Airworthiness Directives; Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F Airplanes, 69069-69071 [05-22220]

Download as PDF Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations Related Information (j) French airworthiness directive F–2004– 038, dated March 17, 2004, also addresses the subject of this AD. in Table 1 of this AD, no further work is required by this paragraph. TABLE 1.—AFFECTED ACT P/NS Material Incorporated by Reference (k) You must use Airbus Service Bulletin A320–28–1105, Revision 02, dated March 11, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. 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 https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. D2827091100000 D2827091100200 D2827091100600 D2827091300000 D2827091300200 D2827091300400 D2827105100000 D2827105100200 D2827105100400 D2827105200000 D2827105200200 D2827105200400 D2827105300000 D2827105300200 D2827105300400 D2827105400000 D2827105400200 D2827105400400 D2827105400600 D2827105400800 D2827105500000 D2827105500200 D2827105500400 D2827105600000 D2827105600200 D2827105600400 D2827107500000 D2827107500200 Manhole Cover/Seal Replacement (g) Within 30 days (for Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes) or 12 months (for Model A320– 111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, and –131 airplanes) after the effective date of this AD: For each ACT P/N listed in Table 1 of this AD: Before further flight, replace the outer ACT manhole cover with a reinforced manhole cover and replace the outer manhole cover seal with a new seal, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 28–1105, Revision 02, dated March 11, 2005. Replacements are also acceptable if done before the effective date of this AD in accordance with Airbus Service Bulletin A320–28–1105, Revision 01, dated March 18, 2003; and Airbus Service Bulletin A320–28– 1105, dated October 22, 2002. Parts Installation (h) As of the effective date of this AD, no person may install an ACT having any P/N listed in Table 1 of this AD, unless the actions required by paragraph (g) of this AD have been done for that ACT. Alternative Methods of Compliance (AMOCs) (i)(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. VerDate Aug<31>2005 15:39 Nov 10, 2005 Jkt 208001 Issued in Renton, Washington on October 26, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–22219 Filed 11–10–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22169; Directorate Identifier 2005–NM–094–AD; Amendment 39–14361; AD 2005–23–03] 69069 spherical accumulator) and fatigue cracks found on four thrust reverser accumulators. We are issuing this AD to prevent failure of the spherical accumulator for the main hydraulic system, due to fatigue cracking on the threads, which could result in the loss of hydraulic power, damage to the surrounding airplane structure, and loss of airplane control. The failure of the accumulator could also result in injury to any persons in the surrounding area. The loss of hydraulic fluid could also leak onto a potential source of ignition and result in a consequent fire. DATES: This AD becomes effective December 19, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 19, 2005. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209–2942, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Robert Busto, Aerospace Engineer, Systems and Propulsion Branch, ACE– 116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4157; fax (316) 946–4107. SUPPLEMENTARY INFORMATION: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B–A, 24C, 24D, 24D–A, 24E, 24F, 24F–A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires replacement of the spherical accumulator for the main hydraulic system with a new cylindrical accumulator. For certain airplanes, this AD also requires modification of the accumulator pressure gauge. This AD results from reports of the failure of two thrust reverser accumulators (which are similar to the main hydraulic system’s Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Learjet Model 23, 24, 24A, 24B, 24B–A, 24C, 24D, 24D–A, 24E, 24F, 24F–A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. That NPRM was published in the Federal Register on August 23, 2005 (70 FR 49210). That NPRM proposed to require replacement of the spherical accumulator for the main hydraulic system with a new cylindrical accumulator. For certain RIN 2120–AA64 Airworthiness Directives; Learjet Model 23, 24, 24A, 24B, 24B–A, 24C, 24D, 24D–A, 24E, 24F, 24F–A, 25, 25A, 25B, 25C, 25D, and 25F Airplanes AGENCY: PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 E:\FR\FM\14NOR1.SGM 14NOR1 69070 Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations airplanes, that proposed AD would also require modification of the accumulator pressure gauge. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Conclusion We have carefully reviewed the available data, and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 434 airplanes of the affected design in the worldwide fleet. This AD will affect about 242 airplanes of U.S. registry. The actions will take about 9 to 13 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will cost about $1,336 to $1,363 per airplane. Based on these figures, the estimated cost of the AD for U.S. operators is $464,882 to $534,336, or $1,921 to $2,208 per airplane. Authority for This Rulemaking 15:39 Nov 10, 2005 Jkt 208001 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. VerDate Aug<31>2005 Regulatory Findings § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–23–03 Learjet: Amendment 39–14361. Docket No. FAA–2005–22169; Directorate Identifier 2005–NM–094–AD. Effective Date (a) This AD becomes effective December 19, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Learjet Model 23, 24, 24A, 24B, 24B–A, 24C, 24D, 24D–A, 24E, 24F, 24F–A, 25, 25A, 25B, 25C, 25D, and 25F airplanes, certificated in any category; having serial numbers 23–003 through 23–099 inclusive, 24–100 through 24–284 inclusive, and 25–003 through 25–153 inclusive. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Unsafe Condition (d) This AD results from reports of the failure of two thrust reverser accumulators (which are similar to the main hydraulic system’s accumulator) and fatigue cracks found on four thrust reverser accumulators. We are issuing this AD to prevent failure of the spherical accumulator for the main hydraulic system, due to fatigue cracking on the threads, which could result in the loss of hydraulic power, damage to the surrounding airplane structure, and loss of airplane control. The failure of the accumulator could also result in injury to any persons in the surrounding area. The loss of hydraulic fluid could also leak onto a potential source of ignition and result in a consequent fire. 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. Replacement (f) Within 60 days after the effective date of this AD, replace the spherical accumulator having part number (P/N) 2380025–() or P/N 2380167–() with a new cylindrical accumulator having P/N 2497202–801, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A23/24/25–29–4, Revision 1, dated January 17, 2005. Concurrent Action (g) For airplanes having serial numbers 23– 003 through 23–014 inclusive: Prior to or concurrently with the actions in Bombardier Alert Service Bulletin A23/24/25–29–4, Revision 1, dated January 17, 2005, relocate the accumulator pressure gauge in accordance with Learjet Service Kit SK23– 215, dated April 4, 1966. Parts Installation (h) As of the effective date, no spherical accumulator having P/N 2380025–() or P/N 2380167–() may be installed on any airplane. Previous Actions (i) Replacements done before the effective date of this AD in accordance with Bombardier Alert Service Bulletin A23/24/ 25–29–4, dated August 20, 2004, are acceptable for compliance with the requirements of paragraph (f) of this AD. No Reporting Required (j) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Wichita Aircraft Certification Office, 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. E:\FR\FM\14NOR1.SGM 14NOR1 Federal Register / Vol. 70, No. 218 / Monday, November 14, 2005 / Rules and Regulations Material Incorporated by Reference (l) You must use Bombardier Alert Service Bulletin A23/24/25–29–4, Revision 1, dated January 17, 2005; and Learjet Service Kit SK23–215, dated April 4, 1966; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (The issue date of Learjet Service Kit SK23– 215 is located only on the first and last pages of the document.) 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 Learjet, Inc., One Learjet Way, Wichita, Kansas 67209–2942, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 26, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–22220 Filed 11–10–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22147; Directorate Identifier 2005–NM–114–AD; Amendment 39–14371; AD 2005–23–13] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB–135 airplanes, and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This AD requires modification of the logic of the steering system of the nose landing gear (NLG) wheel. This AD results from reports of the loss of directional control of the airplane on the ground after an internal failure of the NLG wheel steering system. We are issuing this AD to 15:39 Nov 10, 2005 Jkt 208001 Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 Airplanes, and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes VerDate Aug<31>2005 prevent failure of the NLG wheel steering system, which could result in reduced controllability of the airplane. DATES: This AD becomes effective December 19, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 19, 2005. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain EMBRAER Model EMB–135 airplanes, and Model EMB– 145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. That NPRM was published in the Federal Register on August 22, 2005 (70 FR 48906). That NPRM proposed to require modification of the logic of the steering system of the nose landing gear (NLG) wheel. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Reference Latest Revision of EMBRAER Service Bulletins Two commenters request that the NPRM reference EMBRAER Service PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 69071 Bulletin 145–32–0104, Revision 03, dated June 21, 2005 (EMBRAER Service Bulletin 145–32–0104, dated January 18, 2005, is referenced as an appropriate source of service information for doing the actions specified in the NPRM). One commenter proposes revising paragraphs (c) and (f) of the NPRM to reference Revision 03 of the service bulletin. The same commenter also requests that EMBRAER Service Bulletin 145–32–0104, dated January 18, 2005; EMBRAER Service Bulletin 145– 32–0104, Revision 01, dated April 14, 2005; and EMBRAER Service Bulletin 145–32–0104, Revision 02, dated May 19, 2005; be considered acceptable for compliance with the NPRM. The same commenter also requests that paragraphs (c) and (f) of the NPRM be revised to reference EMBRAER Service Bulletin 145LEG–32–0020, Revision 01, June 21, 2005 (EMBRAER Service Bulletin 145LEG–32–0020, dated April 1, 2005, is referenced as an appropriate source of service information for doing the actions specified in the NPRM). In addition, the commenter requests that EMBRAER Service Bulletin 145LEG–32–0020, dated April 1, 2005, be considered acceptable for compliance with the NPRM. We agree with the commenters. The procedures in Revision 01 of EMBRAER Service Bulletin 145LEG–32–0020 are essentially the same as those in the original issue of the service bulletin. Revision 01 was issued to correct certain diagrams. The procedures in Revision 03 of EMBRAER Service Bulletin 145–32– 0104 are essentially the same as those in the original issue of the service bulletin. Revisions 01 and 02 were issued to revise certain figures. Revisions 01 and 02 were also issued to split the effectivity of the service bulletin into groups and clarify that serial numbers 14500839, 14500848, and 14500882 have an equivalent factory-incorporated modification and are not affected airplanes. Revision 03 was issued to update kit information. No airplanes have been added to the effectivity of any revision of EMBRAER Service Bulletin 145–32–0104 or 145LEG–32–0020. We have revised paragraphs (c) and (f) of this AD to reference EMBRAER Service Bulletin 145–32–0104, Revision 03, dated June 21, 2005; and EMBRAER Service Bulletin 145LEG–32–0020, Revision 01, June 21, 2005. We have also added a new paragraph (g) to this AD to state that actions accomplished according to the previous issues of the service bulletins are acceptable for E:\FR\FM\14NOR1.SGM 14NOR1

Agencies

[Federal Register Volume 70, Number 218 (Monday, November 14, 2005)]
[Rules and Regulations]
[Pages 69069-69071]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22220]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22169; Directorate Identifier 2005-NM-094-AD; 
Amendment 39-14361; AD 2005-23-03]
RIN 2120-AA64


Airworthiness Directives; Learjet Model 23, 24, 24A, 24B, 24B-A, 
24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 
24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires 
replacement of the spherical accumulator for the main hydraulic system 
with a new cylindrical accumulator. For certain airplanes, this AD also 
requires modification of the accumulator pressure gauge. This AD 
results from reports of the failure of two thrust reverser accumulators 
(which are similar to the main hydraulic system's spherical 
accumulator) and fatigue cracks found on four thrust reverser 
accumulators. We are issuing this AD to prevent failure of the 
spherical accumulator for the main hydraulic system, due to fatigue 
cracking on the threads, which could result in the loss of hydraulic 
power, damage to the surrounding airplane structure, and loss of 
airplane control. The failure of the accumulator could also result in 
injury to any persons in the surrounding area. The loss of hydraulic 
fluid could also leak onto a potential source of ignition and result in 
a consequent fire.

DATES: This AD becomes effective December 19, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 19, 
2005.

ADDRESSES: You may examine the AD docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209-2942, 
for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Robert Busto, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4157; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Learjet Model 
23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 
25B, 25C, 25D, and 25F airplanes. That NPRM was published in the 
Federal Register on August 23, 2005 (70 FR 49210). That NPRM proposed 
to require replacement of the spherical accumulator for the main 
hydraulic system with a new cylindrical accumulator. For certain

[[Page 69070]]

airplanes, that proposed AD would also require modification of the 
accumulator pressure gauge.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    There are about 434 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 242 airplanes of U.S. 
registry. The actions will take about 9 to 13 work hours per airplane, 
at an average labor rate of $65 per work hour. Required parts will cost 
about $1,336 to $1,363 per airplane. Based on these figures, the 
estimated cost of the AD for U.S. operators is $464,882 to $534,336, or 
$1,921 to $2,208 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We 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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-23-03 Learjet: Amendment 39-14361. Docket No. FAA-2005-22169; 
Directorate Identifier 2005-NM-094-AD.

Effective Date

    (a) This AD becomes effective December 19, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Learjet Model 23, 24, 24A, 24B, 24B-A, 
24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F 
airplanes, certificated in any category; having serial numbers 23-
003 through 23-099 inclusive, 24-100 through 24-284 inclusive, and 
25-003 through 25-153 inclusive.

Unsafe Condition

    (d) This AD results from reports of the failure of two thrust 
reverser accumulators (which are similar to the main hydraulic 
system's accumulator) and fatigue cracks found on four thrust 
reverser accumulators. We are issuing this AD to prevent failure of 
the spherical accumulator for the main hydraulic system, due to 
fatigue cracking on the threads, which could result in the loss of 
hydraulic power, damage to the surrounding airplane structure, and 
loss of airplane control. The failure of the accumulator could also 
result in injury to any persons in the surrounding area. The loss of 
hydraulic fluid could also leak onto a potential source of ignition 
and result in a consequent fire.

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.

Replacement

    (f) Within 60 days after the effective date of this AD, replace 
the spherical accumulator having part number (P/N) 2380025-() or P/N 
2380167-() with a new cylindrical accumulator having P/N 2497202-
801, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A23/24/25-29-4, Revision 1, dated 
January 17, 2005.

Concurrent Action

    (g) For airplanes having serial numbers 23-003 through 23-014 
inclusive: Prior to or concurrently with the actions in Bombardier 
Alert Service Bulletin A23/24/25-29-4, Revision 1, dated January 17, 
2005, relocate the accumulator pressure gauge in accordance with 
Learjet Service Kit SK23-215, dated April 4, 1966.

Parts Installation

    (h) As of the effective date, no spherical accumulator having P/
N 2380025-() or P/N 2380167-() may be installed on any airplane.

Previous Actions

    (i) Replacements done before the effective date of this AD in 
accordance with Bombardier Alert Service Bulletin A23/24/25-29-4, 
dated August 20, 2004, are acceptable for compliance with the 
requirements of paragraph (f) of this AD.

No Reporting Required

    (j) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Wichita Aircraft Certification Office, 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 Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

[[Page 69071]]

Material Incorporated by Reference

    (l) You must use Bombardier Alert Service Bulletin A23/24/25-29-
4, Revision 1, dated January 17, 2005; and Learjet Service Kit SK23-
215, dated April 4, 1966; as applicable, to perform the actions that 
are required by this AD, unless the AD specifies otherwise. (The 
issue date of Learjet Service Kit SK23-215 is located only on the 
first and last pages of the document.) 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 Learjet, 
Inc., One Learjet Way, Wichita, Kansas 67209-2942, for a copy of 
this service information. You may review copies at the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street SW., room PL-401, Nassif Building, Washington, DC; on the 
Internet at https://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 26, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22220 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P
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