Special Conditions: Airbus Model A350-900 Airplanes; High-Speed Protection System
Federal Register, Volume 79 Issue 162 (Thursday, August 21, 2014)
Federal Register Volume 79, Number 162 (Thursday, August 21, 2014)
Rules and Regulations
Pages 49427-49429
From the Federal Register Online via the Government Printing Office www.gpo.gov
FR Doc No: 2014-19824
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
Docket No. FAA-2013-1001; Special Conditions No. 25-535-SC
Special Conditions: Airbus Model A350-900 Airplanes; High-Speed Protection System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
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SUMMARY: These special conditions are issued for Airbus Model A350-900 airplanes. These airplanes will have a novel or unusual design feature associated with a high-speed protection system that limits nose-down pilot authority at speeds above VC/MC, and prevents the airplane from performing the maneuver required under the Code of Federal Regulations. 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.
DATES: Effective date: September 22, 2014.
FOR FURTHER INFORMATION CONTACT: Todd Martin, FAA, Airframe/Cabin Safety, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 227-1178; facsimile (425) 227-1322.
SUPPLEMENTARY INFORMATION:
Background
On August 25, 2008, Airbus applied for a type certificate for their new Model A350-900 airplane. Later, Airbus requested, and the FAA approved, an extension to the application for FAA type certification to November 15, 2009. The Model A350-900 airplane has a conventional layout with twin wing-mounted Rolls-Royce Trent XWB engines. It features a twin-aisle, 9-abreast, economy-class layout, and accommodates side-by-side placement of LD-3 containers in the cargo compartment. The basic Model A350-900 airplane configuration accommodates 315 passengers in a standard two-class arrangement. The design cruise speed is Mach 0.85 with a maximum take-off weight of 602,000 lbs.
The Model A350-900 airplane, like Airbus Model A320, A330, A340 and A380 series airplanes, has a high-speed protection system that limits nose-down pilot authority at speeds above VC/MC, and prevents the airplane from actually performing the maneuver required under Sec. 25.335(b)(1). Special conditions are necessary to address the Model A350-900 airplane high-speed protection system. These special conditions identify various symmetric and non-symmetric maneuvers that will ensure that an appropriate design dive speed, VD/MD, is established.
Type Certification Basis
Under Title 14, Code of Federal Regulations (14 CFR) 21.17, Airbus must show that the Model A350-900 airplane meets the applicable provisions of part 25, as amended by Amendments 25-1 through 25-129.
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 A350-900 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 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 or similar novel or unusual design feature, the special conditions would also apply to the other model under Sec. 21.101.
In addition to the applicable airworthiness regulations and special conditions, the Model A350-900 airplane 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 must issue a finding of regulatory adequacy under section 611 of Public Law 92-574, the ``Noise Control Act of 1972.''
The FAA issues special conditions, as defined in 14 CFR 11.19, under Sec. 11.38, and they become part of the type-certification basis under Sec. 21.17(a)(2).
Novel or Unusual Design Features
In addition to the applicable airworthiness regulations and special conditions, the Model A350-900 airplane 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 must issue a finding of regulatory adequacy under Sec. 611 of Public Law 92-574, the ``Noise Control Act of 1972.''
The Airbus Model A350-900 airplane will incorporate the following novel or unusual design features:
A high-speed protection system that limits nose-down pilot authority at speeds above VC/MC, and prevents the airplane from actually performing the maneuver required under Sec. 25.335(b)(1). The special conditions identify various symmetric and non-symmetric maneuvers that will ensure that an appropriate design dive speed, VD/MD, is established.
Discussion
Section 25.335(b)(1) is an analytical envelope condition originally adopted in Part 4b of the Civil Air Regulations to provide an acceptable speed margin
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between design cruise speed and design dive speed. Flutter-clearance design speeds and airframe design loads are impacted by the design dive speed. While the initial condition for the upset specified in the rule is 1g level flight, protection is afforded for other inadvertent overspeed conditions as well. Section 25.335(b)(1) is intended as a conservative enveloping condition for potential overspeed conditions, including non-symmetric conditions.
To establish that potential overspeed conditions are enveloped, Airbus should demonstrate that any reduced speed margin, based on the high-speed protection system in the Model A350-900 airplane, will not be exceeded in inadvertent, or gust-induced, upsets resulting in initiation of the dive from non-symmetric attitudes; or that the airplane is protected, by the flight-control laws, from getting into non-symmetric upset conditions. The special conditions identify various symmetric and non-symmetric maneuvers that will ensure that an appropriate design dive speed, VD/MD, is established.
These special conditions are in lieu of Sec. 25.335(b)(1). Section 25.335(b)(2), which also addresses the design dive speed, is applied separately (Advisory Circular (AC) 25.335-1A provides an acceptable means of compliance to Sec. 25.335(b)(2)). The applicant should conduct a demonstration that includes a comprehensive set of conditions, as described below.
Special conditions (3) and (4) indicate that failures of the high-
speed protection system must be improbable and must be annunciated to the pilots. If these two criteria are not met, then the probability that the established dive speed will be exceeded, and the resulting risk to the airplane, is too great. On the other hand, if the high-
speed protection system is known to be inoperative, then dispatch of the airplane could be acceptable under an approved minimum-equipment list (MEL) containing language similar to special condition (5). Dispatch under an MEL would require that appropriate reduced operating speeds, VMO/MMO, are provided in the airplane flight manual (AFM), and the cockpit display of those reduced speeds, as well as the overspeed warning for exceeding those speeds, are equivalent to that of the normal airplane with the high-speed protection system operative.
We do not believe that application of the Interaction of Systems and Structures special conditions (docket no. FAA-2013-0894), or the European Aviation Safety Agency (EASA) Certification Specification (CS) 25.302, is appropriate in this case because design dive speed is, in and of itself, part of the design criteria. Stability and control, flight loads, and flutter evaluations all depend on the design dive speed. Therefore, a single design dive speed should be established that will not be exceeded, taking into account the performance of the high-
speed protection system as well as its failure modes, failure indications, and accompanying AFM instructions.
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.
Discussion of Comments
Notice of proposed special conditions No. 25-13-35-SC for Airbus Model A350-900 airplanes was published in the Federal Register on December 24, 2013 (78 FR 77611). No comments were received and the special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions apply to Airbus Model A350-900 airplanes. Should Airbus apply at a later date for a change to the type certificate to include another airplane series incorporating the same novel or unusual design feature, the special conditions would apply to that series as well.
Conclusion
This action affects only certain novel or unusual design features on the Airbus Model A350-900 series airplanes. It is not a rule of general applicability.
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 and 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 Airbus Model A350-900 series airplanes.
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In lieu of compliance with Sec. 25.335(b)(1), if the flight-
control system includes functions that act automatically to initiate recovery before the end of the 20-second period specified in Sec. 25.335(b)(1), VD/MD must be determined from the greater of the speeds resulting from conditions (a) and (b), below. The speed increase occurring in these maneuvers may be calculated if reliable or conservative aerodynamic data are used.
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From an initial condition of stabilized flight at VC/
MC, the airplane is upset so as to travel a new flight path 7.5 degrees below the initial path. Control application, up to full authority, is made to try to maintain this new flight path. Twenty seconds after initiating the upset, manual recovery is made at a load factor of 1.5 g (0.5 acceleration increment), or such greater load factor that is automatically applied by the system with the pilot's pitch control set to neutral. Power, as specified in Sec. 25.175(b)(1)(iv), is assumed until recovery is initiated, at which time power reduction and the use of pilot-controlled drag devices may be used.
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From a speed below VC/MC, with power to maintain stabilized level flight at this speed, the airplane is upset so as to accelerate through VC/MC at a flight path 15 degrees below the initial path (or at the steepest nose-down attitude that the system will permit with full control authority, if less than 15 degrees). The pilot's controls may be in the neutral position after reaching VC/MC and before recovery is initiated. Recovery may be initiated three seconds after operation of the high-speed warning system by application of a load of 1.5g (0.5 acceleration increment), or such greater load factor that is automatically applied by the system with the pilot's pitch control set to neutral. Power may be reduced simultaneously. All other means of decelerating the airplane, the use of which is authorized up to the highest speed reached in the maneuver, may be used. The interval between successive pilot actions must not be less than one second.
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The applicant must also demonstrate that the speed margin, established as above, will not be exceeded in inadvertent, or gust-
induced, upsets resulting in initiation of the dive from non-symmetric attitudes, unless the airplane is protected by the flight-control laws from getting into non-symmetric upset conditions. The upset maneuvers described in AC 25-7C, Chapter 2, Section 8, Paragraph 32c.(3)(a) and (c), may be used to comply with this requirement.
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Detected loss of the high-speed protection function must be less than 10-3 per flight hour.
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Failures of the system must be annunciated to the pilots. The Operating Limitations Section of the AFM must contain instructions that reduce the maximum operating speeds, Vmax/Mmax, to a value that maintains a speed margin between these speeds and
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VD/MD that is consistent with showing compliance to Sec. 25.335(b), without the benefit of the high-speed protection system.
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Dispatch of the airplane with the high-speed protection system inoperative is prohibited except under an approved MEL that requires AFM instructions to indicate reduced maximum operating speeds, as described in special condition (4), above. In addition, the cockpit display of the reduced operating speeds, as well as the overspeed warning for exceeding those speeds, must be equivalent to that of the normal airplane with the high-speed protection system operative. Also, it must be shown that no additional hazards are introduced with the high-speed protection system inoperative.
Issued in Renton, Washington, on July 30, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
FR Doc. 2014-19824 Filed 8-20-14; 8:45 am
BILLING CODE 4910-13-P
