[Federal Register Volume 74, Number 168 (Tuesday, September 1, 2009)]
[Rules and Regulations]
[Pages 45100-45101]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-21056]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE294; Special Conditions No. 23-234-SC]


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Cessna Aircraft 
Company, 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 
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: Effective Date: August 20, 2009.

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:

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 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 and 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 14 CFR part 
25, Sec.  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 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 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 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.
    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

[[Page 45101]]

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: A single point refuel/defuel system.

Discussion of Comments

    Notice of proposed special conditions No. 23-09-01-SC for the 
Cessna Aircraft Company, model 525C airplanes was published in the 
Federal Register on April 15, 2009 (74 FR 17438). No comments were 
received, and the special conditions are adopted as proposed.

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 standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register; however, as the certification date for the Cessna 
Aircraft Company, Model 525C is imminent, the FAA finds that good cause 
exists to make these special conditions effective upon issuance.

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

0
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 Special Conditions

    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 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 August 20, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-21056 Filed 8-31-09; 8:45 am]
BILLING CODE 4910-13-P