Airworthiness Directives; The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes, 47711-47714 [E6-13442]
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47711
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE—Continued
Service Bulletin
Revision level
Date
Boeing Service Bulletin MD11–34–129 ...............................................................................................
Boeing Service Bulletin MD11–34–130 ...............................................................................................
McDonnell Douglas Service Bulletin MD11–34–085 ...........................................................................
Original ..................
Original ..................
01 ..........................
September 22, 2004.
March 16, 2005.
September 20, 1999.
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 2 of this AD
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Boeing
Boeing
Boeing
Boeing
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
MD10–31–053
MD11–34–068
MD11–34–129
MD11–34–130
...............................................................................................
...............................................................................................
...............................................................................................
...............................................................................................
(2) On November 26, 2001 (66 FR 53335,
October 22, 2001), the Director of the Federal
Register approved the incorporation by
reference of McDonnell Douglas Service
Bulletin MD11–34–085, Revision 01, dated
September 20, 1999.
(3) Contact Boeing Commercial Airplanes,
Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846,
Attention: Data and Service Management,
Dept. C1–L5A (D800–0024), for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
3, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–13448 Filed 8–17–06; 8:45 am]
BILLING CODE 4910–13–P
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]
rwilkins on PROD1PC63 with RULES
RIN 2120–AA64
Airworthiness Directives; The Cessna
Aircraft Company Models 172R, 172S,
182T, T182T, 206H, and T206H
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Aug<31>2005
18:30 Aug 17, 2006
Revision level
Jkt 208001
Final rule; request for
comments.
ACTION:
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 https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
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Date
1 ............................
3 ............................
Original ..................
Original ..................
June 14, 2005.
April 6, 2005.
September 22, 2004.
March 16, 2005.
• 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 https://dms.dot.gov. 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
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47712
Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
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 2006CE–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 https://
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
https://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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
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
Model
Serial Nos.
(1) Group 1 Airplanes: All models not equipped with the Garmin G1000 System ...........
rwilkins on PROD1PC63 with RULES
Group
(i) 172R ..................
(ii) 172S .................
(iii) 182T .................
(iv) T182T ..............
(v) 206H .................
(vi) T206H ..............
(i) 172R ..................
(ii) 172S .................
(iii) 182T .................
17281244 through 17281334.
172S9809 through 172S10219.
18281527 through 18281832.
T18208381 through T18208583.
20608231 through 20608265.
T20608515 through T20608635.
17281244 through 17281334.
172S9809 through 172S10219.
18281527 through 18281832.
(2) Group 2 Airplanes: All models equipped with the Garmin G1000 System .................
VerDate Aug<31>2005
18:30 Aug 17, 2006
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Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
47713
TABLE 1.—APPLICABILITY AND AIRPLANE GROUPS—Continued
Group
(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
Serial Nos.
(iv) T182T ..............
(v) 206H .................
(vi) T206H ..............
Unsafe Condition
Model
T18208381 through T18208583.
20608231 through 20608265.
T20608515 through T20608635.
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
Actions
Compliance
Procedures
(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.
(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
4.
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 fittings.
Follow Cessna Service Bulletin No. SB06–71–
02, dated June 19, 2006.
Before further flight after the inspection re- Follow Cessna Service Bulletin No. SB06–71–
quired by paragraph (e)(1) of this AD, in
02, dated June 19, 2006.
which any incorrect torque values are found.
(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
Compliance
Procedures
(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.
rwilkins on PROD1PC63 with RULES
Actions
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 fittings.
Follow Cessna Service Bulletin No. SB06–71–
02, dated June 19, 2006.
VerDate Aug<31>2005
19:19 Aug 17, 2006
Jkt 208001
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Federal Register / Vol. 71, No. 160 / Friday, August 18, 2006 / Rules and Regulations
TABLE 3.—ACTIONS, COMPLIANCE, AND PROCEDURES FOR GROUP 2 AIRPLANES—Continued
Actions
Compliance
(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
4.
(g) Use the following table for the correct
torque values to tighten the hose end fittings
Procedures
Before further flight after the inspection re- Follow Cessna Service Bulletin No. SB06–71–
quired by paragraph (f)(1) of this AD, in
02, dated June 19, 2006.
which any incorrect torque values are found.
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
¥4
¥6
¥8
⁄
................................................................................................................................................
..............................................................................................................................................
7⁄8 .................................................................................................................................................
9 16
⁄
11 16
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.
rwilkins on PROD1PC63 with RULES
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: https://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 https://
dms.dot.gov. The docket number is FAA–
2006–25262; Directorate Identifier 2006–CE–
39–AD.
VerDate Aug<31>2005
18:30 Aug 17, 2006
Jkt 208001
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]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24641; Directorate
Identifier 2006–CE–27–AD; Amendment 39–
14724; AD 2006–17–03]
RIN 2120–AA64
Airworthiness Directives; Stemme
GmbH & Co. KG Models S10, S10–V,
and S10–VT Sailplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Stemme GmbH & Co. KG (Stemme)
Models S10, S10–V, and S10–VT
sailplanes. This AD requires you to
inspect the connection between the
aileron push-rod and the connecting
shaft to determine if a safety washer is
installed. If there is no safety washer
installed, this AD requires you to
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
135
270
450
Maximum
150
300
500
modify the aileron control assembly.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by the airworthiness
authority for Germany. We are issuing
this AD to prevent a loose bearing in the
aileron control lever, which could result
in separation of the aileron control
system. Separation of the aileron control
system could lead to loss of aileron
control.
DATES: This AD becomes effective on
September 22, 2006.
As of September 22, 2006, the
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulation.
ADDRESSES: To get the service
information identified in this AD,
contact STEMME AG, Flugplatzstrabe F
2, Nr. 7, D–15344 Strausberg, Germany;
telephone: + 49.33.41/36 12–0;
facsimile: + 49.33.41/36 12–30; e-mail:
P.Ellwanger@stemme.de.
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–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–24641; Directorate Identifier
2006–CE–27–AD.
FOR FURTHER INFORMATION CONTACT:
Gregory A. Davison, Aerospace
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]]>Agencies
[Federal Register Volume 71, Number 160 (Friday, August 18, 2006)]
[Rules and Regulations]
[Pages 47711-47714]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13442]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 https://dms.dot.gov. 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 https://
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 https://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 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
----------------------------------------------------------------------------------------------------------------
Group Model Serial Nos.
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------
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
------------------------------------------------------------------------
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: https://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 https://dms.dot.gov. 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]
BILLING CODE 4910-13-P
