to the pilot, and loss of an SVS/EVS feature. The system should be designed accordingly. The hazard classification will be based on display location, intended function of the system features, and phase of flight. The hazard classification of misleading information for SVS/EVS/CVS on the primary flight displays will be higher than the classification of misleading information on a display outside the pilot’s primary field of view. For example, the hazard classification of misleading information may be lower if the SVS/EVS/CVS is placed on ancillary displays not used for the display of flight information and not in the pilot’s primary field of view. Additionally, see Appendix H of this AC for further guidance. However for rotorcraft the FAA does not accept “situation awareness only” information on primary flight displays (either
Appendix G G-2 PFD or MFD’s within the pilot’s primary field of view). Therefore the intended function of the SVS/EVS/CVS should be defined. If HTAWS or HTAWS-like features are incorporated, see TSO-C194 HTAWS