Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes, 38912-38914 [E9-18018]

Download as PDF 38912 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations after a full up or down selection in the hydraulic mode. Based on the above described failure scenario, the differences in the design properties and the positive experience, aeroplanes in pre-SBF50–27–030 configuration are not affected by this AD. Corrective actions include readjusting the upstop position if clearance between the flap mechanical drive nut and the up-and-downstop is incorrect, and if any cracks are found during the non-destructive inspection, replacing the part with a serviceable part. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 12 months after the effective date of this AD, inspect the clearance between the flap mechanical drive nut and the up-and-down-stop, and before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF50–27–043, dated November 17, 2008. (2) If, during accomplishment of the actions required by paragraph (f)(1) of this AD, abutments marks are found, or when the up-and-down-stop touches the drive nut after a full up or down selection in the hydraulic mode, before further flight, do a nondestructive inspection for cracking, in accordance with Fokker Service Bulletin SBF50–27–043, dated November 17, 2008. If any cracking is found, before further flight, replace the part with a serviceable part. FAA AD Differences srobinson on DSKHWCL6B1PROD with RULES Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the VerDate Nov<24>2008 16:20 Aug 04, 2009 Jkt 217001 provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2009–0047, dated March 2, 2009; Fokker Service Bulletin SBF50–27–043, dated November 17, 2008; for related information. Material Incorporated by Reference (i) You must use Fokker Service Bulletin SBF50–27–043, dated November 17, 2008, 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 Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; e-mail technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference 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. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A failure mode has been identified that can lead to loss of a nose wheel. Any combination of excessive wear and/or adverse tolerances on the axle inner cone, outer cone or wheel hub splined sleeve cones can result in the loss of the critical gap between the inner flange face of the wheel outer cone and the axle end face. If this gap is lost, it can result in the wheel having free play along the length of the axle. This condition, if not corrected, can result in breakage of the wheel nut lock plate leading to unscrewing of the wheel retention nut and subsequent separation of the nose wheel from the landing gear axle. DEPARTMENT OF TRANSPORTATION * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 9, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 9, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Federal Aviation Administration Discussion Issued in Renton, Washington, on July 24, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–18417 Filed 8–4–09; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2009–0463; Directorate Identifier 2008–NM–065–AD; Amendment 39–15984; AD 2009–16–01] RIN 2120–AA64 Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 20, 2009 (74 FR 23671). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: A failure mode has been identified that can lead to loss of a nose wheel. Any combination of excessive wear and/or adverse tolerances on the axle inner cone, outer cone or wheel hub splined sleeve cones E:\FR\FM\05AUR1.SGM 05AUR1 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations can result in the loss of the critical gap between the inner flange face of the wheel outer cone and the axle end face. If this gap is lost, it can result in the wheel having free play along the length of the axle. This condition, if not corrected, can result in breakage of the wheel nut lock plate leading to unscrewing of the wheel retention nut and subsequent separation of the nose wheel from the landing gear axle. For the reasons described above, this AD requires repetitive inspections of the nose landing gear to ensure that the wheels are correctly retained and, depending on findings, replacement of worn parts. Required actions include inspecting the lock plate for damage (including excessive wear) and cracking, and replacing the lock plate with a new or serviceable part if any damage or cracking is found; inspecting the wheel nut for damage, and replacing any damaged nut with a new or serviceable part; and measuring the gap between the inner flange of the outer cone (at each of the three sections) and the end face of the axle to determine if parts are worn, and replacing worn parts with new or serviceable parts. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. srobinson on DSKHWCL6B1PROD with RULES Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 7 products of U.S. registry. We also estimate that it will take about 4 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. VerDate Nov<24>2008 17:30 Aug 04, 2009 Jkt 217001 Based on these figures, we estimate the cost of this AD to the U.S. operators to be $2,240, or $320 per product. 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 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 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 38913 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: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–16–01 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39– 15984. Docket No. FAA–2009–0463; Directorate Identifier 2008–NM–065–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 9, 2009. Affected ADs (b) None. Applicability (c) This AD applies to BAE Systems (Operations) Limited Model Jetstream 4101 airplanes, certificated in any category, all models, all serial numbers. Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: A failure mode has been identified that can lead to loss of a nose wheel. Any combination of excessive wear and/or adverse tolerances on the axle inner cone, outer cone or wheel hub splined sleeve cones can result in the loss of the critical gap between the inner flange face of the wheel outer cone and the axle end face. If this gap is lost, it can result in the wheel having free play along the length of the axle. This condition, if not corrected, can result in breakage of the wheel nut lock plate leading to unscrewing of the wheel retention nut and subsequent separation of the nose wheel from the landing gear axle. For the reasons described above, this AD requires repetitive inspections of the nose landing gear to ensure that the wheels are correctly retained and, depending on findings, replacement of worn parts. Required actions include inspecting the lock plate for damage (including excessive wear) and cracking, and replacing the lock plate with a new or serviceable part if any damage or cracking is found; inspecting the wheel E:\FR\FM\05AUR1.SGM 05AUR1 38914 Federal Register / Vol. 74, No. 149 / Wednesday, August 5, 2009 / Rules and Regulations nut for damage, and replacing any damaged nut with a new or serviceable part; and measuring the gap between the inner flange of the outer cone (at each of the three sections) and the end face of the axle to determine if parts are worn, and replacing worn parts with new or serviceable parts. Actions and Compliance (f) Unless already done, do the following actions for the left and right nose wheel attachments to the axle. (1) Within 3 months after the effective date of this AD, inspect the lock plate for damage (including excessive wear) and cracking, inspect the wheel nut for damage, and measure the gap between the inner flange of the outer cone and the end face of the axle to determine if parts are worn, in accordance with paragraph 2.B. of BAE Systems (Operations) Limited Service Bulletin J41– 32–086, dated June 27, 2007. (2) If, during any inspection required by paragraph (f)(1) of this AD, any damage or cracking of the lock plate is found, before further flight, replace the lock plate with a new or serviceable part, in accordance with paragraph 2.B. of BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007. (3) If, during any inspection required by paragraph (f)(1) of this AD, any damage of the wheel nut is found, before further flight, replace the wheel nut with a new or serviceable part, in accordance with paragraph 2.B. of BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007. (4) If, during any measurement required by paragraph (f)(1) of this AD, the measured gap size is found to be less than 0.002 inch (0.05 mm), before further flight, replace any worn parts with new or serviceable parts, in accordance with paragraph 2.B. of BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007. Within 3,000 flight hours after doing the replacement, repeat the actions for the left and right nose wheel attachments to the axle that are required by paragraph (f)(1) of this AD. (5) If, during any measurement required by paragraph (f)(1) of this AD, the measured gap size is equal to or more than 0.002 inch (0.05 mm), repeat the actions for the left and right nose wheel attachments to the axle that are required by paragraph (f)(1) of this AD thereafter at intervals not to exceed the value indicated in Table 1 of this AD, depending on the exact finding. If, during any repeat inspection, the finding has changed to another value (see Table 1), adjust the new interval accordingly. srobinson on DSKHWCL6B1PROD with RULES TABLE 1—REPEAT INSPECTION INTERVALS Measured gap size 0.002 inch to 0.005 inch inclusive (0.05/0.13mm) ............... Greater than 0.005 inch to less than or equal to 0.010 inch (0.13/0.25mm) ....................... VerDate Nov<24>2008 16:20 Aug 04, 2009 Repeat inspection interval in flight hours 500 1,000 Jkt 217001 TABLE 1—REPEAT INSPECTION INTERVALS—Continued Measured gap size Repeat inspection interval in flight hours Greater than 0.010 inch to less than or equal to 0.020 inch (0.25/0.51mm) ....................... Greater than 0.020 inch (0.51mm) ............................... 2,000 3,000 Note 1: Replacement of parts does not constitute terminating action for the inspection requirements of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Although BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007, does not specify an inspection following the replacement of the left and right nose wheel attachment to the axle for measurements less than 0.002 inch, paragraph (f)(4) of this AD requires an inspection within 3,000 flight hours after replacing the part. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0036, dated February 22, 2008; and BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007; for related information. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Material Incorporated by Reference (i) You must use BAE Systems (Operations) Limited Service Bulletin J41–32–086, dated June 27, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; e-mail raebusiness@baesystems.com; Internet https://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 22, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–18018 Filed 8–4–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Bureau of the Census 15 CFR Part 30 [Docket Number: 090422707–9708–01] RIN 0607–AA48 Foreign Trade Regulations (FTR): Eliminate the Social Security Number (SSN) as an Identification Number in the Automated Export System (AES) AGENCY: Bureau of the Census, Commerce Department. ACTION: Interim final rule with request for comments. SUMMARY: The U.S. Census Bureau (Census Bureau) is amending the Foreign Trade Regulations (FTR) to eliminate the requirement to report a Social Security Number (SSN) as an identification number when registering to file and filing electronic export information in the Automated Export System (AES) or AESDirect. Under the current regulations, the U.S. Principal Party in Interest (USPPI) or U.S. authorized agent residing or having an E:\FR\FM\05AUR1.SGM 05AUR1

Agencies

[Federal Register Volume 74, Number 149 (Wednesday, August 5, 2009)]
[Rules and Regulations]
[Pages 38912-38914]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-18018]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0463; Directorate Identifier 2008-NM-065-AD; 
Amendment 39-15984; AD 2009-16-01]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited 
(Jetstream) Model 4101 Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    A failure mode has been identified that can lead to loss of a 
nose wheel. Any combination of excessive wear and/or adverse 
tolerances on the axle inner cone, outer cone or wheel hub splined 
sleeve cones can result in the loss of the critical gap between the 
inner flange face of the wheel outer cone and the axle end face. If 
this gap is lost, it can result in the wheel having free play along 
the length of the axle. This condition, if not corrected, can result 
in breakage of the wheel nut lock plate leading to unscrewing of the 
wheel retention nut and subsequent separation of the nose wheel from 
the landing gear axle.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective September 9, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 9, 
2009.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on May 20, 2009 (74 FR 
23671). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A failure mode has been identified that can lead to loss of a 
nose wheel. Any combination of excessive wear and/or adverse 
tolerances on the axle inner cone, outer cone or wheel hub splined 
sleeve cones

[[Page 38913]]

can result in the loss of the critical gap between the inner flange 
face of the wheel outer cone and the axle end face. If this gap is 
lost, it can result in the wheel having free play along the length 
of the axle. This condition, if not corrected, can result in 
breakage of the wheel nut lock plate leading to unscrewing of the 
wheel retention nut and subsequent separation of the nose wheel from 
the landing gear axle.
    For the reasons described above, this AD requires repetitive 
inspections of the nose landing gear to ensure that the wheels are 
correctly retained and, depending on findings, replacement of worn 
parts.

Required actions include inspecting the lock plate for damage 
(including excessive wear) and cracking, and replacing the lock plate 
with a new or serviceable part if any damage or cracking is found; 
inspecting the wheel nut for damage, and replacing any damaged nut with 
a new or serviceable part; and measuring the gap between the inner 
flange of the outer cone (at each of the three sections) and the end 
face of the axle to determine if parts are worn, and replacing worn 
parts with new or serviceable parts. You may obtain further information 
by examining the MCAI in the AD docket.

Comments

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

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 7 products of U.S. registry. 
We also estimate that it will take about 4 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $2,240, or $320 per product.

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 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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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 FAA amends Sec.  39.13 by adding the following new AD:

2009-16-01 BAE Systems (Operations) Limited (Formerly British 
Aerospace Regional Aircraft): Amendment 39-15984. Docket No. FAA-
2009-0463; Directorate Identifier 2008-NM-065-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 9, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to BAE Systems (Operations) Limited Model 
Jetstream 4101 airplanes, certificated in any category, all models, 
all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    A failure mode has been identified that can lead to loss of a 
nose wheel. Any combination of excessive wear and/or adverse 
tolerances on the axle inner cone, outer cone or wheel hub splined 
sleeve cones can result in the loss of the critical gap between the 
inner flange face of the wheel outer cone and the axle end face. If 
this gap is lost, it can result in the wheel having free play along 
the length of the axle. This condition, if not corrected, can result 
in breakage of the wheel nut lock plate leading to unscrewing of the 
wheel retention nut and subsequent separation of the nose wheel from 
the landing gear axle.
    For the reasons described above, this AD requires repetitive 
inspections of the nose landing gear to ensure that the wheels are 
correctly retained and, depending on findings, replacement of worn 
parts.

Required actions include inspecting the lock plate for damage 
(including excessive wear) and cracking, and replacing the lock 
plate with a new or serviceable part if any damage or cracking is 
found; inspecting the wheel

[[Page 38914]]

nut for damage, and replacing any damaged nut with a new or 
serviceable part; and measuring the gap between the inner flange of 
the outer cone (at each of the three sections) and the end face of 
the axle to determine if parts are worn, and replacing worn parts 
with new or serviceable parts.

Actions and Compliance

    (f) Unless already done, do the following actions for the left 
and right nose wheel attachments to the axle.
    (1) Within 3 months after the effective date of this AD, inspect 
the lock plate for damage (including excessive wear) and cracking, 
inspect the wheel nut for damage, and measure the gap between the 
inner flange of the outer cone and the end face of the axle to 
determine if parts are worn, in accordance with paragraph 2.B. of 
BAE Systems (Operations) Limited Service Bulletin J41-32-086, dated 
June 27, 2007.
    (2) If, during any inspection required by paragraph (f)(1) of 
this AD, any damage or cracking of the lock plate is found, before 
further flight, replace the lock plate with a new or serviceable 
part, in accordance with paragraph 2.B. of BAE Systems (Operations) 
Limited Service Bulletin J41-32-086, dated June 27, 2007.
    (3) If, during any inspection required by paragraph (f)(1) of 
this AD, any damage of the wheel nut is found, before further 
flight, replace the wheel nut with a new or serviceable part, in 
accordance with paragraph 2.B. of BAE Systems (Operations) Limited 
Service Bulletin J41-32-086, dated June 27, 2007.
    (4) If, during any measurement required by paragraph (f)(1) of 
this AD, the measured gap size is found to be less than 0.002 inch 
(0.05 mm), before further flight, replace any worn parts with new or 
serviceable parts, in accordance with paragraph 2.B. of BAE Systems 
(Operations) Limited Service Bulletin J41-32-086, dated June 27, 
2007. Within 3,000 flight hours after doing the replacement, repeat 
the actions for the left and right nose wheel attachments to the 
axle that are required by paragraph (f)(1) of this AD.
    (5) If, during any measurement required by paragraph (f)(1) of 
this AD, the measured gap size is equal to or more than 0.002 inch 
(0.05 mm), repeat the actions for the left and right nose wheel 
attachments to the axle that are required by paragraph (f)(1) of 
this AD thereafter at intervals not to exceed the value indicated in 
Table 1 of this AD, depending on the exact finding. If, during any 
repeat inspection, the finding has changed to another value (see 
Table 1), adjust the new interval accordingly.

                  Table 1--Repeat Inspection Intervals
------------------------------------------------------------------------
                                                                Repeat
                                                              inspection
                     Measured gap size                       interval in
                                                                flight
                                                                hours
------------------------------------------------------------------------
0.002 inch to 0.005 inch inclusive (0.05/0.13mm)...........          500
Greater than 0.005 inch to less than or equal to 0.010 inch        1,000
 (0.13/0.25mm).............................................
Greater than 0.010 inch to less than or equal to 0.020 inch        2,000
 (0.25/0.51mm).............................................
Greater than 0.020 inch (0.51mm)...........................        3,000
------------------------------------------------------------------------


    Note 1:  Replacement of parts does not constitute terminating 
action for the inspection requirements of this AD.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: Although BAE Systems (Operations) Limited Service 
Bulletin J41-32-086, dated June 27, 2007, does not specify an 
inspection following the replacement of the left and right nose 
wheel attachment to the axle for measurements less than 0.002 inch, 
paragraph (f)(4) of this AD requires an inspection within 3,000 
flight hours after replacing the part.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, 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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-1175; fax (425) 227-1149. Before using any approved AMOC 
on any airplane to which the AMOC applies, notify your principal 
maintenance inspector (PMI) or principal avionics inspector (PAI), 
as appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2008-0036, dated February 22, 2008; and BAE Systems 
(Operations) Limited Service Bulletin J41-32-086, dated June 27, 
2007; for related information.

Material Incorporated by Reference

    (i) You must use BAE Systems (Operations) Limited Service 
Bulletin J41-32-086, dated June 27, 2007, to do the actions required 
by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact BAE 
Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com; 
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 22, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-18018 Filed 8-4-09; 8:45 am]
BILLING CODE 4910-13-P
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