Airworthiness Directives; British Aerospace Aircraft Group, Scottish Division, Model Beagle B.121 Series 1, 2, 3 Airplanes, 66087-66089 [E7-23025]

Download as PDF Federal Register / Vol. 72, No. 227 / Tuesday, November 27, 2007 / Proposed Rules requirements. We have determined that special conditions would be promulgated to apply the standards defined in § 25.853(d) to seats with large, non-metallic panels in their design. Applicability As discussed above, these special conditions are applicable to Boeing Model 757 series airplanes. It is not our intent, however, to require seats with large, non-metallic panels to meet § 25.853, Appendix F, parts IV and V, if they are installed in cabins of airplanes that otherwise are not required to meet these standards. Because the heat release and smoke testing requirements of § 25.853 per Appendix F, parts IV and V, are not part of the type certification basis of the Model 757, these special conditions are only applicable if the Model 757 series airplanes are in 14 CFR part 121 operations. Section 121.312 requires compliance with the heat release and smoke testing requirements of § 25.853, for certain airplanes, irrespective of the type certification bases of those airplanes. For Model 757 series airplanes, these are the airplanes that would be affected by these special conditions. Should TIMCO apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. A2NM to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model series of airplanes. It is not a rule of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane. incorporate non-traditional, large, nonmetallic panels that may either be a single component or multiple components in a concentrated area in their design. 2. The applicant may designate up to and including 1.5 square feet of nontraditional, non-metallic panel material per seat place that does not have to comply with special condition Number 1, above. A triple seat assembly may have a total of 4.5 square feet excluded on any portion of the assembly (e.g., outboard seat place 1 square foot, middle 1 square foot, and inboard 2.5 square feet). 3. Seats do not have to meet the test requirements of Title 14 CFR part 25, Appendix F, parts IV and V, when installed in compartments that are not otherwise required to meet these requirements. Examples include: a. Airplanes with passenger capacities of 19 or less, b. Airplanes that do not have § 25.853, Amendment 25–61 or later, in their certification basis and do not need to comply with the requirements of 14 CFR § 121.312, and c. Airplanes exempted from § 25.853, Amendment 25–61 or later. Issued in Renton, Washington, on November 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23079 Filed 11–26–07; 8:45 am] BILLING CODE 4910–13–P ycherry on PROD1PC66 with PROPOSALS The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 27, 2007. You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. ADDRESSES: Federal Aviation Administration You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4138; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2007–0248; Directorate Identifier 2007–CE–084–AD] Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. AGENCY: The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Boeing Model 757 series airplanes modified by TIMCO. 1. Except as provided in paragraph 3 of these special conditions, compliance with Title 14 CFR part 25, Appendix F, parts IV and V, heat release and smoke emission, is required for seats that SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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 Jkt 214001 The Type Certificate Holder (TCH) has received several reports of failed Rudder torque tube assemblies. The torque tube assemblies are subject to repetitive inspection in accordance Airworthiness Directive 2060 PRE 80. The recent failures occurred in service after the inspections required by AD 2060 PRE 80 had been performed. In the event of such failures, loss of directional control through both the Rudder and Nosewheel Steering may occur. The TCH has also received reports of loose rivets attaching the inboard Anchor Assembly to the Starboard Torque Tube. Examining the AD Docket Airworthiness Directives; British Aerospace Aircraft Group, Scottish Division, Model Beagle B.121 Series 1, 2, 3 Airplanes 15:23 Nov 26, 2007 product. The MCAI describes the unsafe condition as: DEPARTMENT OF TRANSPORTATION List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: VerDate Aug<31>2005 66087 RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments E:\FR\FM\27NOP1.SGM 27NOP1 66088 Federal Register / Vol. 72, No. 227 / Tuesday, November 27, 2007 / Proposed Rules to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–****; Directorate Identifier 2007–CE–084–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The United Kingdom Civil Aviation Authority, which is the aviation authority for United Kingdom, has issued AD No: G–2005–0030, dated October 12, 2005 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The Type Certificate Holder (TCH) has received several reports of failed Rudder torque tube assemblies. The torque tube assemblies are subject to repetitive inspection in accordance Airworthiness Directive 2060 PRE 80. The recent failures occurred in service after the inspections required by AD 2060 PRE 80 had been performed. In the event of such failures, loss of directional control through both the Rudder and Nosewheel Steering may occur. The TCH has also received reports of loose rivets attaching the inboard Anchor Assembly to the Starboard Torque Tube. The MCAI requires the inspection of the rudder torque tube assemblies and hubs for cracking and loose rivets with conditional correction or replacement following de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005. You may obtain further information by examining the MCAI in the AD docket. ycherry on PROD1PC66 with PROPOSALS Relevant Service Information De Havilland Support Limited has issued Service Bulletin No. B121/65, Issue 2, dated August 10, 2005. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of VerDate Aug<31>2005 15:23 Nov 26, 2007 Jkt 214001 Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed 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 proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 1 product of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $80, or $80 per product. In addition, we estimate that any necessary follow-on actions would take about 12 work-hours and require parts costing $10,000 for a cost of $10,960 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 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: British Aerospace (Scotland): Docket No. FAA–2007–0248; Directorate Identifier 2007–CE–084–AD. Comments Due Date (a) We must receive comments by December 27, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Beagle B.121 Series 1, 2, 3 airplanes, all serial numbers, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. E:\FR\FM\27NOP1.SGM 27NOP1 Federal Register / Vol. 72, No. 227 / Tuesday, November 27, 2007 / Proposed Rules Reason (e) The mandatory continuing airworthiness information (MCAI) states: The Type Certificate Holder (TCH) has received several reports of failed Rudder torque tube assemblies. The torque tube assemblies are subject to repetitive inspection in accordance Airworthiness Directive 2060 PRE 80. The recent failures occurred in service after the inspections required by AD 2060 PRE 80 had been performed. In the event of such failures, loss of directional control through both the Rudder and Nosewheel Steering may occur. The TCH has also received reports of loose rivets attaching the inboard Anchor Assembly to the Starboard Torque Tube. The MCAI requires the inspection of the rudder torque tube assemblies and hubs for cracking and loose rivets with conditional correction or replacement in accordance with de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005. Actions and Compliance (f) Unless already done, do the following actions: (1) Within 100 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals not to exceed 100 hours TIS, inspect the Rudder Torque Tube Assemblies following de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005. (2) Before further flight, replace any cracked Rudder Torque Tube Assemblies and correct any loose rivets in the Rudder Torque Tube Assemblies that are found in the inspections required in paragraph (f)(1) of this AD, following de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005. (3) After the effective date of this AD, used rudder torque assemblies held as spares for British Aerospace Aircraft Group, Scottish Division, Model Beagle B.121 Series 1, 2, 3 airplanes must be inspected following de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005, and found free of cracks prior to installation. FAA AD Differences ycherry on PROD1PC66 with PROPOSALS Note: 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, Standards Office, 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: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4138; fax: (816) 329– 4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. VerDate Aug<31>2005 15:23 Nov 26, 2007 Jkt 214001 (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 (44 U.S.C. 3501 et seq.), 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 United Kingdom Civil Aviation Authority AD No: G–2005–0030, dated October 12, 2005; and de Havilland Support Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005, for related information. Issued in Kansas City, Missouri, on November 20, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23025 Filed 11–26–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0249; Directorate Identifier 2007–CE–088–AD] RIN 2120–AA64 Airworthiness Directives; Alpha Aviation Design Limited Model R2160 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed 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 distortion of the rudder bars due to rudder control forces during aerobatic operation and nose wheel steering reaction forces. Rudder bar distortion could result in reduced control or loss of control. The proposed AD would require actions that are PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 66089 intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by December 27, 2007. You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0249; Directorate Identifier 2007–CE–088–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this E:\FR\FM\27NOP1.SGM 27NOP1

Agencies

[Federal Register Volume 72, Number 227 (Tuesday, November 27, 2007)]
[Proposed Rules]
[Pages 66087-66089]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23025]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0248; Directorate Identifier 2007-CE-084-AD]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Aircraft Group, 
Scottish Division, Model Beagle B.121 Series 1, 2, 3 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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:

    The Type Certificate Holder (TCH) has received several reports 
of failed Rudder torque tube assemblies. The torque tube assemblies 
are subject to repetitive inspection in accordance Airworthiness 
Directive 2060 PRE 80. The recent failures occurred in service after 
the inspections required by AD 2060 PRE 80 had been performed. In 
the event of such failures, loss of directional control through both 
the Rudder and Nosewheel Steering may occur. The TCH has also 
received reports of loose rivets attaching the inboard Anchor 
Assembly to the Starboard Torque Tube.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by December 27, 
2007.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments

[[Page 66088]]

to an address listed under the ADDRESSES section. Include ``Docket No. 
FAA-2007-****; Directorate Identifier 2007-CE-084-AD'' at the beginning 
of your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. We will consider all comments received by the closing date 
and may amend this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The United Kingdom Civil Aviation Authority, which is the aviation 
authority for United Kingdom, has issued AD No: G-2005-0030, dated 
October 12, 2005 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    The Type Certificate Holder (TCH) has received several reports 
of failed Rudder torque tube assemblies. The torque tube assemblies 
are subject to repetitive inspection in accordance Airworthiness 
Directive 2060 PRE 80. The recent failures occurred in service after 
the inspections required by AD 2060 PRE 80 had been performed. In 
the event of such failures, loss of directional control through both 
the Rudder and Nosewheel Steering may occur. The TCH has also 
received reports of loose rivets attaching the inboard Anchor 
Assembly to the Starboard Torque Tube.

    The MCAI requires the inspection of the rudder torque tube 
assemblies and hubs for cracking and loose rivets with conditional 
correction or replacement following de Havilland Support Limited 
Service Bulletin B121/65, Issue 2, dated August 10, 2005.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    De Havilland Support Limited has issued Service Bulletin No. B121/
65, Issue 2, dated August 10, 2005. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed 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 proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 1 product of U.S. registry. We also estimate that it 
would take about 1 work-hour per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $80, or $80 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 12 work-hours and require parts costing $10,000 for a cost 
of $10,960 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

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

British Aerospace (Scotland): Docket No. FAA-2007-0248; Directorate 
Identifier 2007-CE-084-AD.

Comments Due Date

    (a) We must receive comments by December 27, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Beagle B.121 Series 1, 2, 3 airplanes, 
all serial numbers, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 27: Flight 
Controls.

[[Page 66089]]

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    The Type Certificate Holder (TCH) has received several reports 
of failed Rudder torque tube assemblies. The torque tube assemblies 
are subject to repetitive inspection in accordance Airworthiness 
Directive 2060 PRE 80. The recent failures occurred in service after 
the inspections required by AD 2060 PRE 80 had been performed. In 
the event of such failures, loss of directional control through both 
the Rudder and Nosewheel Steering may occur. The TCH has also 
received reports of loose rivets attaching the inboard Anchor 
Assembly to the Starboard Torque Tube.

The MCAI requires the inspection of the rudder torque tube 
assemblies and hubs for cracking and loose rivets with conditional 
correction or replacement in accordance with de Havilland Support 
Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within 100 hours time-in-service (TIS) after the effective 
date of this AD and thereafter at intervals not to exceed 100 hours 
TIS, inspect the Rudder Torque Tube Assemblies following de 
Havilland Support Limited Service Bulletin B121/65, Issue 2, dated 
August 10, 2005.
    (2) Before further flight, replace any cracked Rudder Torque 
Tube Assemblies and correct any loose rivets in the Rudder Torque 
Tube Assemblies that are found in the inspections required in 
paragraph (f)(1) of this AD, following de Havilland Support Limited 
Service Bulletin B121/65, Issue 2, dated August 10, 2005.
    (3) After the effective date of this AD, used rudder torque 
assemblies held as spares for British Aerospace Aircraft Group, 
Scottish Division, Model Beagle B.121 Series 1, 2, 3 airplanes must 
be inspected following de Havilland Support Limited Service Bulletin 
B121/65, Issue 2, dated August 10, 2005, and found free of cracks 
prior to installation.

FAA AD Differences

    Note: 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, 
Standards Office, 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: Taylor Martin, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4138; fax: (816) 329-4090. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.
    (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 (44 
U.S.C. 3501 et seq.), 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 United Kingdom Civil Aviation Authority AD No: 
G-2005-0030, dated October 12, 2005; and de Havilland Support 
Limited Service Bulletin B121/65, Issue 2, dated August 10, 2005, 
for related information.

    Issued in Kansas City, Missouri, on November 20, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E7-23025 Filed 11-26-07; 8:45 am]
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