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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 25
Docket ID: [Docket No. NM349; Special Conditions No. 25-319-SC]
NOTICE: RULES
ACTION: Airworthiness standards:
DOCUMENT ACTION: Final special conditions; request for comments.
SUBJECT CATEGORY: Special Conditions: Dassault Aviation Model Falcon 900EX and Falcon 2000EX Airplanes; Enhanced Flight Visibility System (EFVS)
DATES: The effective date of these special conditions is July 7, 2006. We must receive your comments by September 1, 2006.
DOCUMENT SUMMARY: These special conditions are issued for certain Dassault Aviation Model Falcon 900EX and Falcon 2000EX airplanes. These airplanes will have an advanced enhanced flight visibility system (EFVS). The EFVS is a novel or unusual design feature which consists of a head up display (HUD) system modified to display forwardlooking infrared (FLIR) imagery. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
SUMMARY: Special conditions—; Dassault Aviation Model Falcon 900EX and Falcon 2000EX airplanes,
SUPPLEMENTAL INFORMATION
The FAA has determined that the substance of these special conditions has previously been subject to the public comment process. These particular special conditions were recently issued and only three nonsubstantive comments were received during the public comment period. The FAA therefore finds that good cause exists for making these special conditions effective upon issuance. Comments InvitedWe invite interested people to take part in this rulemaking by sending written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. We ask that you send us two copies of written comments.
We will file in the docket all comments we receive, as well as a report summarizing each substantive public contact with FAA personnel about these special conditions. You can inspect the docket before and after the comment closing date. If you wish to review the docket in person, go to the address in the ADDRESSES section of this preamble between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
We will consider all comments we receive by the closing date for comments. We will consider comments filed late if it is possible to do so without incurring expense or delay. We may change these special conditions based on the comments we receive.
If you want us to let you know we received your comments on these special conditions, send us a preaddressed, stamped postcard on which the docket number appears. We will stamp the date on the postcard and mail it back to you.
Background
On August 18, 2004, Dassault Aviation applied for an amendment to the type design for the installation and operation of an infrared enhanced flight visibility system (EFVS) on Model Falcon 900EX airplanes with modification M3083 installed, and Model Falcon 2000EX airplanes with modification M1691 installed. Commercially, these airplanes are identified as the Falcon 900EX EASy and the Falcon 2000EX EASy. In this document, all references to Falcon 900EX EASy and Falcon 2000EX EASy airplanes mean airplanes with the applicable modification installed. The original type certificate for the Model Falcon 900EX airplane is A46EU, revision 13, dated February 27, 2006. The original type certificate for the Model Falcon 2000EX airplane is A50NM revision 3, dated September 21, 2004.
The Dassault Aviation Model Falcon 900EX and Falcon 2000EX are transport category airplanes that operate with a crew of two. The Model Falcon 900EX has a wing span of 63 feet 5 inches, a length of 66 feet 4 inches, a maximum takeoff gross weight of 48,300 pounds, is powered by three Allied Signal Engines TFE 731601C turbofan engines, and has a maximum range of 4,500 nautical miles. The Model Falcon 2000EX airplane has a wing span of 63 feet 5 inches, a length of 66 feet 4 inches, a maximum takeoff gross weight of 41,300 pounds, is powered by two Pratt & Whitney Canada Model PW308C turbofan engines, and has a maximum range of 3,800 nautical miles.
The electronic infrared image displayed between the pilot and the
forward windshield represents a novel or unusual design feature in the
context of 14 CFR 25.773. Section 25.773 was not written in
anticipation of such technology. The electronic image has the potential
to enhance the pilot's awareness of the terrain, hazards and airport
features. At the same time, the image may partially obscure the pilot's
direct outside compartment view. Therefore, the FAA needs adequate
safety standards to evaluate the EFVS to determine that the imagery
provides the intended visual enhancements without undue interference
with the pilot's outside compartment view. The FAA intent is that the
pilot will be able to use a combination of the information seen in the
image and the natural view of the outside scene seen through the image, as
[[Page 40649]]
safely and effectively as a pilot compartment view without an EVS image that is compliant with Sec. 25.773.
Although the FAA has determined that the existing regulations are not adequate for certification of EFVSs, it believes that EFVSs could be certified through application of appropriate safety criteria. Therefore, the FAA has determined that special conditions should be issued for certification of EFVS to provide a level of safety equivalent to that provided by the standard in Sec. 25.773.
Note: The term ``enhanced vision system'' (EVS) has been
commonly used to refer to a system comprised of a headup display,
imaging sensor(s), and avionics interfaces that displayed the sensor
imagery on the head up display (HUD) and overlaid it with alpha
numeric and symbolic flight information. However, the term has also
been commonly used in reference to systems which displayed the
sensor imagery, with or without other flight information, on a head
down display. To avoid confusion, the FAA created the term
``enhanced flight visibility system'' (EFVS) to refer to certain EVS
systems that meet the requirements of the new operational rulesin particular the requirement for a HUD and specified flight
informationand can be used to determine ``enhanced flight
visibility.'' EFVSs can be considered a subset of systems otherwise labeled EVSs.
On January 9, 2004, the FAA published revisions to operational rules in 14 CFR parts 1, 91, 121, 125, and 135 to allow aircraft to operate below certain altitudes during a straightin instrument approach while using an EFVS to meet visibility requirements.
Prior to this rule change, the FAA issued Special Conditions No. 25180SC, which approved the use of an EVS on Gulfstream Model GV airplanes. Those special conditions addressed the requirements for the pilot compartment view and limited the scope of the intended functions permissible under the operational rules at the time. The intended function of the EVS imagery was to aid the pilot during the approach and allow the pilot to detect and identify the visual references for the intended runway down to 100 feet above the touchdown zone. However, the EVS imagery alone was not to be used as a means to satisfy visibility requirements below 100 feet.
The recent operational rule change expands the permissible application of certain EVSs that are certified to meet the new EFVS standards. The new rule will allow the use of EFVSs for operation below the minimum descent altitude (MDA) or decision height (DH) to meet new visibility requirements of Sec. 91.175(l). The purpose of these special conditions is not only to address the issue of the ``pilot compartment view,'' as was done by Special Conditions No. 25180SC, but also to define the scope of intended function consistent with Sec. 91.175(l) and (m).
Type Certification Basis
Under the provisions of 14 CFR 21.101, Dassault Aviation must show that the Model Falcon 900EX and Falcon 2000EX airplanes, as modified, comply with the regulations in the U.S. type certification basis established for those airplanes. The U.S. type certification basis for the airplanes is established in accordance with Sec. Sec. 21.21 and 21.17, and the type certification application date. The U.S. type certification basis for the Model Falcon 900EX airplanes is listed in Type Certificate Data Sheet No. A46EU, revision 13, dated February 27, 2006, which covers all variants of the Model Falcon 900 airplanes, including the Falcon 900EX EASy. The U.S. type certification basis for the Model Falcon 2000EX airplanes is listed in Type Certificate Data Sheet No. A50NM, revision 3, dated September 21, 2004, which covers all variants of the Model Falcon 2000 airplanes, including the Falcon 2000 EX EASy.
In addition, the certification basis includes certain special conditions and exemptions that are not relevant to these special conditions. Also, if the regulations incorporated by reference do not provide adequate standards with respect to the change, the applicant must comply with certain regulations in effect on the date of application for the change.
If the Administrator finds that the applicable airworthiness regulations (i.e., part 25 as amended) do not contain adequate or appropriate safety standards for the Dassault Aviation Model Falcon 900EX and Falcon 2000EX, modified by Dassault Aviation, because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 21.16.
In addition to the applicable airworthiness regulations and special conditions, the Dassault Aviation Model Falcon 900EX EASy and Falcon 2000EX EASy airplanes must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36.
The FAA issues special conditions, as defined in Sec. 11.19, under Sec. 11.38 and they become part of the type certification basis under Sec. 21.101.
Special conditions are initially applicable to the model for which they are issued. Should the type certificate for those models be amended later to include any other model that incorporates the same novel or unusual design feature, the special conditions would also apply to the other model.
Novel or Unusual Design Features
The Dassault Aviation Model Falcon 900EX EASy and Falcon 2000EX EASy airplanes will incorporate an EFVS, which is a novel or unusual design feature. The EFVS is a novel or unusual design feature because it projects a video image derived from a forwardlooking infrared (FLIR) camera through the HUD. The EFVS image is projected in the center of the ``pilot compartment view,'' which is governed by Sec. 25.773. The image is displayed with HUD symbology and overlays the forward outside view. Therefore, Sec. 25.773 does not contain appropriate safety standards for the EFVS display.
Operationally, during an instrument approach, the EFVS image is intended to enhance the pilot's ability to detect and identify ``visual references for the intended runway'' [see Sec. 91.175(l)(3)] to continue the approach below decision height or minimum descent altitude. Depending on atmospheric conditions and the strength of infrared energy emitted and/or reflected from the scene, the pilot can see these visual references in the image better than he or she can see them through the window without EFVS.
Scene contrast detected by infrared sensors can be much different from that detected by natural pilot vision. On a dark night, thermal differences of objects which are not detectable by the naked eye will be easily detected by many imaging infrared systems. On the other hand, contrasting colors in visual wavelengths may be distinguished by the naked eye but not by an imaging infrared system. Where thermal contrast in the scene is sufficiently detectable, the pilot can recognize shapes and patterns of certain visual references in the infrared image. However, depending on conditions, those shapes and patterns in the infrared image can appear significantly different than they would with normal vision. Considering these factors, the EFVS image needs to be evaluated to determine that it can be accurately interpreted by the pilot.
The image may improve the pilot's ability to detect and identify items of interest. However, the EFVS needs to be evaluated to determine that the imagery allows the pilot to perform the normal duties of the flightcrew and adequately see outside the window through the image, consistent with the safety intent of Sec. 25.773(a)(2).
Compared to a HUD displaying the EFVS image and symbology, a HUD that
[[Page 40650]]
only displays strokewritten symbols is easier to see through. Stroke
symbology illuminates a small fraction of the total display area of the
HUD, leaving much of that area free of reflected light that could
interfere with the pilot's view out the window through the display.
However, unlike stroke symbology, the video image illuminates most of
the total display area of the HUD (approximately 30 degrees
horizontally and 25 degrees vertically) which is a significant fraction
of the pilot compartment view. The pilot cannot see around the larger
illuminated portions of the video image, but must see the outside scene through it.
Unlike the pilot's external view, the EFVS image is a monochrome, twodimensional display. Many, but not all, of the depth cues found in the natural view are also found in the image. The quality of the EFVS image and the level of EFVS infrared sensor performance could depend significantly on conditions of the atmospheric and external light sources. The pilot needs adequate control of sensor gain and image brightness, which can significantly affect image quality and transparency (i.e., the ability to see the outside view through the image). Certain system characteristics could create distracting and confusing display artifacts. Finally, because this is a sensorbased system intended to provide a conformal perspective corresponding with the outside scene, the system must be able to ensure accurate alignment.
Therefore, safety standards are needed for each of the following factors:
Section 25.773, Pilot compartment view, specifies that ``Each pilot compartment must be free of glare and reflection that could interfere with the normal duties of the minimum flight crew * * *.'' In issuing Sec. 25.773, the FAA did not anticipate the development of EFVSs and does not consider Sec. 25.773 to be adequate to address the specific issues related to such a system. Therefore, the FAA has determined that special conditions are needed to address the specific issues particular to the installation and use of an EFVS.
Discussion
The EFVS is intended to function by presenting an enhanced view during the approach. This enhanced view would help the pilot to see and recognize external visual references, as required by Sec. 91.175(l), and to visually monitor the integrity of the approach, as described in FAA Order 6750.24D (``Instrument Landing System and Ancillary Electronic Component Configuration and Performance Requirements,'' dated March 1, 2000).
Based on this approved functionality, users would seek to obtain operational approval to conduct approachesincluding approaches to Type I runwaysin visibility conditions much lower than those for conventional Category I.
The purpose of these special conditions is to ensure that the EFVS to be installed can perform the following functions:
Depending on the atmospheric conditions and the particular visual references that happen to be distinctly visible and detectable in the EFVS image, these functions would support its use by the pilot to visually monitor the integrity of the approach path.
Compliance with these special conditions does not affect the applicability of any of the requirements of the operating regulations (i.e., 14 CFR parts 91, 121, and 135). Furthermore, use of the EFVS does not change the approach minima prescribed in the standard instrument approach procedure being used; published minima still apply.
The FAA certification of this EFVS is limited as follows:
An EFVS image may provide an enhanced image of the scene that may compensate for any reduction in the clear outside view of the visual field framed by the HUD combiner. The pilot must be able to use this combination of information seen in the image and the natural view of the outside scene seen through the image as safely and effectively as the pilot would use a pilot compartment view without an EVS image that is compliant with Sec. 25.773. This is the fundamental objective of the special conditions.
The FAA will also apply additional certification criteria, not as special conditions, for compliance with related regulatory requirements, such as Sec. Sec. 25.1301 and 25.1309. These additional criteria address certain image characteristics, installation, demonstration, and system safety.
Image characteristics criteria include the following:
Installation criteria address visibility and access to EFVS controls and integration of EFVS in the cockpit.
The EFVS demonstration criteria address the flight and environmental conditions that need to be covered.
The FAA also intends to apply certification criteria relevant to high intensity radiated fields (HIRF) and lightning protection. Applicability
As discussed above, these special conditions are applicable to Dassault Aviation Model Falcon 900EX airplanes with modification M3083 installed (Falcon 900EX EASy) and Model Falcon 2000EX airplanes with modification M1691 installed (Falcon 2000EX EASy). Should Dassault Aviation apply at a later date for an amendment to the type design to modify any other model included on Type Certificates No. A46EU or A50NM to incorporate the same novel or unusual design feature, the special conditions would apply to those models as well.
Conclusion
This action affects only certain novel or unusual design features on Dassault Aviation Model Falcon 900EX EASy and Falcon 2000EX EASy airplanes modified by Dassault Aviation. It is not a rule of general applicability.
The substance of these special conditions has been subjected to the
notice and comment period in several prior instances and has been
derived without substantive change from those previously issued. It is
unlikely that prior public comment would result in a significant change
from the substance contained herein. Therefore, because a delay would significantly affect the
[[Page 40651]]
certification of the airplane, which is imminent, the FAA has
determined that prior public notice and comment are unnecessary and
impracticable, and good cause exists for adopting these special
conditions upon issuance. The FAA is requesting comments to allow
interested persons to submit views that may not have been submitted in
response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping requirements.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for Dassault Aviation Model Falcon 900EX
airplanes with modification M3083 installed (Falcon 900EX EASy) and
Model Falcon 2000EX airplanes with modification M1691 installed (Falcon Model 2000EX EASy).
1. The EFVS imagery on the HUD must not degrade the safety of flight or interfere with the effective use of outside visual references for required pilot tasks during any phase of flight in which it is to be used.
2. To avoid unacceptable interference with the safe and effective use of the pilot compartment view, the EFVS device must meet the following requirements:
a. The EFVS design must minimize unacceptable display characteristics or artifacts (e.g. noise, ``burlap'' overlay, running water droplets) that obscure the desired image of the scene, impair the pilot's ability to detect and identify visual references, mask flight hazards, distract the pilot, or otherwise degrade task performance or safety.
b. Control of EFVS display brightness must be sufficiently effective in dynamically changing background (ambient) lighting conditions to prevent full or partial blooming of the display that would distract the pilot, impair the pilot's ability to detect and identify visual references, mask flight hazards, or otherwise degrade task performance or safety. If automatic control for image brightness is not provided, it must be shown that a single manual setting is satisfactory for the range of lighting conditions encountered during a timecritical, high workload phase of flight (e.g., low visibility instrument approach).
c. A readily accessible control must be provided that permits the pilot to immediately deactivate and reactivate display of the EFVS image on demand.
d. The EFVS image on the HUD must not impair the pilot's use of guidance information or degrade the presentation and pilot awareness of essential flight information displayed on the HUD, such as alerts, airspeed, attitude, altitude and direction, approach guidance, windshear guidance, TCAS resolution advisories, or unusual attitude recovery cues.
e. The EFVS image and the HUD symbolswhich are spatially referenced to the pitch scale, outside view and imagemust be scaled and aligned (i.e., conformal) to the external scene. In addition, the EFVS image and the HUD symbolswhen considered singly or in combinationmust not be misleading, cause pilot confusion, or increase workload. There may be airplane attitudes or crosswind conditions which cause certain symbols (e.g., the zeropitch line or flight path vector) to reach field of view limits, such that they cannot be positioned conformally with the image and external scene. In such cases, these symbols may be displayed but with an altered appearance which makes the pilot aware that they are no longer displayed conformally (for example, ``ghosting'').
f. A HUD system used to display EFVS images must, if previously certified, continue to meet all of the requirements of the original approval.
3. The safety and performance of the pilot tasks associated with the use of the pilot compartment view must not be degraded by the display of the EFVS image. These tasks include the following:
a. Detection, accurate identification and maneuvering, as necessary, to avoid traffic, terrain, obstacles, and other hazards of flight.
b. Accurate identification and utilization of visual references required for every task relevant to the phase of flight.
4. Compliance with these special conditions will enable the EFVS to be used during instrument approaches in accordance with Sec. 91.175(l) such that it may be found acceptable for the following intended functions:
a. Presenting an image that would aid the pilot during a straight in instrument approach.
b. Enabling the pilot to determine that there is sufficient ``enhanced flight visibility,'' as required by Sec. 91.175(l)(2), for descent and operation below minimum descent altitude/decision height (MDA)/(DH).
c. Enabling the pilot to use the EFVS imagery to detect and identify the ``visual references for the intended runway,'' required by Sec. 91.175(l)(3), to continue the approach with vertical guidance to 100 feet height above touchdown zone elevation.
5. Use of EFVS for instrument approach operations must be in
accordance with the provisions of Sec. 91.175(l) and (m). Appropriate
limitations must be stated in the Operating Limitations section of the
airplane flight manual to prohibit the use of the EFVS for functions that have not been found to be acceptable.
Issued in Renton, Washington, on July 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E611367 Filed 71706; 8:45 am]
BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT Dale Dunford, FAA, Transport Standards
Staff, ANM111, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue, SW., Renton, Washington 980554056;
telephone (425) 2272239; fax (425) 2271320; email:
dale.dunford@faa.gov.
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