AD 2006-17-04

[Federal Register Volume 71, Number 160 (Friday, August 18, 2006)]
[Rules and Regulations]
[Pages 47711-47714]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E6-13442]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25262; Directorate Identifier 2006-CE-39-AD; 
Amendment 39-14725; AD 2006-17-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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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.
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>. The 
docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD.

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.

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

[[Page 47712]]

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.

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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>; 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

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
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               Group                            Model                               Serial Nos.
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(1) Group 1 Airplanes: All models   (i) 172R.....................  17281244 through 17281334.
 not equipped with the Garmin       (ii) 172S....................  172S9809 through 172S10219.
 G1000 System.
                                    (iii) 182T...................  18281527 through 18281832.
                                    (iv) T182T...................  T18208381 through T18208583.
                                    (v) 206H.....................  20608231 through 20608265.
                                    (vi) T206H...................  T20608515 through T20608635.
(2) Group 2 Airplanes: All models   (i) 172R.....................  17281244 through 17281334.
 equipped with the Garmin G1000     (ii) 172S....................   172S9809 through 172S10219.
 System.
                                    (iii) 182T...................  18281527 through 18281832.

[[Page 47713]]

 
                                    (iv) T182T...................  T18208381 through T18208583.
                                    (v) 206H.....................  20608231 through 20608265.
                                    (vi) T206H...................  T20608515 through T20608635.
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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
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           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the two end       Within the next 5     Follow Cessna
 fittings on each of the       hours time-in-        Service Bulletin
 following hoses in the        service (TIS) after   No. SB06-71-02,
 engine compartment for the    September 1, 2006     dated June 19,
 correct torque values.        (the effective date   2006.
(i) Fuel strainer to engine    of this AD), on
 fuel pump..                   airplanes that have
(ii) Engine fuel pump to       not had a 100-hour
 fuel injector server          or annual
 (except T206)..               inspection of the
(iii) T206 only: Engine fuel   engine installation
 pump to the union at the      fuel hoses for
 aft vertical cooling          security and
 baffle..                      tightness of the
(iv) T206 only: Union at the   end fittings.
 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..
(2) If any incorrect torque   Before further        Follow Cessna
 values are found during the   flight after the      Service Bulletin
 inspection required by        inspection required   No. SB06-71-02,
 paragraph (e)(1) of this      by paragraph (e)(1)   dated June 19,
 AD, clean and dry the         of this AD, in        2006.
 threads of all fittings,      which any incorrect
 and tighten the hose end      torque values are
 fittings to the correct       found.
 torque values as defined in
 Table 4.
------------------------------------------------------------------------

    (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
------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the two end       Within the next 5     Follow Cessna
 fittings on each of the       hours TIS after       Service Bulletin
 following hoses in the        September 1, 2006     No. SB06-71-02,
 engine compartment for the    (the effective date   dated June 19,
 correct torque values.        of this AD), on       2006.
(i) Fuel strainer to engine    airplanes that have
 fuel pump..                   not had a 100-hour
(ii) Engine fuel pump to       or annual
 fuel injector servo (except   inspection of the
 T206)..                       engine installation
(iii) T206 only: Engine fuel   fuel hoses for
 pump to the union at the      security and
 aft vertical cooling          tightness of the
 baffle..                      end fittings.

[[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   Before further        Follow Cessna
 values are found during the   flight after the      Service Bulletin
 inspection required by        inspection required   No. SB06-71-02,
 paragraph (f)(1) of this      by paragraph (f)(1)   dated June 19,
 AD, clean and dry the         of this AD, in        2006.
 threads of all fittings,      which any incorrect
 and tighten the hose end      torque values are
 fittings to the correct       found.
 torque values as defined in
 Table 4.
------------------------------------------------------------------------

    (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
----------------------------------------------------------------------------------------------------------------
                                                                                   Correct torque in inch-pounds
             Flare hex sizes in fractions of an inch                 Hose size   -------------------------------
                                                                                      Minimum         Maximum
----------------------------------------------------------------------------------------------------------------
\9/16\..........................................................              -4             135             150
\11/16\.........................................................              -6             270             300
\7/8\...........................................................              -8             450             500
----------------------------------------------------------------------------------------------------------------

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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a> 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>. The docket number is FAA-2006-
25262; Directorate Identifier 2006-CE-39-AD.

    Issued in Kansas City, Missouri, on August 9, 2006.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-13442 Filed 8-17-06; 8:45 am]
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