Airworthiness Directives; Cessna Aircraft Company Models 525, 525A, and 525B Airplanes, 6582-6584 [E8-1821]

Download as PDF 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:// www.archives.gov/federal-register/cfr/ibrlocations.html. 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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 Frm 00007 Fmt 4700 Sfmt 4700 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. E:\FR\FM\05FER1.SGM 05FER1 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 Frm 00008 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