Source: https://www.federalregister.gov/documents/2002/02/25/02-4411/special-conditions-fairchild-dornier-gmbh-model-728-100-sudden-engine-stoppage
Timestamp: 2017-08-21 03:49:24
Document Index: 705253321

Matched Legal Cases: ['art 25', 'art 25', '§\u200921', '§\u200911', 'art 34', 'art 36', 'art 25', '§\u200925']

Federal Register :: Special Conditions: Fairchild Dornier GmbH, Model 728-100; Sudden Engine Stoppage
Special Conditions: Fairchild Dornier GmbH, Model 728-100; Sudden Engine Stoppage
Comments must be received on or before April 11, 2002.
67 FR 8485
Docket No. NM205
Special Conditions No. 25-01-05-SC
02-4411
https://www.federalregister.gov/d/02-4411 https://www.federalregister.gov/d/02-4411
This notice proposes special conditions for the Fairchild Dornier GmbH Model 728-100 airplane. This airplane will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes, associated with engine size and torque load which affects sudden engine stoppage. 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.
Start Printed Page 8486
Comments on this proposal may be mailed in duplicate to: Federal Aviation Administration, Transport Airplane Directorate, Attention: Rules Docket (ANM-113), Docket No. NM205, 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. NM205. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
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.
On May 5, 1998, Fairchild Dornier GmbH applied for a type certificate for their new Model 728-100 airplane. The Model 728-100 airplane is a 70-85 passenger twin-engine regional jet with a maximum takeoff weight of 77,600 pounds.
Under the provisions of 14 CFR 21.17, Fairchild Dornier must show that the Model 728-100 airplane meets the applicable provisions of part 25, as amended by Amendments 25-1 through 25-96. Fairchild Dornier GmbH has also applied to extend the certification basis to include Amendments 25-97, 25-98, and 25-104.
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 728-100 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.
Special conditions, as defined in 14 CFR 11.19, are issued in accordance with § 11.38 and become part of the type certification basis in accordance with 14 CFR 21.17(a)(2). 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(a)(1).
In addition to the applicable airworthiness regulations and special conditions, the Model 728-100 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, and the FAA must issue a finding of regulatory adequacy pursuant to section 611 of Public Law 92-574, the “Noise Control Act of 1972.”
The Fairchild Dornier GmbH Model 728-100 airplane will incorporate novel or unusual design features involving engine size and torque load that affect sudden engine stoppage conditions. Fairchild Dornier GmbH proposes to treat the sudden engine stoppage condition resulting from structural failure as an ultimate load condition. Section 25.361(b)(1) of part 25 specifically defines the seizure torque load, resulting from structural failure, as a limit load condition.
The limit engine torque load imposed by sudden engine stoppage due to malfunction or structural failure (such as compressor jamming) has been a specific requirement for transport category airplanes since 1957. The size, configuration, and failure modes of jet engines have changed considerably from those envisioned when the engine seizure requirement of § 25.361(b) was first adopted. Current engines are much larger and are now designed with large bypass fans capable of producing much larger torque loads if they become jammed. It is evident from service history that the frequency of occurrence of the most severe sudden engine stoppage events are rare.
Relative to the engine configurations that existed when the rule was developed in 1957, the present generation of engines are sufficiently different and novel to justify issuance of special conditions to establish appropriate design standards. The latest generation of jet engines are capable of producing, during failure, transient loads that are significantly higher and more complex than the generation of engines that were present when the existing standard was developed. Therefore, the FAA has determined that special conditions are needed for the Fairchild Dornier GmbH Model 728-100 airplane.
As discussed above, these special conditions are applicable to the Fairchild Dornier GmbH Model 728-100 airplane. Should Fairchild Dornier apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well under the provisions of section 21.101(a)(1). Fairchild Dornier has submitted applications for certification Start Printed Page 8487of both increased and reduced passenger capacity derivatives of the Model 728-100 airplane. These derivative models are designated the Model 928-100 airplane and the Model 528-100 airplane, respectively. As currently proposed, these derivative models share the same design feature of a high-bypass ratio fan jet engine as the Model 728-100 airplane, and it is anticipated that they will be included in the applicability of these proposed special conditions.
This action affects only certain novel or unusual design features on the Fairchild Dornier GmbH Model 728-100 airplane. It is not a rule of general applicability, and it affects only the applicant who applied to the FAA for approval of these features on the airplane.
Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Fairchild Dornier GmbH Model 728-100 airplanes.
1. Sudden Engine Stoppage. In lieu of compliance with 14 CFR 25.361(b), the following special conditions apply:
a. For turbine engine installations, the engine mounts, pylons and adjacent supporting airframe structure must be designed to withstand 1g level flight loads acting simultaneously with the maximum limit torque loads imposed by each of the following:
b. For auxiliary power unit installations, the power unit mounts and adjacent supporting airframe structure must be designed to withstand 1g level flight loads acting simultaneously with the maximum limit torque loads imposed by the each of the following:
c. For engine supporting structure, an ultimate loading condition must be considered that combines 1g flight loads with the transient dynamic loads resulting from each of the following:
d. The ultimate loads developed from the conditions specified in paragraphs (c)(1) and (c)(2) above are to be multiplied by a factor of 1.0 when applied to engine mounts and pylons and multiplied by a factor of 1.25 when applied to adjacent supporting airframe structure.
[FR Doc. 02-4411 Filed 2-22-02; 8:45 am]