Airworthiness Directives; Cessna Aircraft Company Models 172R and 172S Airplanes, 5737-5739 [E8-1460]
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Federal Register / Vol. 73, No. 21 / Thursday, January 31, 2008 / Rules and Regulations
Cessna Model 650; Citations III, VI, and VII
Dassault-Aviation 20, 50, 50EX, 900,
MF900, and 900EX (900DX) Series
Gulfstream Aerospace LP (formerly IAI)
1125 Westwind Astra, Astra SPX, Gulfstream 100 Series
Israel Aircraft Industries (IAI) 1124 Series
(Westwind 1124)
Learjet 31, 35, 36, 45 (or Learjet 40), and 55
Series
Lockheed-Georgia 3329–25 Series (731
Jetstar, Jetstar II)
Raytheon Corporate Jets (formerly British
Aerospace) Hawker 800 and 850 Series
Sabreliner NA–265–65 (Sabreliner 65)
For All Engines
Unsafe Condition
(d) This AD results from the
manufacturer’s report that some HP turbine
rotor discs received improperly machined
radii in the root of the forward and aft curvic
teeth during manufacture. We are issuing this
AD to prevent uncontained failure of the HP
turbine rotor assembly, which could result in
damage to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
TFE731–2C, –3B, –3BR, –3C, –3CR, –3D,
–3DR, –4R, –5AR, –5BR, and –5R Series
Turbofan Engines
(f) For TFE731–2C, –3B, –3BR, –3C, –3CR,
–3D, –3DR, –4R, –5AR, –5BR, and –5R series
turbofan engines, remove HP turbine rotor
assemblies from service containing HP
turbine rotor discs, part number (P/N)
3075772–1, having any serial number (SN) in
Table 1 of Honeywell Service Bulletin (SB)
No. TFE731–72–3720, dated July 5, 2006. Use
the following drawdown schedule:
(1) For HP turbine discs with 4,200 cyclessince-new (CSN) or more on the effective
date of this AD, remove HP turbine rotor
assemblies within 100 cycles-in-service (CIS)
after the effective date of this AD.
(2) For HP turbine discs with fewer than
4,200 CSN on the effective date of this AD,
remove HP turbine rotor assemblies at the
next access to the HP turbine rotor discs, but
not to exceed 4,300 CSN.
pwalker on PROD1PC71 with RULES
TFE731–20R, –20AR, –20BR, –40, –40AR,
–40R, and –60 Series Turbofan Engines
(g) For TFE731–20R, –20AR, –20BR, –40,
–40AR, –40R, and –60 series turbofan
engines, remove HP turbine rotor assemblies
from service containing HP turbine rotor
discs, P/N 3060841–1, having any SN in
Table 1 of Honeywell Alert SB No. TFE731–
A72–5185, dated July 5, 2006. Use the
following drawdown schedule:
(1) For HP turbine discs with 3,200 CSN or
more on the effective date of this AD, remove
HP turbine rotor assemblies within 100 CIS
after the effective date of this AD.
(2) For HP turbine discs with fewer than
3,200 CSN on the effective date of this AD,
remove HP turbine rotor assemblies at the
next access to the turbine rotor discs, but not
to exceed 3,300 CSN.
VerDate Aug<31>2005
17:48 Jan 30, 2008
Jkt 214001
5737
Issued in Burlington, Massachusetts, on
January 16, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–1238 Filed 1–30–08; 8:45 am]
(h) HP turbine rotor discs removed per
paragraphs (f) and (g) of this AD must pass
a curvic root radius inspection performed by
Honeywell Engines, Systems and Services,
Phoenix, Arizona, Certificate Repair Station
No. ZN3R030M, before the discs are eligible
for reinstallation in an engine.
(i) For the purposes of this AD, access to
the HP turbine rotor discs is defined as the
removal of the HP turbine rotor assembly
from the engine.
BILLING CODE 4910–13–P
Alternative Methods of Compliance
14 CFR Part 39
(j) The Manager, Los Angeles Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
[Docket No. FAA–2007–29138; Directorate
Identifier 2007–CE–073–AD; Amendment
39–15351; AD 2008–03–02]
Related Information
Airworthiness Directives; Cessna
Aircraft Company Models 172R and
172S Airplanes
(k) Contact Joseph Costa, Aerospace
Engineer, Los Angeles Aircraft Certification
Office, FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA
90712–4137; e-mail: joseph.costa@faa.gov;
telephone: (562) 627–5246; fax: (562) 627–
5210, for more information about this AD.
(l) For more information regarding the
engine manufacturer’s accomplishment
instructions or material information, refer to
Honeywell Alert SB No. TFE731–A72–5185,
dated July 5, 2006, and SB No. TFE731–72–
3720, dated July 5, 2006.
(m) Also, for technical support regarding
the curvic root dimensional inspection
criteria, contact the Technical Operations
Center: telephone: (800) 601–3099 (U.S.) or
(602) 365–3099 (International) and press
option #9; e-mail:
AeroTechSupport@Honeywell.com; or fax:
(602) 365–3343.
Material Incorporated by Reference
(n) You must use Table 1 of Honeywell
Alert Service Bulletin No. TFE731–A72–
5185, dated July 5, 2006, or Table 1 of
Honeywell Service Bulletin No. TFE731–72–
3720, dated July 5, 2006, as applicable, to
determine SN applicability of HP turbine
rotor discs requiring removal by this AD. The
Director of the Federal Register approved the
incorporation by reference of these service
bulletins in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Honeywell
Technical Publications and Distribution,
M/S 2101–201, P.O. Box 52170, Phoenix, AZ
85072–2170; telephone: (602) 365–2493
(General Aviation), (602) 365–5535
(Commercial Aviation), fax: (602) 365–5577
(General Aviation and Commercial Aviation)
for a copy of this service information. You
may review copies at the FAA, New England
Region, 12 New England Executive Park,
Burlington, MA; 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Models 172R and 172S airplanes. This
AD requires you to inspect the fuel
return line assembly for chafing; replace
the fuel return line assembly if chafing
is found; and inspect the clearance
between the fuel return line assembly
and both the right steering tube
assembly and the airplane structure,
adjusting as necessary. This AD results
from reports of chafed fuel return line
assemblies, which were caused by the
fuel return line assembly rubbing
against the right steering tube assembly
during full rudder pedal actuation. We
are issuing this AD to detect and correct
chafing of the fuel return line assembly,
which could result in fuel leaking under
the floor and fuel vapors entering the
cabin. This condition could lead to fire
under the floor or in the cabin area.
DATES: This AD becomes effective on
March 6, 2008.
On March 6, 2008, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Cessna
Aircraft Company, Product Support,
P.O. Box 7706, Wichita, Kansas 67277;
telephone: (316) 517–5800; fax: (316)
942–9006.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
E:\FR\FM\31JAR1.SGM
31JAR1
5738
Federal Register / Vol. 73, No. 21 / Thursday, January 31, 2008 / Rules and Regulations
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2007–29138;
Directorate Identifier 2007–CE–073–
AD.
FOR FURTHER INFORMATION CONTACT: Jeff
Janusz, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4148; fax: (316) 946–4107; e-mail:
jeff.janusz@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 17, 2007, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Cessna Models 172R and 172S
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on
October 24, 2007 (72 FR 60291). The
NPRM proposed to require you to detect
and correct chafing of the fuel return
line assembly.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Differences Between This AD and the
Service Information
The service information permits tube
damage up to a depth of 0.0035 inch.
There is no known method to accurately
measure the thickness damage on a
tube. We require replacement of the fuel
return line assembly if any damage is
found.
If no chafing is found in the
inspection of the fuel return line
assembly, the service information does
not require inspection for clearance
around the fuel return line assembly.
We require you to inspect the clearance
between the fuel return line assembly
and both the right steering tube
assembly and airplane structure, for all
applicable aircraft.
The service information does not
specify a minimum clearance
requirement between the fuel return line
assembly and the right steering tube
assembly, only that the fuel return line
assembly does not touch either the right
steering tube assembly or the airplane
structure. We require a minimum of 0.5
inch of clearance between the fuel
return line assembly and both the right
steering tube assembly and the airplane
structure, during full rudder pedal
actuation.
The requirements of this AD take
precedence over the provisions in the
service information.
Costs of Compliance
We estimate that this AD affects 928
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
1 work-hour × $80 per hour = $80 ..............................................................................................
N/A
$80
$74,240
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
inspection. We have no way of
determining the number of airplanes
that may need this replacement:
Labor cost
Parts cost
Total cost per
airplane
0.5 work-hour × $80 per hour = $40 .......................................................................................................................
$123
$163
pwalker on PROD1PC71 with RULES
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 AD.
Regulatory Findings
We have 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 the
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
VerDate Aug<31>2005
17:48 Jan 30, 2008
Jkt 214001
PO 00000
Frm 00030
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Sfmt 4700
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2007–29138;
Directorate Identifier 2007–CE–073–
AD’’ in your request.
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 Federal Aviation Administration
I
E:\FR\FM\31JAR1.SGM
31JAR1
Federal Register / Vol. 73, No. 21 / Thursday, January 31, 2008 / Rules and Regulations
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Unsafe Condition
(a) This AD becomes effective on March 6,
2008.
(d) This AD results from reports of chafed
fuel return line assemblies caused by the fuel
return line assembly rubbing against the right
steering tube assembly during full rudder
pedal actuation. We are issuing this AD to
detect and correct chafing of the fuel return
line assembly, which could result in fuel
leaking under the cabin floor and fuel vapors
entering the cabin. This condition could lead
to fire under the floor or in the cabin area.
(b) None.
1. The authority citation for part 39
continues to read as follows:
Applicability
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Effective Date
Affected ADs
I
[Amended]
5739
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
2. FAA amends § 39.13 by adding the
following new AD:
Models
Serial Nos.
2008–03–02 Cessna Aircraft Company:
Amendment 39–15351; Docket No.
FAA–2007–29138; Directorate Identifier
2007–CE–073–AD.
172R .........
172S .........
17281188 through 17281390.
172S9491 through 172S10489.
I
Compliance
(e) To address this problem, you must do
the following, unless already done:
Note: The requirements of this AD take
precedence over the actions required in the
service information.
Actions
Compliance
Procedures
(1) Inspect the fuel return line assembly
(Cessna part number (P/N) 0500118–49 or
FAA-approved equivalent P/N) for chafing.
Within the next 100 hours time-in-service
(TIS) after March 6, 2008 (the effective date
of this AD) or within the next 12 months
after March 6, 2008 (the effective date of
this AD), whichever occurs first.
Before further flight after the inspection required in paragraph (e)(1) of this AD where
evidence of chafing was found.
Follow Cessna Service Bulletin SB07–28–01,
dated June 18, 2007.
(2) If chafing is found in the inspection required
in paragraph (e)(1) of this AD, replace the
fuel return line assembly (Cessna P/N
0500118–49 or FAA-approved equivalent P/
N).
(3) Inspect for a minimum clearance of 0.5 inch
between the following parts throughout the
entire range of copilot rudder pedal travel
and adjust the clearance as necessary:
Follow Cessna Service Bulletin SB07–28–01,
dated June 18, 2007.
Before further flight after:
(A) The inspection required in paragraph
(e)(1) of this AD if no chafing is found; or
(B) The replacement required in paragraph
(e)(2) of this AD.
Follow paragraph 6 of the Instructions section
of Cessna Service Bulletin SB07–28–01,
dated June 18, 2007. This AD requires a
minimum clearance of 0.5 inch.
Product Support, P.O. Box 7706, Wichita,
Kansas 67277; telephone: (316) 517–5800;
fax: (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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
(i) The fuel return line assembly (Cessna
P/N 0500118–49 or FAA-approved
equivalent P/N) and the steering tube
assembly (Cessna P/N MC0543022–
2C); and
(ii) The fuel return line assembly (Cessna
P/N 0500118–49 or FAA-approved
equivalent P/N) and the airplane structure.
pwalker on PROD1PC71 with RULES
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Jeff
Janusz, Aerospace Engineer, 1801 Airport
Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4148; fax: (316) 946–
4107; e-mail: jeff.janusz@faa.gov. 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.
Material Incorporated by Reference
(g) You must use Cessna Service Bulletin
SB07–28–01, dated June 18, 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 Cessna Aircraft Company,
VerDate Aug<31>2005
17:48 Jan 30, 2008
Jkt 214001
Issued in Kansas City, Missouri, on January
22, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–1460 Filed 1–30–08; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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Sfmt 4700
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–0276; Airspace
Docket No. 07–AEA–16]
Establishment of Class E Airspace;
Lewisburg, PA
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule, request for
comments.
AGENCY:
SUMMARY: This action establishes Class
E Airspace at Lewisburg, PA to support
a new Area Navigation (RNAV) Global
Positioning System (GPS) Special
Instrument Approach Procedure (IAP)
that has been developed for medical
flight operations into the Evangelical
Community Hospital East Heliport. This
action enhances the safety and
E:\FR\FM\31JAR1.SGM
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]]>Agencies
[Federal Register Volume 73, Number 21 (Thursday, January 31, 2008)]
[Rules and Regulations]
[Pages 5737-5739]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1460]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29138; Directorate Identifier 2007-CE-073-AD;
Amendment 39-15351; AD 2008-03-02]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 172R and
172S Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna) Models 172R and 172S airplanes. This
AD requires you to inspect the fuel return line assembly for chafing;
replace the fuel return line assembly if chafing is found; and inspect
the clearance between the fuel return line assembly and both the right
steering tube assembly and the airplane structure, adjusting as
necessary. This AD results from reports of chafed fuel return line
assemblies, which were caused by the fuel return line assembly rubbing
against the right steering tube assembly during full rudder pedal
actuation. We are issuing this AD to detect and correct chafing of the
fuel return line assembly, which could result in fuel leaking under the
floor and fuel vapors entering the cabin. This condition could lead to
fire under the floor or in the cabin area.
DATES: This AD becomes effective on March 6, 2008.
On March 6, 2008, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
ADDRESSES: For service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006.
To view the AD docket, go to U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington,
[[Page 5738]]
DC 20590, or on the Internet at https://www.regulations.gov. The docket
number is FAA-2007-29138; Directorate Identifier 2007-CE-073- AD.
FOR FURTHER INFORMATION CONTACT: Jeff Janusz, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4148; fax: (316) 946-4107; e-mail: jeff.janusz@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 17, 2007, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Cessna Models 172R and 172S airplanes. This
proposal was published in the Federal Register as a notice of proposed
rulemaking (NPRM) on October 24, 2007 (72 FR 60291). The NPRM proposed
to require you to detect and correct chafing of the fuel return line
assembly.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Differences Between This AD and the Service Information
The service information permits tube damage up to a depth of 0.0035
inch. There is no known method to accurately measure the thickness
damage on a tube. We require replacement of the fuel return line
assembly if any damage is found.
If no chafing is found in the inspection of the fuel return line
assembly, the service information does not require inspection for
clearance around the fuel return line assembly. We require you to
inspect the clearance between the fuel return line assembly and both
the right steering tube assembly and airplane structure, for all
applicable aircraft.
The service information does not specify a minimum clearance
requirement between the fuel return line assembly and the right
steering tube assembly, only that the fuel return line assembly does
not touch either the right steering tube assembly or the airplane
structure. We require a minimum of 0.5 inch of clearance between the
fuel return line assembly and both the right steering tube assembly and
the airplane structure, during full rudder pedal actuation.
The requirements of this AD take precedence over the provisions in
the service information.
Costs of Compliance
We estimate that this AD affects 928 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80............................. N/A $80 $74,240
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. We have
no way of determining the number of airplanes that may need this
replacement:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
0.5 work-hour x $80 per hour = $40.... $123 $163
------------------------------------------------------------------------
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 AD.
Regulatory Findings
We have 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 the 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2007-29138; Directorate Identifier 2007-CE-073-AD'' in your
request.
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 Federal Aviation Administration
[[Page 5739]]
amends part 39 of the Federal Aviation Regulations (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. FAA amends Sec. 39.13 by adding the following new AD:
2008-03-02 Cessna Aircraft Company: Amendment 39-15351; Docket No.
FAA-2007-29138; Directorate Identifier 2007-CE-073-AD.
Effective Date
(a) This AD becomes effective on March 6, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Models Serial Nos.
------------------------------------------------------------------------
172R............................... 17281188 through 17281390.
172S............................... 172S9491 through 172S10489.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of chafed fuel return line
assemblies caused by the fuel return line assembly rubbing against
the right steering tube assembly during full rudder pedal actuation.
We are issuing this AD to detect and correct chafing of the fuel
return line assembly, which could result in fuel leaking under the
cabin floor and fuel vapors entering the cabin. This condition could
lead to fire under the floor or in the cabin area.
Compliance
(e) To address this problem, you must do the following, unless
already done:
Note: The requirements of this AD take precedence over the
actions required in the service information.
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Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the fuel return line Within the next Follow Cessna
assembly (Cessna part number (P/ 100 hours time-in- Service Bulletin
N) 0500118-49 or FAA-approved service (TIS) SB07-28-01, dated
equivalent P/N) for chafing. after March 6, June 18, 2007.
2008 (the
effective date of
this AD) or
within the next
12 months after
March 6, 2008
(the effective
date of this AD),
whichever occurs
first.
(2) If chafing is found in the Before further Follow Cessna
inspection required in flight after the Service Bulletin
paragraph (e)(1) of this AD, inspection SB07-28-01, dated
replace the fuel return line required in June 18, 2007.
assembly (Cessna P/N 0500118-49 paragraph (e)(1)
or FAA-approved equivalent P/N). of this AD where
evidence of
chafing was found.
(3) Inspect for a minimum Before further Follow paragraph 6
clearance of 0.5 inch between flight after: of the
the following parts throughout (A) The inspection Instructions
the entire range of copilot required in section of Cessna
rudder pedal travel and adjust paragraph (e)(1) Service Bulletin
the clearance as necessary: of this AD if no SB07-28-01, dated
chafing is found; June 18, 2007.
or. This AD requires
(B) The a minimum
replacement clearance of 0.5
required in inch.
paragraph (e)(2)
of this AD..
(i) The fuel return line
assembly (Cessna P/N
0500118-49 or FAA-approved
equivalent P/N) and the
steering tube assembly
(Cessna P/N MC0543022-2C);
and
(ii) The fuel return line
assembly (Cessna P/N
0500118-49 or FAA-approved
equivalent P/N) and the
airplane structure.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Jeff Janusz, Aerospace Engineer, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4148; fax: (316) 946-
4107; e-mail: jeff.janusz@faa.gov. 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.
Material Incorporated by Reference
(g) You must use Cessna Service Bulletin SB07-28-01, dated June
18, 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
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (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: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.>
Issued in Kansas City, Missouri, on January 22, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-1460 Filed 1-30-08; 8:45 am]
BILLING CODE 4910-13-P
