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Airworthiness Directives; The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes

Document Details

Information about this document as published in the Federal Register.

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Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Final rule; request for comments.

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from one report of loose fuel hose connections to the fuel injector servo on a Cessna Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire.

DATES:

This AD becomes effective on September 1, 2006.

As of September 1, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.

We must receive any comments on this AD by October 17, 2006.

ADDRESSES:

Use one of the following addresses to comment on this AD.

  • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
  • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
  • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001.
  • Fax: (202) 493-2251.
  • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

To get the service information identified in this AD, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-9006.

To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Jeff Janusz, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4148; facsimile: (316) 946-4107.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

We have received one report of loose fuel hose connections to the fuel injector servo on a Cessna Model 172S airplane.

This condition, if not corrected, could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire.

Relevant Service Information

We reviewed Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. The service information describes procedures for inspecting the two end Start Printed Page 47712fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values.

FAA's Determination and Requirements of This AD

We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires you to do the actions in the referenced service bulletin.

In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number “FAA-2006-25262; Directorate Identifier 2006-CE-39-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments.

We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

(1) Is not a “significant regulatory action” under Executive Order 12866;

(2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at http://dms.dot.gov;​ or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Start List of Subjects

List of Subjects in 14 CFR Part 39

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Adoption of the Amendment

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Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend

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PART 39—AIRWORTHINESS DIRECTIVES

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1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Amended]
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2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

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2006-17-04 The Cessna Aircraft Company: Amendment 39-14725; Docket No. FAA-2006-25262; Directorate Identifier 2006-CE-39-AD.

Effective Date

(a) This AD becomes effective on September 1, 2006.

Affected ADs

(b) None.

Applicability

(c) This AD affects the following airplane models and serial numbers that are certificated in any category:

Table 1.—Applicability and Airplane Groups

GroupModelSerial Nos.
(1) Group 1 Airplanes: All models not equipped with the Garmin G1000 System(i) 172R (ii) 172S17281244 through 17281334. 172S9809 through 172S10219.
(iii) 182T18281527 through 18281832.
(iv) T182TT18208381 through T18208583.
(v) 206H20608231 through 20608265.
(vi) T206HT20608515 through T20608635.
(2) Group 2 Airplanes: All models equipped with the Garmin G1000 System(i) 172R (ii) 172S17281244 through 17281334. 172S9809 through 172S10219.
(iii) 182T18281527 through 18281832.
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(iv) T182TT18208381 through T18208583.
(v) 206H20608231 through 20608265.
(vi) T206HT20608515 through T20608635.

Unsafe Condition

(d) This AD is the result of one report of loose fuel hose connections to the fuel injector servo on a Cessna Aircraft Company Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire.

Compliance

(e) For Group 1 Airplanes not equipped with the Garmin G1000 System: To address this problem, you must do the following:

Table 2.—Actions, Compliance, and Procedures for Group 1 Airplanes

ActionsComplianceProcedures
(1) Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values (i) Fuel strainer to engine fuel pump. (ii) Engine fuel pump to fuel injector server (except T206). (iii) T206 only: Engine fuel pump to the union at the aft vertical cooling baffle. (iv) T206 only: Union at the aft vertical cooling baffle to the fuel injector servo. (v) Fuel injector servo to fuel manifold valve (except turbo models). (vi) Turbo models only: Fuel injector servo to fuel flow transducer. (vii) Turbo models only: Fuel flow transducer to fuel manifold valve. (viii) Fuel injector servo return to firewall fitting.Within the next 5 hours time-in-service (TIS) after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittingsFollow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.
(2) If any incorrect torque values are found during the inspection required by paragraph (e)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4Before further flight after the inspection required by paragraph (e)(1) of this AD, in which any incorrect torque values are foundFollow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(f) For Group 2 Airplanes equipped with the Garmin G1000 System: To address this problem, you must do the following:

Table 3.—Actions, Compliance, and Procedures for Group 2 Airplanes

ActionsComplianceProcedures
(1) Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values (i) Fuel strainer to engine fuel pump. (ii) Engine fuel pump to fuel injector servo (except T206). (iii) T206 only: Engine fuel pump to the union at the aft vertical cooling baffle.Within the next 5 hours TIS after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittingsFollow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.
Start Printed Page 47714
(iv) T206 only: Union at the aft vertical cooling baffle to the fuel injector servo.
(v) Fuel injector servo to fuel flow transducer.
(vi) Fuel flow transducer to fuel manifold valve.
(vii) Fuel injector servo return to firewall fitting.
(2) If any incorrect torque values are found during the inspection required by paragraph (f)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4Before further flight after the inspection required by paragraph (f)(1) of this AD, in which any incorrect torque values are foundFollow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006.

(g) Use the following table for the correct torque values to tighten the hose end fittings as required in paragraphs (e)(2) and (f)(2) of this AD:

Table 4.—Torque Values for Hose End Fittings

Flare hex sizes in fractions of an inchHose sizeCorrect torque in inch-pounds
MinimumMaximum
9/16−4135150
11/16−6270300
7/8−8450500

Alternative Methods of Compliance (AMOCs)

(h) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Jeff Janusz, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4148; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

(i) You must do the actions required by this AD following the instructions in Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-9006. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD.

Start Signature

Issued in Kansas City, Missouri, on August 9, 2006.

John R. Colomy,

Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

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[FR Doc. E6-13442 Filed 8-17-06; 8:45 am]

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