Federal Aviation Administration (FAA), DOT.
Final special conditions.
These special conditions are issued 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 airplane jacking loads. 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. Additional special conditions will be issued for other novel or unusual design features of the Airbus Model A380-800 airplane.
Effective Date: The effective date of these special conditions is July 20, 2006.Start Further Info
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.End Further Info End Preamble Start Supplemental Information
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 Start Printed Page 48450initial 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 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 A380 has a multi-leg landing gear arrangement consisting of a nose gear, two wing mounted gear, and two body mounted gear. This arrangement is different from the simpler, conventional landing gear arrangement envisioned by the jacking load requirements of 14 CFR 25.519. Those regulations assume a landing gear arrangement comprising a three point suspension system (two main gear and a nose or tail gear) in which load sharing between the landing gear can be determined without considering the flexibility of the airframe.
For a five point suspension system, like that of the A380, calculations that consider airplane flexibilities are necessary to determine load sharing between landing gear units accurately. (The flexibility of the individual landing gear oleos and of the airplane itself affect how the weight of the airplane is distributed among the individual landing gear units.)
Special conditions are necessary to allow a rational analysis of the jacking condition for the main and body landing gear. (This analysis will include the case of bogie gears where one leg of a bogie is jacked and the other leg is supported on a tripod—which is not addressed by § 25.519.) The applicant has proposed a rational jacking analysis, which makes reasonable or conservative assumptions about the runway configuration and ground wind speeds.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-06-04-SC, pertaining to airplane jacking loads for the Airbus A380 airplane, was published in the Federal Register on March 28, 2006. A single comment which supports the intent and language of the special conditions, as proposed, was received from the Airline Pilots Association (ALPA). Accordingly, the special conditions are adopted as proposed.
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 § 21.101.
This action affects only certain novel or unusual design features of the Airbus A380-800 airplane. It is not a rule of general applicability.Start List of Subjects
List of Subjects in 14 CFR Part 25End List of Subjects Start Amendment Part
The authority citation for these special conditions is as follows:End Amendment Part
The Special ConditionsStart Amendment Part
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 the Airbus A380-800 airplane.End Amendment Part
In lieu of compliance with 14 CFR 25.519(b)(1), for jacking by the landing gear at the maximum ramp weight of the airplane, the airplane structure may be designed to withstand the maximum limit loads arising from conditions a. and b. below.
a. The loads arising from jacking by the landing gear may be derived from a rational analysis under both of the following conditions:
1. A ramp crown defined by a 1.5% gradient, the crest of the gradient to be in the most adverse position for the loading of the undercarriage unit in question; and the maximum allowable steady wind for jacking operations from any horizontal direction; and the most adverse combination of oleo leg pressures within service tolerances; and jack(s) at the maximum possible overshoot.
2. A ramp crown defined by a 1.5% gradient, the crest of the gradient to be in the most adverse position for the loading of the undercarriage unit in question; and twice the maximum allowable steady wind for jacking operations from any horizontal direction; and a nominal distribution of oleo leg pressures; and jacking performed in accordance with recommended procedures.
b. The limit horizontal load at the jacking point undercarriage unit may not be less than the higher of that derived from the above rational analysis or 0.33 times the limit static vertical Start Printed Page 48451reaction found with the undercarriage unit in question supported at the jacking points with the aircraft in the unjacked position. This load must be applied in combination with the vertical loads arising from the analysis of (a) above.
Jacking equipment used for the airplane jacking operation must be controlled by a specification that assures that jacking operations are conducted in a manner that is consistent with the provisions of this special condition. Jacking instructions must be developed and incorporated in the Instructions for Continued Airworthiness to assure that the proper jacking equipment is used and that the jacking operation is conducted in a manner consistent with the provisions of this special conditions. The jacking instructions may be by means of placards conspicuously located near the jacking points or by other suitable means acceptable to the Administrator.Start Signature
Issued in Renton, Washington, on July 20, 2006.
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E6-13789 Filed 8-18-06; 8:45 am]
BILLING CODE 4910-13-P