[Federal Register: April 12, 2007 (Volume 72, Number 70)]
[Rules and Regulations]
[Page 18380-18383]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12ap07-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27709; Directorate Identifier 2007-CE-028-AD;
Amendment 39-15020; AD 2007-08-03]
RIN 2120-AA64
Airworthiness Directives; 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) to
supersede AD 2006-17-04, which applies to certain Cessna Aircraft
Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes. AD 2006-17-04 currently 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 four reports of
loose fuel lines connected to the fuel servo or fuel flow transducer.
Two reports were of in-flight engine failure on a Model T182T airplane.
A third report was of in-flight engine failure on a Model 206H
airplane. A fourth report was of a Model 172S airplane losing engine
power on final approach. Consequently, this AD would require you to
establish the correct torque values of the end fittings on fuel hoses
for certain Cessna Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes. This AD clarifies that the torque values need to be
physically established and visual inspection only is not sufficient. We
are issuing this AD to detect and correct potential loss of fuel flow,
which may result in partial or complete loss of engine power and/or
uncontrolled engine compartment fire due to fuel leakage forward of the
firewall.
DATES: This AD becomes effective on May 2, 2007.
On May 2, 2007 the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
We must receive any comments on this AD by June 11, 2007.
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.
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.
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
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-2007-27709; Directorate Identifier 2007-CE-028-AD.
FOR FURTHER INFORMATION CONTACT: Trenton Shepherd, Aerospace Engineer,
Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946-4143; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
One report of loose fuel hose connections to the fuel injector
servo on a Cessna Model 172S airplane caused us to issue AD 2006-17-04,
Amendment 39-14725 (71 FR 47711, August 18, 2006). AD 2006-17-04 on
certain Cessna Models 172R, 172S, 182T, T182T, 206H, and T206H
airplanes, currently requires you to:
Inspect the two end fittings on each of the flexible fuel
hoses located in the
[[Page 18381]]
engine compartment for the correct torque values; and
Tighten the hose end fittings to the correct torque
values, if any incorrect torque values are found during the inspection.
Since issuing AD 2006-17-04, we have received four additional
reports of loose fuel lines connected to the fuel servo or fuel flow
transducer. Two reports were of in-flight engine failure on a Model
T182T airplane. A third report was of in-flight engine failure on a
Model 206H airplane. A fourth report was of a Model 172S airplane that
lost engine power on final approach.
In issuing AD 2006-17-04, our intent was for the torque values
provided in Table 4 of the AD to be verified. However, the actions we
specified in AD 2006-17-04 resulted in visual-only inspections being
accomplished in some cases. Visual inspection of torque paint or putty
is not sufficient to address the unsafe condition. This AD clarifies
that the torque values need to be physically established.
This condition, if not corrected, could result in loss of fuel flow
resulting in partial or complete loss of engine power and/or
uncontrolled engine compartment fire due to fuel leakage forward of the
firewall.
Relevant Service Information
We reviewed Cessna Service Bulletin No. SB07-71-01, original issue
dated March 2, 2007, Revision 1, dated March 16, 2007. The service
information describes procedures for a physical inspection of the fuel
hose connections on each of the hoses by loosening each connection and
then reapplying the correct torque value to make sure that they are
correctly torqued.
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 establish the correct torque values of the end fittings on fuel
hoses for certain Cessna Models 172R, 172S, 182T, T182T, 206H, and
T206H airplanes. This AD clarifies that the torque values need to be
physically established and visual inspection only is not sufficient.
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 ``Docket No.
FAA-2007-27709; Directorate Identifier 2007-CE-028-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.
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 removing Airworthiness Directive (AD)
2006-17-04, Amendment 39-14725 (71 FR 47711, August 18, 2006), and by
adding a new AD to read as follows:
2007-08-03 Cessna Aircraft Company: Amendment 39-15020; Docket No.
FAA-2007-27709; Directorate Identifier 2007-CE-028-AD.
Effective Date
(a) This AD becomes effective on May 2, 2007.
[[Page 18382]]
Affected ADs
(b) This AD supersedes AD 2006-17-04; Amendment 39-14725.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
Table 1.--Applicability
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Model Serial Nos.
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(i) 172R...................... 17281244 through 17281364, 17281366
through 17281372, 17281374 through
17281376, and 17281379.
(ii) 172S..................... 172S9809 through 172S10349, 172S10351
through 172S10374, 172S10376 through
172S10423, 172S10425 through 172S10426,
172S10428 through 172S10430, 172S10432
through 172S10444, 172S10446 through
172S10450, and 172S10452 through
172S10454.
(iii) 182T.................... 18281527 through 18281889, 18281892,
18281895, 18281897, 18281899, 18281901,
and 18281904.
(iv) T182T.................... T18208381 through T18208659, T18208661,
T18208663 through T18208678, T18208680
through T18208686, T18208689, and
T18208690.
(v) 206H...................... 20608231 through 20608285.
(vi) T206H.................... T20608515 through T20608662, T20608664
through T20608697, T20608699 through
T20608714, and T20608717.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD is the result of four reports of loose fuel lines
connected to the fuel servo or fuel flow transducer. Two reports
were of in-flight engine failure on a Model T182T airplane. A third
report was of in flight-engine failure on a Model 206H airplane. A
fourth report was of a Model 172S airplane that lost engine power on
final approach. We are issuing this AD to detect and correct
potential loss of fuel flow, which may result in partial or complete
loss of engine power and/or uncontrolled engine compartment fire due
to fuel leakage forward of the firewall.
Compliance
(e) To address this problem, you must do the following, unless
already done:
Table 2.--Actions, Compliance, and Procedures
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Actions Compliance Procedures
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(1) For all airplanes not equipped Within the next 5 hours time-in- Follow Cessna Service Bulletin No.
with the Garmin G1000 System: service (TIS) after May 2, 2007 SB07-71-01, Revision 1, dated March
Establish the correct torque values (the effective date of this AD). 16, 2007; the procedures of the
of the end fittings on each of the appendix to this AD; and the torque
following hoses in the engine values from the table Torque Values
compartment: for Hose End Fittings in the
(i) Fuel strainer to engine fuel appendix to this AD.
pump.
(ii) Engine fuel pump to fuel
injector servo (except T206H).
(iii) T206H only: Engine fuel
pump to the union at the aft
vertical cooling baffle.
(iv) T206H 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 fuel
return to firewall fitting.
(2) For all airplanes equipped with Within the next 5 hours TIS after Follow Cessna Service Bulletin No.
the Garmin G1000 System: Establish May 2, 2007 (the effective date of SB07-71-01, Revision 1, dated March
the correct torque values of the this AD). 16, 2007; the procedures of the
end fittings on each of the appendix to this AD; and the torque
following hoses in the engine values from the table Torque Values
compartment: for Hose End Fittings in the
(i) Fuel strainer to engine fuel appendix to this AD.
pump.
(ii) Engine fuel pump to fuel
injector servo (except T206H).
(iii) T206H only: Engine fuel
pump to the union at the aft
vertical cooling baffle.
(iv) T206H 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 fuel
return to firewall fitting.
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[[Page 18383]]
Special Flight Permit
(f) Under 14 CFR 39.23, we are allowing special flight permits
for the purpose of compliance with this AD under the following
conditions: Only operate under day visual flight rules (VFR).
Alternative Methods of Compliance (AMOCs)
(g) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, ATTN: Trenton Shepherd, Aerospace Engineer, Wichita ACO, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4143; fax: (316) 946-4107, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(h) AMOCs approved for AD 2006-17-04 are not approved for this
AD.
Material Incorporated by Reference
(i) You must use Cessna Service Bulletin No. SB07-71-01,
Revision 1, dated March 16, 2007, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For 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.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Appendix to AD 2007-08-03--Inspection Instructions--Cessna Aircraft
Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes
1. Remove upper and side cowlings to perform torque procedure.
2. Remove all signs of old torque putty or paint.
3. Using a suitable tool loosen the hose end fitting of each
joint, while using a suitable tool to restrain the other end fitting
of the joint to preclude rotation.
4. Using the applicable fitting torque from the table Torque
Values for Hose End Fittings of this appendix to AD 2007-08-03,
torque the hose end fitting to the proper torque, while using a
suitable tool to restrain the other end fitting of the joint to
preclude rotation.
5. After proper torque has been applied to the hose end fitting,
apply the applicable torque paint or putty to the hose end fitting
joint.
6. If during any torque procedure any of the non-hose end
fittings rotate, stop the torque procedure. Totally disconnect the
hose end joint and remove any fitting that has rotated. After the
cleaning, visual examination, and/or replacement of the fitting and/
or any seals or sealant, reinstall the fitting and torque it to the
applicable requirement. Then reconnect the hose end fitting and
repeat Step 4. of this appendix to AD 2007-08-03.
7. Use the table below Torque Values for Hose End Fittings for
the correct torque values to tighten the hose end fittings as
required in paragraphs (e)(1) and (e)(2) of this AD:
Torque Values for Hose End Fittings
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Correct torque in inch-pounds
Flare hex sizes in fractions of an inch Hose size -------------------------------
Minimum Maximum
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\9/16\.......................................................... -4 135 150
\11/16\......................................................... -6 270 300
\7/8\........................................................... -8 450 500
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Issued in Kansas City, Missouri, on April 5, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-6826 Filed 4-11-07; 8:45 am]
BILLING CODE 4910-13-P