Airworthiness Directives; Cirrus Design Corporation Models SR20 and SR22 Airplanes, 16027-16029 [06-2982]

Download as PDF Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations Unsafe Condition (d) This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from 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. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ cprice-sewell on PROD1PC66 with RULES Inspection and Corrective Action (f) Perform a detailed inspection for cracks or failure of the primary load path components of the engine forward mount by doing all the applicable actions in accordance with the procedures in Airbus AOT A320–71A1036, Revision 1, dated June 28, 2005. Perform the actions at the time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, as applicable. Do any corrective action before further flight in accordance with the procedures in the AOT. (1) For Model A321–131, –231, and –232 airplanes: Do the inspection within 5 days after the effective date of this AD. (2) For Model A319–131, –132, and –133 airplanes: Do the inspection within 10 days after the effective date of this AD. (3) For Model A320–232 and –233 airplanes: Do the inspection within 10 days after the effective date of this AD. (g) For all airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-torque each of the attachment bolts of the engine forward mount assembly in accordance with the procedures in Airbus AOT A320–71A1036, Revision 1, dated June 28, 2005. (1) If the inspection specified in paragraph (f) of this AD was accomplished after the effective date of this AD: Do the actions within 2,250 flight cycles after accomplishing the inspection. (2) If the inspection specified in paragraph (f) of this AD was accomplished before the effective date of this AD: Do the actions within 2,250 flight cycles after the effective date of this AD. No Reporting Required DEPARTMENT OF TRANSPORTATION (i) Although Airbus AOT A320–71A1036, Revision 1, dated June 28, 2005, recommends that inspection results be reported to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) French emergency airworthiness directive UF–2005–117, dated June 29, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus All Operators Telex A320–71A1036, Revision 1, dated June 28, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. (Only page 1 of the all operators telex contains the document number, revision number, and date of the document; no other page of the document contains this information.) The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 17, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2961 Filed 3–29–06; 8:45 am] BILLING CODE 4910–13–P Actions Accomplished Previously (h) Inspections, adjustments or repairs done before the effective date of this AD in accordance with the procedures in Airbus AOT A320–71A1036, dated June 27, 2005, are acceptable for compliance with the corresponding actions required by this AD. VerDate Aug<31>2005 15:18 Mar 29, 2006 Jkt 208001 PO 00000 Frm 00013 Fmt 4700 16027 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23023; Directorate Identifier 2005–CE–49–AD; Amendment 39– 14533; AD 2006–07–06] RIN 2120–AA64 Airworthiness Directives; Cirrus Design Corporation Models SR20 and SR22 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect the fuel line and wire bundles for any chafing damage; replace any damaged fuel line and repair any damaged wires or sheathing of the wire harness if any chafing damage is found; and install (to prevent any chafing damage to the fuel line and wire bundles) the forward loop clamp, fuel line shield, aft loop clamp, and anti-chafe tubing. This AD results from reports of fuel line leaks resulting from wire chafing on the fuel lines. We are issuing this AD to detect, correct, and prevent damage to the fuel line and wire bundles, which could result in fuel leaks. This failure could lead to unsafe fuel vapor within the cockpit and possible fire. DATES: This AD becomes effective on May 11, 2006. As of May 11, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727–2737, or on the Internet at http://www.cirrusdesign.com. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2005–23023; Directorate Identifier 2005–CE–49–AD. FOR FURTHER INFORMATION CONTACT: Wess Rouse, Aerospace Engineer, ACE– 117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294–8113; facsimile: (847) 294–7834. E:\FR\FM\30MRR1.SGM 30MRR1 16028 Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations SUPPLEMENTARY INFORMATION: Comments Discussion The FAA has received two reports of fuel line leaks within a compartment in the center console of Model SR22 airplanes. This compartment is drained to the belly of the aircraft. Investigation found that the leaks resulted from wire chafing on the fuel lines. This condition, if not corrected, could result in unsafe fuel vapor within the cockpit and possible fire. 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 Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 8, 2005 (70 FR 72945). The NPRM proposed to require you to inspect the fuel line and wire bundles for any chafing damage; replace any damaged fuel line and repair any damaged wires or sheathing of the wire harness if any chafing damage is found; and install the forward loop clamp, fuel line shield, aft loop clamp, and antichafe tubing. We provided the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and FAA’s response to the comment: —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. Changes to 14 CFR Part 39—Effect on the AD Comment Issue: Revision Date for Cirrus Design Corporation Service Bulletin The commenter notes that throughout the NPRM the date of Service Bulletin SB 2X–28–04 R1, Issued: November 1, 2005, Revised: November 8, 2005, should read, ‘‘Revised: November 14, 2005.’’ The FAA agrees with the commenter. We will change the final rule to include the correct revised date for the service bulletin. 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: How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA’s AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Costs of Compliance We estimate that this AD affects 2,135 airplanes in the U.S. registry. We estimate the following costs to do the inspection of the fuel line and wire harness for any chafing damage: Total cost per airplane Labor cost Parts cost 1 work hour × $80 = $80 ............................................................. Not Applicable .......................... We estimate the following costs to do necessary replacements of any damaged fuel line or repair any damaged wires or sheathing of the wire harness that would be required based on the results of this inspection. We have no way of $80 Total cost on U.S. operators 2,135 × $80 = $170,800 determining the number of airplanes that may need these repairs or replacements: Labor cost Parts cost 6 work hours × $80 = $480 ..................................................................................................................................... We estimate the following costs to do the installation of the forward loop Parts cost 1 work hour × $80 = $80 ........................................................................................ cprice-sewell on PROD1PC66 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 VerDate Aug<31>2005 15:18 Mar 29, 2006 Jkt 208001 $547 clamp, fuel line shield, aft loop clamp, and anti-chafe tubing: Labor cost Warranty credit for parts and labor costs is referenced in the service bulletin. $67 Total cost per airplane $146 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 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Total cost per airplane $226 Total cost on U.S. operators 2,135 × $246 = $482,510 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, E:\FR\FM\30MRR1.SGM 30MRR1 Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations 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–2005–23023; Directorate Identifier 2005–CE–49–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 Effective Date (a) This AD becomes effective on May 11, 2006. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: I 2006–07–06 Cirrus Design Corporation: Amendment 39–14533; Docket No. FAA–2005–23023; Directorate Identifier 2005–CE–49–AD. Model Serial Nos. SR20 .............. SR22 .............. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 16029 1005 through 1581. 0002 through 1643 and 1645 through 1662. Unsafe Condition (d) This AD is the result of reports of fuel line leaks resulting from wire chafing on the fuel lines. The actions specified in this AD are intended to detect, correct, and prevent damage to the fuel line and wire bundles, which could result in fuel leaks. This failure could lead to unsafe fuel vapor within the cockpit and possible fire. Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the fuel line and wire harness for any chafing damage. Within the next 50 hours time-in-service (TIS) after May 11, 2006 (the effective date of this AD). Before further flight after the inspection required by paragraph (e)(1) of this AD. Follow Cirrus Design Corporation Service Bulletin SB 2X–28–04 R1, Issued: November 1, 2005, Revised: November 14, 2005. Follow Cirrus Design Corporation Service Bulletin SB 2X–28–04 R1, Issued: November 1, 2005, Revised: November 14, 2005. Within the next 50 hours time-in-service (TIS) after May 11, 2006 (the effective date of this AD). Follow Cirrus Design Corporation Service Bulletin SB 2X–28–04 R1, Issued: November 1, 2005, Revised: November 14, 2005. (2) If any chafing damage is found as a result of the inspection required by paragraph (e)(1) of this AD: (i) Replace any damaged fuel line; and (ii) Repair any damaged wires or sheathing of the wire harness (3) Install the following: (i) Forward loop clamp; (ii) Fuel line shield; (iii) Aft loop clamp; and (iv) Anti-chafe tubing Alternative Methods of Compliance (AMOCs) (f) The Manager, Chicago Aircraft Certification Office (ACO), FAA, ATTN: Wess Rouse, Aerospace Engineer, ACE–117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294–8113; fax: (847) 294–7834, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. cprice-sewell on PROD1PC66 with RULES Material Incorporated by Reference (g) You must do the actions required by this AD following the instructions in Cirrus Design Corporation Service Bulletin SB 2X– 28–04 R1, Issued: November 1, 2005, Revised: November 14, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, VerDate Aug<31>2005 15:18 Mar 29, 2006 Jkt 208001 Minnesota 55811; telephone: (218) 727–2737 or on the Internet at http:// www.cirrusdesign.com. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– 2005–23023; Directorate Identifier 2005–CE– 49–AD. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Issued in Kansas City, Missouri, on March 20, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2982 Filed 3–29–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\30MRR1.SGM 30MRR1

Agencies

[Federal Register Volume 71, Number 61 (Thursday, March 30, 2006)]
[Rules and Regulations]
[Pages 16027-16029]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2982]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23023; Directorate Identifier 2005-CE-49-AD; 
Amendment 39-14533; AD 2006-07-06]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Models SR20 
and SR22 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD 
requires you to inspect the fuel line and wire bundles for any chafing 
damage; replace any damaged fuel line and repair any damaged wires or 
sheathing of the wire harness if any chafing damage is found; and 
install (to prevent any chafing damage to the fuel line and wire 
bundles) the forward loop clamp, fuel line shield, aft loop clamp, and 
anti-chafe tubing. This AD results from reports of fuel line leaks 
resulting from wire chafing on the fuel lines. We are issuing this AD 
to detect, correct, and prevent damage to the fuel line and wire 
bundles, which could result in fuel leaks. This failure could lead to 
unsafe fuel vapor within the cockpit and possible fire.

DATES: This AD becomes effective on May 11, 2006.
    As of May 11, 2006, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, 
Minnesota 55811; telephone: (218) 727-2737, or on the Internet at 
http://www.cirrusdesign.com.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://
dms.dot.gov. The docket number is FAA-2005-23023; Directorate 
Identifier 2005-CE-49-AD.

FOR FURTHER INFORMATION CONTACT: Wess Rouse, Aerospace Engineer, ACE-
117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, 
Room 107, Des Plaines, Illinois 60018; telephone: (847) 294-8113; 
facsimile: (847) 294-7834.

[[Page 16028]]


SUPPLEMENTARY INFORMATION:

Discussion

    The FAA has received two reports of fuel line leaks within a 
compartment in the center console of Model SR22 airplanes. This 
compartment is drained to the belly of the aircraft. Investigation 
found that the leaks resulted from wire chafing on the fuel lines.
    This condition, if not corrected, could result in unsafe fuel vapor 
within the cockpit and possible fire.
    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 Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on December 8, 2005 (70 FR 72945). The NPRM 
proposed to require you to inspect the fuel line and wire bundles for 
any chafing damage; replace any damaged fuel line and repair any 
damaged wires or sheathing of the wire harness if any chafing damage is 
found; and install the forward loop clamp, fuel line shield, aft loop 
clamp, and anti-chafe tubing.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comment received on the proposal 
and FAA's response to the comment:

Comment Issue: Revision Date for Cirrus Design Corporation Service 
Bulletin

    The commenter notes that throughout the NPRM the date of Service 
Bulletin SB 2X-28-04 R1, Issued: November 1, 2005, Revised: November 8, 
2005, should read, ``Revised: November 14, 2005.''
    The FAA agrees with the commenter. We will change the final rule to 
include the correct revised date for the service bulletin.

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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    We estimate that this AD affects 2,135 airplanes in the U.S. 
registry.
    We estimate the following costs to do the inspection of the fuel 
line and wire harness for any chafing damage:

----------------------------------------------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                   Parts cost          airplane          Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $80 = $80...........  Not Applicable......             $80  2,135 x $80 = $170,800
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do necessary replacements of any 
damaged fuel line or repair any damaged wires or sheathing of the wire 
harness that would be required based on the results of this inspection. 
We have no way of determining the number of airplanes that may need 
these repairs or replacements:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
6 work hours x $80 = $480...............             $67            $547
------------------------------------------------------------------------

    We estimate the following costs to do the installation of the 
forward loop clamp, fuel line shield, aft loop clamp, and anti-chafe 
tubing:

----------------------------------------------------------------------------------------------------------------
                                                       Total cost per
              Labor cost                 Parts cost       airplane            Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $80 = $80..............            $146            $226   2,135 x $246 = $482,510
----------------------------------------------------------------------------------------------------------------

    Warranty credit for parts and labor costs is referenced in the 
service bulletin.

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,

[[Page 16029]]

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-2005-23023; Directorate Identifier 2005-CE-49-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 a new AD to read as follows:

2006-07-06 Cirrus Design Corporation: Amendment 39-14533; Docket No. 
FAA-2005-23023; Directorate Identifier 2005-CE-49-AD.

Effective Date

    (a) This AD becomes effective on May 11, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
SR20......................................  1005 through 1581.
SR22......................................  0002 through 1643 and 1645
                                             through 1662.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is the result of reports of fuel line leaks 
resulting from wire chafing on the fuel lines. The actions specified 
in this AD are intended to detect, correct, and prevent damage to 
the fuel line and wire bundles, which could result in fuel leaks. 
This failure could lead to unsafe fuel vapor within the cockpit and 
possible fire.

Compliance

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the fuel line     Within the next 50    Follow Cirrus Design
 and wire harness for any      hours time-in-        Corporation Service
 chafing damage.               service (TIS) after   Bulletin SB 2X-28-
                               May 11, 2006 (the     04 R1, Issued:
                               effective date of     November 1, 2005,
                               this AD).             Revised: November
                                                     14, 2005.
(2) If any chafing damage is  Before further        Follow Cirrus Design
 found as a result of the      flight after the      Corporation Service
 inspection required by        inspection required   Bulletin SB 2X-28-
 paragraph (e)(1) of this      by paragraph (e)(1)   04 R1, Issued:
 AD:                           of this AD.           November 1, 2005,
(i) Replace any damaged fuel                         Revised: November
 line; and                                           14, 2005.
(ii) Repair any damaged
 wires or sheathing of the
 wire harness
(3) Install the following:    Within the next 50    Follow Cirrus Design
(i) Forward loop clamp;        hours time-in-        Corporation Service
(ii) Fuel line shield;         service (TIS) after   Bulletin SB 2X-28-
(iii) Aft loop clamp; and      May 11, 2006 (the     04 R1, Issued:
(iv) Anti-chafe tubing         effective date of     November 1, 2005,
                               this AD).             Revised: November
                                                     14, 2005.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Chicago Aircraft Certification Office (ACO), 
FAA, ATTN: Wess Rouse, Aerospace Engineer, ACE-117C, Chicago 
Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des 
Plaines, Illinois 60018; telephone: (847) 294-8113; fax: (847) 294-
7834, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (g) You must do the actions required by this AD following the 
instructions in Cirrus Design Corporation Service Bulletin SB 2X-28-
04 R1, Issued: November 1, 2005, Revised: November 14, 2005. The 
Director of the Federal Register approved the incorporation by 
reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. To get a copy of this service information, 
contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, 
Minnesota 55811; telephone: (218) 727-2737 or on the Internet at 
http://www.cirrusdesign.com. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To 
view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2005-23023; 
Directorate Identifier 2005-CE-49-AD.

    Issued in Kansas City, Missouri, on March 20, 2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 06-2982 Filed 3-29-06; 8:45 am]
BILLING CODE 4910-13-P