Airworthiness Directives; Cessna Aircraft Company Models 525, 525A, and 525B Airplanes, 6582-6584 [E8-1821]
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6582
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
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://
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Issued in Renton, Washington, on January
24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–1813 Filed 2–4–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28956; Directorate
Identifier 2007–CE–068–AD; Amendment
39–15360; AD 2008–03–10]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Models 525, 525A,
and 525B Airplanes
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 525, 525A, and 525B airplanes.
This AD requires you to inspect the
lower wing skin structure, forward wing
spar, lower fuselage skin, fairings, and
the external fairing frames for corrosion;
repair any damage found; apply a
corrosion inhibitive sealant to the
fuselage fairings before reinstalling; and
disable the cockpit mounted pilot relief
tube. This AD results from leaking of the
cockpit mounted pilot relief tube, which
caused corrosion of the airplane
structure. We are issuing this AD to
detect and correct any damage from
corrosion of the airplane structure.
Corrosion of the airplane structure
could cause structural degradation and
lead to structural failure of the airplane
with consequent loss of control.
DATES: This AD becomes effective on
March 11, 2008.
On March 11, 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, Citation Marketing
Division, P.O. Box 7706, Wichita,
Kansas 67277; telephone: 1–800–835–
4090; fax: 1–800–517–8500.
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,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2007–28956;
Directorate Identifier 2007–CE–068–AD.
FOR FURTHER INFORMATION CONTACT: T.N.
Baktha, Aerospace Engineer,1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4155; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
include an AD that would apply to
certain Cessna Models 525, 525A, and
525B airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on October 26, 2007 (72 FR 60790). The
NPRM proposed to require you to
inspect the lower wing skin structure,
forward wing spar, lower fuselage skin,
fairings, and the external fairing frames
for corrosion; repair any damage found;
apply a corrosion inhibitive sealant to
the fuselage fairings before reinstalling;
and disable the cockpit mounted pilot
relief tube.
Discussion
On October 22, 2007, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
We estimate that this AD affects 261
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
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.
Costs of Compliance
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
80 work-hours × $80 per hour = $6,400 ...................................................
Not applicable ..................................
$6,400
$1,670,400
We have no way of determining the
number of airplanes that may need
repair or further inspection based on the
results of the inspection, or the costs
associated with such repair or
inspection.
We estimate the following costs to
disable the cockpit mounted pilot relief
tube:
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
.5 work-hour × $80 per hour = $40 ...........................................................
rmajette on PROD1PC64 with RULES
Labor cost
Not applicable ..................................
$40
$10,440
Cessna will provide warranty credit to
the extent specified in Cessna Citation
Service Bulletin SB525–53–20, dated
April 30, 2007; Cessna Citation Service
Bulletin SB525A–53–01, dated April 30,
2007; Cessna Citation Service Bulletin
SB525B–53–01, dated April 30, 2007;
Cessna Citation Alert Service Letter
VerDate Aug<31>2005
15:28 Feb 04, 2008
Jkt 214001
ASL525–53–04, Revision 2, dated
August 19, 2007; Cessna Citation Alert
Service Letter ASL525A–53–05,
Revision 2, dated July 25, 2007; and
Cessna Citation Alert Service Letter
ASL525B–53–02, Revision 2, dated July
25, 2007.
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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
E:\FR\FM\05FER1.SGM
05FER1
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
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–2007–28956;
Directorate Identifier 2007-CE–068-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
amends part 39 of the Federal Aviation
Regulations (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]
6583
2008–03–10 Cessna Aircraft Company:
Amendment 39–15360; Docket No.
FAA–2007–28956; Directorate Identifier
2007-CE–068-AD.
Effective Date
(a) This AD becomes effective on March 11,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplane models and serial numbers that have
a cockpit mounted pilot relief tube installed
and are certificated in any category:
Models
Serial No.
(1) 525 ..........................
(2) 525A .......................
(3) 525B .......................
0001 through 0637.
0001 through 0347.
0001 through 0152.
Unsafe Condition
(d) This AD results from leaking of the
pilot relief tube, which caused corrosion of
the airplane structure. We are issuing this AD
to detect and correct any damage from
corrosion on the airplane structure. Corrosion
of the airplane structure could cause
structural degradation and lead to structural
failure of the airplane with consequent loss
of control.
Compliance
2. FAA amends § 39.13 by adding the
following new AD:
I
(e) To address this problem, you must do
the following, unless already done:
TABLE 1.—ACTIONS, COMPLIANCE, AND PROCEDURES
Compliance
Procedures
(1) Inspect the lower wing skin structure, forward wing spars, lower fuselage skin, fairings, and external fairing frames for corrosion.
Within the next 90 days after March 11, 2008
(the effective date of this AD).
(2) If corrosion damage is found in the lower
wing skin structure, forward wing spars,
lower fuselage skin, fairings, or external fairing frames during the inspection required in
paragraph (e)(1) of this AD, repair as specified in the applicable service information. If
the corrosion damage cannot be repaired
within the limits specified in the applicable
service information, contact the manufacturer
at 1–800–835–4090 for an FAA-approved repair scheme and incorporate this repair.
(3) If corrosion on the lower wing skin structure, forward wing spars, and lower fuselage
skin was repaired by blending within the limits specified in the service information, do a
surface eddy current inspection or a dyepenetrant inspection for cracks.
rmajette on PROD1PC64 with RULES
Actions
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Cessna Citation Alert Service Letter
ASL525–53–04, Revision 2, dated August
19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July
25, 2007; or Cessna Citation Alert Service
Letter ASL525B–53–02, Revision 2, dated
July 25, 2007.
Follow Cessna Citation Alert Service Letter
ASL525–53–04, Revision 2, dated August
19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July
25, 2007; or Cessna Citation Alert Service
Letter ASL525B–53–02, Revision 2, dated
July 25, 2007.
(4) If cracks are found during the surface eddy
current inspection or the dye-penetrant inspection required in paragraph (e)(3) of this
AD, contact the manufacturer for an FAA-approved repair scheme and incorporate this
repair.
VerDate Aug<31>2005
15:28 Feb 04, 2008
Jkt 214001
Before further flight after the repair by blending was done as specified in paragraph
(e)(2) of this AD.
Before further flight after the inspection required in paragraph (e)(3) of this AD.
PO 00000
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Follow Cessna Citation Alert Service Letter
ASL525–53–04, Revision 2, dated August
19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July
25, 2007; or Cessna Citation Alert Service
Letter ASL525B–53–02, Revision 2, dated
July 25, 2007.
Contact Cessna Aircraft Company, Citation
Customer Support at 1–800–835–4090.
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6584
Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations
TABLE 1.—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued
Actions
Compliance
Procedures
(5) Install the fuselage fairings and apply corrosion inhibitive sealant.
Before further flight after the inspection required in paragraph (e)(1) of this AD if no
corrosion was found; or before further flight
after doing the repairs and inspections required in paragraphs (e)(2), (e)(3), and
(e)(4) of this AD if corrosion or cracks were
found.
Before further flight after the inspection required in paragraph (e)(1) of this AD.
Follow Cessna Citation Alert Service Letter
ASL525–53–04, Revision 2, dated August
19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July
25, 2007; or Cessna Citation Alert Service
Letter ASL525B–53–02, Revision 2, dated
July 25, 2007.
Cessna Citation Service Bulletin SB525–53–
20, dated April 30, 2007; Cessna Citation
Service Bulletin SB525A–53–01, dated April
30, 2007; or Cessna Citation Service Bulletin SB525B–53–01, dated April 30, 2007.
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
Citation Marketing Division, P.O. 7706,
Wichita, Kansas 67277; telephone: 1–800–
835–4090; fax: 1–800–517–8500.
(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.
(6) Determine the type of installation of the
cockpit mounted pilot relief tube and disable
the relief tube.
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: T.N.
Baktha, Wichita ACO, Aerospace Engineer,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–4155;
fax: (316) 946–4107. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Material Incorporated by Reference
(g) You must use the service information
specified in Table 2 of this AD 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,
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin No.
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Citation
Citation
Citation
Citation
Citation
Citation
Alert Service Letter ASL525–53–04 .....................................................................................
Alert Service Letter ASL525A–53–05 ...................................................................................
Alert Service Letter ASL525B–53–02 ...................................................................................
Service Bulletin SB525A–53–20 ...........................................................................................
Service Bulletin SB525A–53–01 ...........................................................................................
Service Bulletin SB525B–53–01 ...........................................................................................
Issued in Kansas City, Missouri, on January
24, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–1821 Filed 2–4–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0100; Directorate
Identifier 2007–SW–41–AD; Amendment 39–
15356; AD 2008–03–07]
rmajette on PROD1PC64 with RULES
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Model AS 332 L2 Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
Revision
15:28 Feb 04, 2008
Jkt 214001
Final rule; request for
comments.
ACTION:
SUMMARY: We are adopting a new
airworthiness directive (AD) for
Eurocopter Model AS 332 L2
helicopters. This AD results from
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority to identify and
correct an unsafe condition on an
aviation product. The European
Aviation Safety Agency (EASA), the
Technical Agent of France, with which
we have a bilateral agreement, states in
the MCAI:
A borescope inspection during scheduled
maintenance revealed wear on the internal
skin of a Life Raft Inflation Cylinder, P/N
41918001, that had been installed on a
Eurocopter AS 332 L2 helicopter. The
plunger tube end is fitted with a metal endfitting that presses against the internal
surface of the cylinder due to its installation
horizontally aboard the aircraft. Vibrations
generated by helicopter operation are
therefore causing such wear, which may
PO 00000
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Fmt 4700
Sfmt 4700
2
2
2
....................
....................
....................
Date
August 19, 2007.
July 25, 2007.
July 25, 2007.
April 30, 2007
April 30, 2007.
April 30, 2007.
result in a drop of internal pressure of the
cylinder. This internal damage, if not
corrected, could lead to functional failure of
the cylinder, making the life raft inflation no
longer possible.
This AD requires actions that are
intended to address the failure of a life
raft to inflate during an emergency
landing on water (ditching), which
could result in loss of the crew and
passengers.
This AD becomes effective on
February 20, 2008.
The Director of the Federal Register
approved the incorporation by reference
of Eurocopter Alert Service Bulletin No.
05.00.71, dated July 31, 2007, as of
February 20, 2008.
We must receive comments on this
AD by April 7, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
DATES:
E:\FR\FM\05FER1.SGM
05FER1
]]>Agencies
[Federal Register Volume 73, Number 24 (Tuesday, February 5, 2008)]
[Rules and Regulations]
[Pages 6582-6584]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-1821]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28956; Directorate Identifier 2007-CE-068-AD;
Amendment 39-15360; AD 2008-03-10]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 525,
525A, and 525B 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 525, 525A, and 525B airplanes.
This AD requires you to inspect the lower wing skin structure, forward
wing spar, lower fuselage skin, fairings, and the external fairing
frames for corrosion; repair any damage found; apply a corrosion
inhibitive sealant to the fuselage fairings before reinstalling; and
disable the cockpit mounted pilot relief tube. This AD results from
leaking of the cockpit mounted pilot relief tube, which caused
corrosion of the airplane structure. We are issuing this AD to detect
and correct any damage from corrosion of the airplane structure.
Corrosion of the airplane structure could cause structural degradation
and lead to structural failure of the airplane with consequent loss of
control.
DATES: This AD becomes effective on March 11, 2008.
On March 11, 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, Citation Marketing Division, P.O. Box 7706,
Wichita, Kansas 67277; telephone: 1-800-835-4090; fax: 1-800-517-8500.
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, DC 20590, or on the Internet at
https://www.regulations.gov. The docket number is FAA-2007-28956;
Directorate Identifier 2007-CE-068-AD.
FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer,1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4155; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
On October 22, 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 525, 525A, and 525B airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on October 26, 2007 (72 FR 60790). The NPRM
proposed to require you to inspect the lower wing skin structure,
forward wing spar, lower fuselage skin, fairings, and the external
fairing frames for corrosion; repair any damage found; apply a
corrosion inhibitive sealant to the fuselage fairings before
reinstalling; and disable the cockpit mounted pilot relief tube.
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.
Costs of Compliance
We estimate that this AD affects 261 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
----------------------------------------------------------------------------------------------------------------
80 work-hours x $80 per hour = $6,400....... Not applicable................. $6,400 $1,670,400
----------------------------------------------------------------------------------------------------------------
We have no way of determining the number of airplanes that may need
repair or further inspection based on the results of the inspection, or
the costs associated with such repair or inspection.
We estimate the following costs to disable the cockpit mounted
pilot relief tube:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
.5 work-hour x $80 per hour = $40........... Not applicable................. $40 $10,440
----------------------------------------------------------------------------------------------------------------
Cessna will provide warranty credit to the extent specified in
Cessna Citation Service Bulletin SB525-53-20, dated April 30, 2007;
Cessna Citation Service Bulletin SB525A-53-01, dated April 30, 2007;
Cessna Citation Service Bulletin SB525B-53-01, dated April 30, 2007;
Cessna Citation Alert Service Letter ASL525-53-04, Revision 2, dated
August 19, 2007; Cessna Citation Alert Service Letter ASL525A-53-05,
Revision 2, dated July 25, 2007; and Cessna Citation Alert Service
Letter ASL525B-53-02, Revision 2, dated July 25, 2007.
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
[[Page 6583]]
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-2007-28956; Directorate Identifier 2007-CE-068-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 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:
2008-03-10 Cessna Aircraft Company: Amendment 39-15360; Docket No.
FAA-2007-28956; Directorate Identifier 2007-CE-068-AD.
Effective Date
(a) This AD becomes effective on March 11, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that have a cockpit mounted pilot relief tube installed and
are certificated in any category:
------------------------------------------------------------------------
Models Serial No.
------------------------------------------------------------------------
(1) 525............................. 0001 through 0637.
(2) 525A............................ 0001 through 0347.
(3) 525B............................. 0001 through 0152.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from leaking of the pilot relief tube, which
caused corrosion of the airplane structure. We are issuing this AD
to detect and correct any damage from corrosion on the airplane
structure. Corrosion of the airplane structure could cause
structural degradation and lead to structural failure of the
airplane with consequent loss of control.
Compliance
(e) To address this problem, you must do the following, unless
already done:
Table 1.--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the lower wing skin Within the next 90 Follow Cessna
structure, forward wing spars, days after March Citation Alert
lower fuselage skin, fairings, 11, 2008 (the Service Letter
and external fairing frames for effective date of ASL525-53-04,
corrosion. this AD). Revision 2, dated
August 19, 2007;
Cessna Citation
Alert Service
Letter ASL525A-53-
05, Revision 2,
dated July 25,
2007; or Cessna
Citation Alert
Service Letter
ASL525B-53-02,
Revision 2, dated
July 25, 2007.
(2) If corrosion damage is Before further Follow Cessna
found in the lower wing skin flight after the Citation Alert
structure, forward wing spars, inspection Service Letter
lower fuselage skin, fairings, required in ASL525-53-04,
or external fairing frames paragraph (e)(1) Revision 2, dated
during the inspection required of this AD. August 19, 2007;
in paragraph (e)(1) of this AD, Cessna Citation
repair as specified in the Alert Service
applicable service information. Letter ASL525A-53-
If the corrosion damage cannot 05, Revision 2,
be repaired within the limits dated July 25,
specified in the applicable 2007; or Cessna
service information, contact Citation Alert
the manufacturer at 1-800-835- Service Letter
4090 for an FAA-approved repair ASL525B-53-02,
scheme and incorporate this Revision 2, dated
repair. July 25, 2007.
(3) If corrosion on the lower Before further Follow Cessna
wing skin structure, forward flight after the Citation Alert
wing spars, and lower fuselage repair by Service Letter
skin was repaired by blending blending was done ASL525-53-04,
within the limits specified in as specified in Revision 2, dated
the service information, do a paragraph (e)(2) August 19, 2007;
surface eddy current inspection of this AD. Cessna Citation
or a dye-penetrant inspection Alert Service
for cracks. Letter ASL525A-53-
05, Revision 2,
dated July 25,
2007; or Cessna
Citation Alert
Service Letter
ASL525B-53-02,
Revision 2, dated
July 25, 2007.
(4) If cracks are found during Before further Contact Cessna
the surface eddy current flight after the Aircraft Company,
inspection or the dye-penetrant inspection Citation Customer
inspection required in required in Support at 1-800-
paragraph (e)(3) of this AD, paragraph (e)(3) 835-4090.
contact the manufacturer for an of this AD.
FAA-approved repair scheme and
incorporate this repair.
[[Page 6584]]
(5) Install the fuselage Before further Follow Cessna
fairings and apply corrosion flight after the Citation Alert
inhibitive sealant. inspection Service Letter
required in ASL525-53-04,
paragraph (e)(1) Revision 2, dated
of this AD if no August 19, 2007;
corrosion was Cessna Citation
found; or before Alert Service
further flight Letter ASL525A-53-
after doing the 05, Revision 2,
repairs and dated July 25,
inspections 2007; or Cessna
required in Citation Alert
paragraphs Service Letter
(e)(2), (e)(3), ASL525B-53-02,
and (e)(4) of Revision 2, dated
this AD if July 25, 2007.
corrosion or
cracks were found.
(6) Determine the type of Before further Cessna Citation
installation of the cockpit flight after the Service Bulletin
mounted pilot relief tube and inspection SB525-53-20,
disable the relief tube. required in dated April 30,
paragraph (e)(1) 2007; Cessna
of this AD. Citation Service
Bulletin SB525A-
53-01, dated
April 30, 2007;
or Cessna
Citation Service
Bulletin SB525B-
53-01, dated
April 30, 2007.
------------------------------------------------------------------------
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: T.N. Baktha, Wichita ACO, Aerospace Engineer, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4155;
fax: (316) 946-4107. 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 the service information specified in Table 2 of
this AD 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, Citation Marketing Division, P.O. 7706,
Wichita, Kansas 67277; telephone: 1-800-835-4090; fax: 1-800-517-
8500.
(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.
Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin No. Revision Date
------------------------------------------------------------------------
Cessna Citation Alert Service 2 August 19, 2007.
Letter ASL525-53-04.
Cessna Citation Alert Service 2 July 25, 2007.
Letter ASL525A-53-05.
Cessna Citation Alert Service 2 July 25, 2007.
Letter ASL525B-53-02.
Cessna Citation Service ........... April 30, 2007
Bulletin SB525A-53-20.
Cessna Citation Service ........... April 30, 2007.
Bulletin SB525A-53-01.
Cessna Citation Service ........... April 30, 2007.
Bulletin SB525B-53-01.
------------------------------------------------------------------------
Issued in Kansas City, Missouri, on January 24, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-1821 Filed 2-4-08; 8:45 am]
BILLING CODE 4910-13-P
