Special Conditions: Cessna Aircraft Company, Model 525C; High Fuel Temperature

Federal Register: September 1, 2009 (Volume 74, Number 168)

Proposed Rules

Page 45133-45135

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

DOCID:fr01se09-13

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 14 CFR Part 23

Docket No. CE299; Notice No. 23-09-03-SC

Special Conditions: Cessna Aircraft Company, Model 525C; High

Fuel Temperature

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

SUMMARY: This notice proposes special conditions for the Cessna

Aircraft Company, Model 525C airplane. This airplane will have a novel or unusual design feature(s) associated with high fuel temperature. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. 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.

DATES: Comments must be received on or before October 1, 2009.

ADDRESSES: Comments on this proposal may be mailed in duplicate to:

Federal Aviation Administration, Regional Counsel, ACE-7, Attention:

Rules Docket, Docket No. CE299, 901 Locust, Room 506, Kansas City,

Missouri 64106, or delivered in duplicate to the Regional Counsel at the above address. Comments must be marked: CE299. 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: Peter L. Rouse, Federal Aviation

Administration, Aircraft Certification Service, Small Airplane

Directorate, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4135, fax 816-329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of these proposed special conditions by submitting such written data, views, or arguments as they may desire. Communications should identify the regulatory docket or notice number and be submitted in duplicate to the address specified above. All communications received on or before the closing date for comments will be considered by the Administrator.

The proposals described in this notice may be changed in light of the comments received. All comments received will be available in the Rules

Docket for examination by interested persons, both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerning this rulemaking will be filed in the docket. Persons wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must include with those comments a self-addressed, stamped postcard on which the following statement is made: ``Comments to CE299.'' The postcard will be date stamped and returned to the commenter.

Background

On August 9, 2006, Cessna Aircraft Company applied for an amendment to Type Certificate Number A1WI to include the new model 525C (CJ4).

The model 525C (CJ4), which is a derivative of the model 525B (CJ3) currently approved under Type Certificate Number A1WI, is a commuter category, low-winged monoplane with ``T'' tailed vertical and horizontal stabilizers, retractable tricycle type landing gear and twin turbofan engines mounted on the aircraft fuselage. The maximum takeoff weight is 16,950 pounds, the VMO/MMOis 305 KIAS/

M 0.77 and maximum altitude is 45,000 feet.

The Cessna Model 525C (CJ4) fuel tank system is similar to other

Cessna Model 525 designs which use the Williams FJ44 series of engine.

The fuel tank system is configured to reject engine heat through the airplane fuel tank system by using an engine oil/fuel heat exchanger.

Certified as part of the engine, the engine oil/fuel heat exchanger cools the oil and heats the fuel. Over time the engine manufacturers have optimized the design, size, placement, and space management of the oil/fuel heat exchanger such that today's engines now reject more heat back into the airplane fuel tank system than has existed in the past.

As can be seen by the chart below we are now exposing the fuel tank system and airplane to temperatures above the critical temperature test requirements of Sec. Sec. 23.961 and 23.965(d), which has been the FAA standard for fuel system hot weather operations and fuel tank test and evaluation since 1951.

Page 45134

IM max. fuel pump inlet

Aircraft model

Engine model

Motive flow

Fuel tank

Fuel pump

temp. (sea

([deg]F)

([deg]F)

inlet ([deg]F)

level)

([deg]F)

525, CJ1+..................... FJ44-1AP........

205

115

165

255 525A, CJ2..................... FJ44-2C.........

230

140

188

200 525B, CJ3..................... FJ44-3A.........

202

117

155

200

14 CFR part 23 certification experience to date has shown that fuel system hot weather certification testing with 110 [deg]F fuel temperatures is adequate for fuel system operations for fuel tank temperatures characterized by ambient air temperatures including cooling as a result of the atmospheric temperature lapse rate. Heating of the fuel that increases the airplane fuel tank system operational temperatures introduces a number of fuel tank system and airplane concerns. Each must be shown to be acceptable. Compliance by design

(i.e. lack of ability to shutoff the engine motive flow) may be utilized although associated type certificate data sheet information may also be necessary to assure future system changes are compliant.

The following are those concerns:

Evaluation of engine, fuel tank system and airplane performance and engine compatibility with elevated fuel tank system temperatures. [Sec. Sec. 23.901(e)(1) and (e)(2), 23.939(a), and 23.951(a)]

Evaluation of fuel tank system and airplane performance due to fuel degradation and resultant byproducts at elevated fuel tank system temperatures. [Sec. Sec. 23.961, 23.939(a), 23.993(e), 23.1301, and 23.1529)]

Evaluation of fuel tank system and airplane performance and engine compatibility due to the higher vapor/liquid ratios with elevated fuel tank system temperatures. [Sec. Sec. 23.903(f), 23.951(a), 23.955(a) and (f), 23.961, and 23.1301]

Evaluation of fuel tank system and airplane performance and engine compatibility due to the solubility of water and potential for greater microbial growth with elevated fuel tank system temperatures. [Sec. Sec. 23.951(c) and 23.971]

Evaluation of fuel tank system and airplane performance due to elevated fuel tank system material temperatures and surrounding structure compatibility. [Sec. Sec. 23.613(c), 23.963(a), 23.965(d), and 23.993(e)]

Evaluation of fuel tank system component qualification as a result of elevated fuel tank system temperatures. [Sec. Sec. 23.1301 and 23.1309]

Evaluation of service/maintenance instructions, activities and personnel due to elevated fuel tank system temperatures. [Sec. 23.1529]

Type Certification Basis

Under the provisions of Sec. 21.101, Cessna Aircraft Company must show that the model 525C meets the applicable provisions of the regulations incorporated by reference in Type Certificate Number A1WI or the applicable regulations in effect on the date of application for the change to the model 525C. The regulations incorporated by reference in the type certificate are commonly referred to as the ``original type certification basis.'' In addition, the certification basis includes exemptions, if any; equivalent level of safety findings, if any; and the special condition adopted by this rulemaking action.

If the Administrator finds that the applicable airworthiness regulations in 14 CFR part 23 do not contain adequate or appropriate safety standards for the model 525C because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 21.16.

In addition to the applicable airworthiness regulations and special conditions, the model 525C 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.

Special conditions, as appropriate, as defined in Sec. 11.19, are issued in accordance with Sec. 11.38, and become part of the type certification basis in accordance with Sec. 21.101(b)(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, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, the special conditions would also apply to the other model under the provisions of Sec. 21.101.

Novel or Unusual Design Features

The model 525C will incorporate the following novel or unusual design features:

High Fuel Temperatures.

Applicability

As discussed above, these special conditions are applicable to the

Model 525C. Should Cessna Aircraft Company apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the 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 on one model, model 525C, of airplanes. 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.

List of Subjects in 14 CFR Part 23

Aircraft, Aviation safety, Signs and symbols.

Citation

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19.

The Proposed Special Conditions

Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the Cessna Aircraft Company, model 525C airplanes. 1. SC Sec. 23.961:

Instead of compliance with Sec. 23.961, the following apply:

Each fuel system must be free from vapor lock when using fuel at its critical temperature, with respect to vapor formation, when operating the airplane in all critical operating and environmental conditions for which approval is requested. For turbine fuel, the initial temperature must be 110 [deg]F, -0[deg], +5 [deg]F or the maximum outside air temperature for which approval is requested or the fuel tank system temperature that is determined to be more critical.

Page 45135

Issued in Kansas City, Missouri on August 20, 2009.

Kim Smith,

Manager, Small Airplane Directorate, Aircraft Certification Service.

FR Doc. E9-21057 Filed 8-31-09; 8:45 am

BILLING CODE 4910-13-P