Source: https://www.global-regulation.com/law/united-states/29651/special-conditions%253a-bombardier-inc.-model-bd-700-2a12-and-bd-700-2a13-airplanes%253b-design-roll-maneuver-condition.html
Timestamp: 2018-05-24 02:05:34
Document Index: 754940619

Matched Legal Cases: ['art 25', '§ 25', 'art 25', '§ 21', '§ 21', '§ 25', '§ 25', '§ 25', '§ 25']

Special Conditions: Bombardier Inc. Model BD-700-2A12 and BD-700-2A13 Airplanes; Design Roll-Maneuver Condition (United States)
Link to law: https://www.federalregister.gov/articles/text/raw_text/201/510/102.txt
http://www.regulations.gov/ at any time. Follow the online instructions for accessing the docket, or go to Docket Operations in Room W12-140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
In addition, the substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA therefore finds that good cause exists for making these special conditions effective upon publication in the Federal Register .
The design of the Model BD-700-2A12 and BD-700-2A13 airplanes includes new high-speed transonic wings with improved aerodynamic efficiency, a pressurized cabin for luxury interiors, and they share an identical supplier base and significant common design elements. The current design roll-maneuver requirement in Title 14, Code of Federal Regulations (14 CFR) part 25 is inadequate for addressing an airplane with electronic flight controls that affect maneuvering. These special conditions adjust the current roll-maneuver requirement, § 25.349, to take into account the effects of an electronic flight-control system.
If the Administrator finds that the applicable airworthiness regulations ( i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Model BD-700-2A12 and BD-700-2A13 airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.
Special conditions are initially applicable to the Model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101.
These special conditions differ from current requirements in that they require that the roll maneuver is based on defined actuation of the cockpit roll control as opposed to defined deflections of the aileron itself. Also, the special conditions require an additional load condition at V A , in which the cockpit roll control is returned to neutral following the initial roll input.
These special conditions differ from similar special conditions applied on previous programs. These special conditions are limited to the roll axis only, whereas previous special conditions also included the pitch and yaw axes. Special conditions are no longer needed for the pitch or yaw axes, because Amendment 25-91 takes into account the effects of an electronic flight-control system in those axes (§ 25.331 for pitch and § 25.351 for yaw).
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 certification of the airplane, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon publication in the Federal Register . 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.
In lieu of compliance to § 25.349(a):
The following conditions, speeds, and cockpit roll-control motions (except as the motions may be limited by pilot effort) must be considered in combination with an airplane load factor of zero and of two-thirds of the positive maneuvering factor used in design. In determining the resulting control-surface deflections, the torsional flexibility of the wing must be considered in accordance with § 25.301(b):
2. At V A , sudden movement of the cockpit roll control up to the limit is assumed. The position of the cockpit roll control must be maintained until a steady roll rate is achieved and then must be returned suddenly to the neutral position.
3. At V C , the cockpit roll control must be moved suddenly and maintained so as to achieve a roll rate not less than that obtained in Special Condition 2, above.
4. At V D , the cockpit roll control must be moved suddenly and maintained so as to achieve a roll rate not less than one third of that obtained in Special Condition 2, above.