[Federal Register Volume 74, Number 71 (Wednesday, April 15, 2009)]
[Proposed Rules]
[Pages 17438-17439]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-8583]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 74, No. 71 / Wednesday, April 15, 2009 / 
Proposed Rules  

[[Page 17438]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE294; Notice No. 23-09-01-SC]


Special Conditions: Cessna Aircraft Company, Model 525C; Single 
Point Refuel/Defuel System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

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SUMMARY: This action proposes special conditions for the Cessna Model 
525C airplane. This airplane will have a novel or unusual design 
feature(s) associated with a Single Point Refuel/Defuel system. 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: We must receive your comments by May 15, 2009.

ADDRESSES: Mail two copies of your comments to: Federal Aviation 
Administration, Regional Counsel, ACE-7, Attention: Rules Docket, 
Docket No. CE294, 901 Locust, Room 506, Kansas City, Missouri 64106. 
You may deliver two copies to the Regional Counsel at the above 
address. Mark your comments: Docket No. CE294. You may inspect comments 
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

    We invite interested people to take part in this rulemaking by 
sending 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 special conditions. You may inspect the docket before 
and after the comment period closing date. If you wish to review the 
docket in person, go to the address in the ADDRESSES section of this 
preamble 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 
these special conditions based on 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

    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 16,650 pounds, the VMO/MMO is 305 KIAS/
M 0.77 and maximum altitude is 45,000 feet.
    The model 525C fuel system will incorporate a Single Point Refuel/
Defuel system. The model 525C Single Point Refuel/Defuel system is used 
to pressure refuel and defuel the left and right wing fuel tanks from a 
single refuel/defuel adapter. The system is operated by fuel level and 
positive refuel or negative defuel pressure. This system is similar in 
design to other 14 CFR part 25 Cessna Citation airplanes and uses many 
of the same components that are used in these other airplanes. The 
components for the model 525C refuel/defuel system include a refuel/
defuel adapter, a precheck valve, various other check valves, a high 
level pilot valve, a refuel valve, a defuel valve, and a positive/
negative relief valve. Single point refueling is accomplished by 
connecting the refuel equipment to the refuel/defuel adapter and 
applying positive pressure. Fuel is directed through a common manifold 
to each wing tank's fuel shutoff (refuel) valve. Single point defueling 
is accomplished by connecting defuel equipment to the refuel/defuel 
adapter and applying negative pressure. Defueling is controlled by fuel 
level and negative pressure from the defuel equipment.
    The incorporation of a pressure defueling system was not considered 
when 14 CFR part 23 was created; thus, there are no applicable 
certification requirements for this novel and unusual design feature. 
Pressure defueling systems are more common on part 25 airplanes, and 
the applicable certification requirements are contained in part 25, 
section 25.979(e), which states: ``The airplane defueling system (not 
including fuel tanks and fuel tank vents) must withstand an ultimate 
load that is 2.0 times the load arising from the maximum permissible 
defueling pressure (positive or negative) at the airplane fueling 
connection.'' With the pressure defueling system design incorporated on 
the model 525C it is necessary to apply a special condition to this 
novel and unusual design feature.

Type Certification Basis

    Under the provisions of section 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 525B. 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

[[Page 17439]]

condition adopted by this rulemaking action.
    If the Administrator finds that the applicable airworthiness 
regulations in 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 
section 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.
    The FAA issues special conditions, as appropriate, as defined in 
section 11.19, under section 11.38, and they become part of the type 
certification basis under section 21.101.
    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 section 21.101.

Novel or Unusual Design Features

    The model 525C will incorporate the following novel or unusual 
design features:
    A single point refuel/defuel system.

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.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of 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.

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 
21.17; 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 Cessna Aircraft Company model 525C airplanes.

1. SC25.979(e)

    The airplane defueling system (not including fuel tanks and fuel 
tank vents) must withstand an ultimate load that is 2.0 times the load 
arising from the maximum permissible defueling pressure (positive or 
negative) at the airplane fueling connection.

    Issued in Kansas City, Missouri on April 8, 2009.
John Colomy,
Acting Manager, Small Airplane Directorate Aircraft Certification 
Service.
 [FR Doc. E9-8583 Filed 4-14-09; 8:45 am]
BILLING CODE 4910-13-P