Airworthiness standards: Special conditions— Airbus Model A380-800 airplane,

[Federal Register: March 29, 2006 (Volume 71, Number 60)]

[Proposed Rules]

[Page 15645-15647]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr29mr06-25]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM342; Notice No. 25-06-03-SC]

Special Conditions: Airbus Model A380-800 Airplane, Extendable Length Escape System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

SUMMARY: This notice proposes special conditions for the Airbus A380- 800 airplane. This airplane will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. Many of these novel or unusual design features are associated with the complex systems and the configuration of the airplane, including its full- length double deck. For these design features, the applicable airworthiness regulations do not contain adequate or appropriate safety standards regarding extendable length escape slides. These proposed 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.

DATES: Comments must be received on or before May 15, 2006.

ADDRESSES: Comments on this proposal may be mailed in duplicate to: Federal Aviation Administration, Transport Airplane Directorate, Attention: Rules Docket (ANM-113), Docket No. NM342, 1601 Lind Avenue SW., Renton, Washington 98055-4056; or delivered in duplicate to the Transport Airplane Directorate at the above address. All comments must be marked: Docket No. NM342. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.

FOR FURTHER INFORMATION CONTACT: Holly Thorson, FAA, International Branch, ANM-116, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (425) 227-1357; facsimile (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites interested persons to participate in this rulemaking by submitting 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 concerning these proposed special conditions. The docket is available for public inspection 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 notice between 7:30 a.m. and 4 p.m., Monday through Friday, except Federal holidays.

We will consider all comments we receive on or before 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 the proposed special conditions in light of the comments we receive.

If you want the FAA to acknowledge receipt of your comments on this proposal, include with your comments a pre-addressed, stamped postcard on which the docket number appears. We will stamp the date on the postcard and mail it back to you.

Background

Airbus applied for FAA certification/validation of the provisionally-designated Model A3XX-100 in its letter AI/L 810.0223/98, dated August 12, 1998, to the FAA. Application for certification by the Joint Aviation Authorities (JAA) of Europe had been made on January 16, 1998, reference AI/L 810.0019/98. In its letter to the FAA, Airbus requested an extension to the 5-year period for type certification in accordance with 14 CFR 21.17(c). The request was for an extension to a 7-year period, using the date of the initial application letter to the JAA as the reference date. The reason given by Airbus for the request for extension is related to the technical challenges, complexity, and the number of new and novel features on the airplane. On November 12, 1998, the Manager, Aircraft Engineering Division, AIR-100, granted Airbus' request for the 7-year period, based on the date of application to the JAA.

In its letter AI/LE-A 828.0040/99 Issue 3, dated July 20, 2001, Airbus stated that its target date for type certification of the Model A380-800 had been moved from May 2005, to January 2006, to match the delivery date of the first production airplane. In a subsequent letter (AI/L 810.0223/98 issue 3, dated January 27, 2006), Airbus stated that its target date for type certification is October 2, 2006. In accordance with 14 CFR 21.17(d)(2), Airbus chose a new application date of December 20, 1999, and requested that the 7-year certification period which had already been approved be continued. The FAA has reviewed the part 25 certification basis for the Model A380-800 airplane, and no changes are required based on the new application date.

The Model A380-800 airplane will be an all-new, four-engine jet transport airplane with a full double-deck, two-aisle cabin. The maximum takeoff weight will be 1.235 million pounds with a typical three-class layout of 555 passengers.

Type Certification Basis

Under the provisions of 14 CFR 21.17, Airbus must show that the Model A380-800 airplane meets the applicable provisions of 14 CFR part 25, as amended by Amendments 25-1 through 25-98. If the Administrator finds that the applicable airworthiness regulations do not contain adequate or appropriate safety standards for the Airbus A380-800 airplane because of novel or unusual design features, special conditions are prescribed under the provisions of 14 CFR 21.16.

In addition to the applicable airworthiness regulations and special conditions, the Airbus Model A380-800 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. In addition, the FAA must issue a finding of regulatory adequacy pursuant to section 611 of Public Law 93-574, the ``Noise Control Act of 1972.''

Special conditions, as defined in 14 CFR 11.19, are issued in accordance with 14 CFR 11.38 and become part of the type certification basis in

[[Page 15646]]

accordance with 14 CFR 21.17(a)(2), Amendment 21-69, effective September 16, 1991.

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, the special conditions would also apply to the other model under the provisions of 14 CFR 21.101.

Discussion of Novel or Unusual Design Features

The Airbus Model A380-800 airplane has 16 emergency exits and 16 escape slides to be used for evacuation of passengers in case of emergency. Of these, 14 are fixed-length escape slides, and two (at door M1) are extendable length escape slides. The extendable length escape slides have a 16-foot extension packed at the toe.

Typically, airplanes have fixed length escape slides. However, it was not possible to use fixed length escape slides for the A380 door M1 because of the extreme difference between normal sill height and high sill height associated with collapse of some of the landing gear in an emergency. Some combinations of landing gear collapse could cause the airplane to tip back on its tail.

On the door, there is an electronic sensor that evaluates the attitude of the airplane and determines whether the extension is needed. During normal operation, the extension remains packed at the toe end of the escape slide. When the extension is needed, the system sends a signal to a squib that allows the extension to be inflated during deployment. If the system detects that the slide extension has failed to deploy, a warning is activated that tells the flight attendants that the slide should not be used. The warning will also activate--if after initial deployment of the slide without the extension deploying--the attitude of the airplane changes to the extent that the extension should be deployed. The slide system design cannot accommodate deploying the extension after deployment of the main body of the slide.

The performance requirements for escape systems are contained in 14 CFR 25.810 and address several abnormal operating conditions as well as failure conditions and reliability. The requirements of Sec. 25.810 remain applicable for the slide in the unextended mode, and for the most part, in the extended mode. The special conditions indicate where the requirements differ from the requirements of Sec. 25.810 for the slide in the extended mode.

The extension is intended only for use at high sill heights. A typical fixed-length slide operating at high sill height does not satisfy all of the performance requirements of Sec. 25.810, but its variations in performance are understood and largely predictable. Certain performance criteria are valid regardless of sill height, whereas other aspects of performance can be expected to decline at higher sill heights. With an extendable slide, there is a step change in configuration and potentially a step change in performance.

Therefore, special conditions are needed to ensure acceptable performance in the extended mode. Section 25.810 specifies the basic performance requirements for escape slides including wind testing, repeatability testing, and testing at adverse sill heights. Section 25.1309(a) requires that systems perform under foreseeable operating conditions, such as extreme temperatures, and a demonstration that the system design is appropriate for its intended function. Standards for the equipment itself are contained in Technical Standard Order C69c and contribute to a satisfactory installation.

Existing 14 CFR part 25 regulations governing the certification of the A380 do not adequately address certification requirements of an extendable length escape slide. The FAA is proposing special conditions to ensure that an extendable length escape slide performs adequately in both the unextended and the extended configuration.

Technical Standard Order C69c addresses many detailed aspects of escape slide performance that are not specified in 14 CFR part 25 but are generally considered essential to assuring adequate escape slide performance. These special conditions supplement the requirements of 14 CFR part 25, for the slide in its extended mode. However, because of the novel nature of this design, the special conditions will require that the escape slide receive TSO authorization or satisfy an equivalent standard.

Wind tests are typically conducted only on fixed length slides at normal sill height. Since the regulations require that the 25 knot standard is met at the most critical wind angle, escape slides usually exceed 25 knots performance at other than the critical angle. The same is expected to be true of the slide in its extended mode, but some reduction in the required wind velocity is appropriate since the slide will be in an abnormal condition. Available data indicates that a value of 22 knots is appropriate to cover the slide in its extended mode at normal sill height. This corresponds to roughly 75% of the wind energy required for the slide in its normal attitude and will ensure that the slide can function in its extended mode at least as well as a fixed length slide under similar abnormal conditions.

The special conditions also specify a rate for evacuation of passengers which is consistent with that of fixed length escape slides.

Applicability

As discussed above, these special conditions are applicable to the Airbus A380-800 airplane. Should Airbus apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design features, these special conditions would apply to that model as well under the provisions of Sec. 21.101.

Conclusion

This action affects only certain novel or unusual design features of the Airbus A380-800 airplane. 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, 44704.

The Proposed Special Conditions

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the Airbus A380-800 airplane.

In addition to the provisions of 14 CFR part 25, the following special conditions apply:

1. The extendable escape slide must receive TSO C69c authorization or the equivalent.

2. In addition to the requirements of Sec. 25.810(a)(1)(iii) for usability in conditions of landing gear collapse, the deployed escape slide in the extended mode must demonstrate an evacuation rate of 45 persons per minute per lane at the sill height corresponding to activation of the extension.

3. In lieu of the requirements of Sec. 25.810(a)(1)(iv), the escape slide deployed in the extended mode must be capable of being used in 22 knot winds directed from the critical angle, with the airplane on all its landing gear.

4. Pitch sensor tolerances and accuracy must be taken into account when demonstrating compliance with

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   Sec. 25.1309(a) for the escape slide in both the extended and unextended modes.

5. Design of the ``slide extension'' warning must be such that the cabin crew is made aware of a non usable slide (i.e., the main slide has deployed, and the door sill height is such that the extension should be deployed but cannot be deployed), even if this is due to the airplane attitude changing during the evacuation. The ability to provide such a warning must be available for ten minutes after the airplane is immobilized on the ground.

   Issued in Renton, Washington, on March 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

   [FR Doc. E6-4511 Filed 3-28-06; 8:45 am]

   BILLING CODE 4910-13-P