Airworthiness Directives; British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes, 12133-12135 [E7-4739]

Download as PDF Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 12133 Actions Compliance Procedures (1) Visually inspect the engine mount for any cracks. Initially inspect upon accumulating 1,300 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, unless already done. Thereafter, inspect repetitively at intervals not to exceed 300 hours TIS. Before further flight after any inspection required by paragraph (e)(1) of this AD where crack damage is found. If you repair the cracked engine mount, then continue to reinspect at intervals not to exceed 300 hours TIS, unless the repair scheme states differently. If you replace the engine mount, then initially inspect upon accumulating 1,300 hours TIS and repetitively at intervals not to exceed 300 hours TIS. Within the next 30 days after you find the cracks or within the next 30 days after the effective date of this AD, whichever occurs later. Follow Snow Engineering Co. Service Letter #253, dated December 12, 2005, revised January 22, 2007. (2) If you find any crack damage, do the following: (i) Obtain an FAA-approved repair scheme or replacement procedure from the manufacturer; and (ii) Repair following the FAA-approved repair scheme or replace the engine mount with a new engine mount following the replacement procedure. (3) Report any cracks that you find to the FAA at the address specified in paragraph (f) of this AD. Include in your report: (i) Airplane serial number; (ii) Airplane hours TIS and engine mount hours TIS; (iii) Crack location(s) and size(s); (iv) Corrective action taken; and (v) Point of contact name and telephone number. For obtaining a repair scheme or replacement procedure: Contact Air Tractor Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120–0056. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION directional control during critical phases of take-off and landing. (f) The Manager, Fort Worth Airplane Certification Office, FAA, ATTN: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308–3365; facsimile: (210) 308–3370, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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. (g) AMOCs approved for AD 2006–22–08 are not approved for this AD. Federal Aviation Administration 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 April 16, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. Related Information rmajette on PROD1PC67 with PROPOSALS (h) To get copies of the service information referenced in this AD, contact Air Tractor Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https:// ms.dot.gov. The docket number is Docket No. FAA–2007–27212; Directorate Identifier 2007–CE–011–AD. Issued in Kansas City, Missouri, on March 8, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–4737 Filed 3–14–07; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 14:19 Mar 14, 2007 Jkt 211001 14 CFR Part 39 [Docket No. FAA–2007–27213; Directorate Identifier 2007–CE–012–AD] RIN 2120–AA64 Airworthiness Directives; British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 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: Cracking has been found in the nose landing gear steering jack piston rod adjacent to the eye-end. This was caused by the application of excessive tightening torque applied to the eye-end whilst being assembled during component overhaul. Failure of the steering jack piston during operation will result in loss of nose wheel steering, which may lead to loss of PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.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– 5227) is in the ADDRESSES section. E:\FR\FM\15MRP1.SGM 15MRP1 12134 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 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: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. rmajette on PROD1PC67 with PROPOSALS 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–2007–27213; Directorate Identifier 2007–CE–012–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:// dms.dot.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 On March 25, 2003, we issued AD 2003–07–06, Amendment 39–13102 (68 FR 16195, April 3, 2003). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2003–07–06, following the completion of their testing, the equipment manufacturer has VerDate Aug<31>2005 14:19 Mar 14, 2007 Jkt 211001 determined that the fatigue life needs further revision (reduction) and has published inspection criteria and a revised formula for calculating the piston safe life. This calculation and a revised end fitting tightening torque are contained in Revision 1 to APPH Ltd. Service Bulletin 32–76. As a result, pistons, which were previously calculated to have significant remaining life, may now be unserviceable. The Civil Aviation Authority, which is the aviation authority for the United Kingdom, has issued AD No. G–2004– 0029, dated December 20, 2004 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Cracking has been found in the nose landing gear steering jack piston rod adjacent to the eye-end. This was caused by the application of excessive tightening torque applied to the eye-end whilst being assembled during component overhaul. Failure of the steering jack piston during operation will result in loss of nose wheel steering, which may lead to loss of directional control during critical phases of take-off and landing. The MCAI requires: The inspections and any required rectification actions detailed in BAe Systems Service Bulletin 32–JA030644 and associated APPH Service Bulletin 32–76 Revision 1 are required to be performed to ensure continued airworthiness of the aircraft. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information BAE Systems has issued British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JA030644, dated October 6, 2003. APPH Ltd. has issued Service Bulletin 32–76, Revision 1, dated August 2003. 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. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 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 190 products of U.S. registry. We also estimate that it would take about 2 work-hours 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 $30,400, or $160 per product. In addition, we estimate that any necessary follow-on actions would take about 8 work-hours and require parts costing $5,300, for a cost of $5,940 per product. We have no way of determining the number of products that may need these actions. 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 E:\FR\FM\15MRP1.SGM 15MRP1 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 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 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2003–07–06, Amendment 39–13102 (68 FR 16195, April 3, 2003), and adding the following new AD: British Aerospace Regional Aircraft: Docket No. FAA–2007–27213; Directorate Identifier 2007–CE–012–AD. Comments Due Date (a) We must receive comments by April 16, 2007. rmajette on PROD1PC67 with PROPOSALS Affected ADs (b) Supersedes AD 2003–07–06, Amendment 39–13102. Applicability (c) This AD applies to Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes, all serial numbers, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 32: Landing Gear. VerDate Aug<31>2005 14:19 Mar 14, 2007 Reason FAA AD Differences (e) The mandatory continuing airworthiness information (MCAI) states: Cracking has been found in the nose landing gear steering jack piston rod adjacent to the eye-end. This was caused by the application of excessive tightening torque applied to the eye-end whilst being assembled during component overhaul. Failure of the steering jack piston during operation will result in loss of nose wheel steering, which may lead to loss of directional control during critical phases of take-off and landing. Note: This AD differs from the MCAI and/ or service information as follows: No differences. Retained Requirements of AD 2003–07–06 (f) Unless already done, do the following actions in accordance with the procedures in APPH Ltd. Service Bulletin 32–76 (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), as referenced in BAe Systems British Aerospace Jetstream Mandatory Service Bulletin 32– JA020741, Original Issue: November 2, 2002; or APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003, as referenced in BAe Systems British Aerospace Jetstream Mandatory Service Bulletin 32–JA030644, Original Issue: October 6, 2003. (1) Within the next 90 days or 200 groundair-ground (GAG) cycles after May 22, 2003 (the effective date of AD 2003–07–06), whichever occurs first, inspect the steering jack piston rod for cracks. (2) If cracks are found, replace the cracked steering jack piston rod. Install the new steering jack piston rod using a torque setting of 175 lbf (pound force) inch or 20 Nm (Newton meters) when tightening the end fitting and stop bolt. (3) If no cracks are found, determine the torque setting of the steering jack piston rod end fitting and stop bolt. New Requirements of This AD: Actions and Compliance [Amended] Jkt 211001 12135 (g) Unless already done, do the following actions: (1) Within 90 days after the effective date of this AD, recalculate the safe life of the steering jack piston rod and re-torque the piston rod eye-end in accordance with APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003, as referenced in paragraph 2, Part 2 of BAe Systems Service Bulletin 32–JA030644, dated October 6, 2003. (2) If the piston rod is found unserviceable when inspected in accordance with APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003, as referenced in paragraph 2, Part 2 of BAe Systems Service Bulletin 32–JA030644, dated October 6, 2003, before further flight remove the steering jack and replace with a serviceable unit. (3) As of the effective date of this AD, before a steering jack piston rod is installed, it must be inspected and the safe life determined in accordance APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003, as referenced in paragraph 2 of BAe Systems Service Bulletin 32–JA030644, dated October 6, 2003. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, Small Airplane Directorate, ATTN: Taylor Martin, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4138; fax: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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) AMOCs approved for AD 2003–07–06 are not approved for this AD. (3) 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. (4) 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 (i) Refer to MCAI Civil Aviation Authority AD No. G–2004–0029, dated December 20, 2004; BAE Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JA030644, dated October 6, 2003; BAe Systems British Aerospace Jetstream Mandatory Service Bulletin 32–JA020741, Original Issue: November 2, 2002; APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003; and APPH Ltd. Service Bulletin 32–76 (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002, for related information. Issued in Kansas City, Missouri, on March 8, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–4739 Filed 3–14–07; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\15MRP1.SGM 15MRP1

Agencies

[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Proposed Rules]
[Pages 12133-12135]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4739]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27213; Directorate Identifier 2007-CE-012-AD]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Regional Aircraft 
Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 
3101, and Jetstream Model 3201 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 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:

    Cracking has been found in the nose landing gear steering jack 
piston rod adjacent to the eye-end. This was caused by the 
application of excessive tightening torque applied to the eye-end 
whilst being assembled during component overhaul. Failure of the 
steering jack piston during operation will result in loss of nose 
wheel steering, which may lead to loss of directional control during 
critical phases of take-off and landing.

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 April 16, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: https://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
dms.dot.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) 647-5227) is in the ADDRESSES section.

[[Page 12134]]

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:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This proposed AD references the MCAI and related service 
information that we considered in forming the engineering basis to 
correct the unsafe condition. The proposed AD contains text copied from 
the MCAI and for this reason might not follow our plain language 
principles.

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-
27213; Directorate Identifier 2007-CE-012-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://
dms.dot.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

    On March 25, 2003, we issued AD 2003-07-06, Amendment 39-13102 (68 
FR 16195, April 3, 2003). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2003-07-06, following the completion of their 
testing, the equipment manufacturer has determined that the fatigue 
life needs further revision (reduction) and has published inspection 
criteria and a revised formula for calculating the piston safe life. 
This calculation and a revised end fitting tightening torque are 
contained in Revision 1 to APPH Ltd. Service Bulletin 32-76. As a 
result, pistons, which were previously calculated to have significant 
remaining life, may now be unserviceable.
    The Civil Aviation Authority, which is the aviation authority for 
the United Kingdom, has issued AD No. G-2004-0029, dated December 20, 
2004 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    Cracking has been found in the nose landing gear steering jack 
piston rod adjacent to the eye-end. This was caused by the 
application of excessive tightening torque applied to the eye-end 
whilst being assembled during component overhaul. Failure of the 
steering jack piston during operation will result in loss of nose 
wheel steering, which may lead to loss of directional control during 
critical phases of take-off and landing.
    The MCAI requires:
    The inspections and any required rectification actions detailed 
in BAe Systems Service Bulletin 32-JA030644 and associated APPH 
Service Bulletin 32-76 Revision 1 are required to be performed to 
ensure continued airworthiness of the aircraft.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    BAE Systems has issued British Aerospace Jetstream Series 3100 & 
3200 Service Bulletin 32-JA030644, dated October 6, 2003. APPH Ltd. has 
issued Service Bulletin 32-76, Revision 1, dated August 2003. 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 190 products of U.S. registry. We also estimate that 
it would take about 2 work-hours 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 $30,400, or $160 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours and require parts costing $5,300, for a cost of 
$5,940 per product. We have no way of determining the number of 
products that may need these actions.

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

[[Page 12135]]

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 removing Airworthiness Directive 
(AD) 2003-07-06, Amendment 39-13102 (68 FR 16195, April 3, 2003), and 
adding the following new AD:

British Aerospace Regional Aircraft: Docket No. FAA-2007-27213; 
Directorate Identifier 2007-CE-012-AD.

Comments Due Date

    (a) We must receive comments by April 16, 2007.

Affected ADs

    (b) Supersedes AD 2003-07-06, Amendment 39-13102.

Applicability

    (c) This AD applies to Model HP.137 Jetstream Mk.1, Jetstream 
Series 200, Jetstream Series 3101, and Jetstream Model 3201 
airplanes, all serial numbers, certificated in any category.

Subject

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

Reason

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

    Cracking has been found in the nose landing gear steering jack 
piston rod adjacent to the eye-end. This was caused by the 
application of excessive tightening torque applied to the eye-end 
whilst being assembled during component overhaul. Failure of the 
steering jack piston during operation will result in loss of nose 
wheel steering, which may lead to loss of directional control during 
critical phases of take-off and landing.

Retained Requirements of AD 2003-07-06

    (f) Unless already done, do the following actions in accordance 
with the procedures in APPH Ltd. Service Bulletin 32-76 (pages 1, 2, 
and 4 through 7, dated October 2002; and page 3, Erratum 1, dated 
November 2002), as referenced in BAe Systems British Aerospace 
Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: 
November 2, 2002; or APPH Ltd. Service Bulletin 32-76, Revision 1, 
dated August 2003, as referenced in BAe Systems British Aerospace 
Jetstream Mandatory Service Bulletin 32-JA030644, Original Issue: 
October 6, 2003.
    (1) Within the next 90 days or 200 ground-air-ground (GAG) 
cycles after May 22, 2003 (the effective date of AD 2003-07-06), 
whichever occurs first, inspect the steering jack piston rod for 
cracks.
    (2) If cracks are found, replace the cracked steering jack 
piston rod. Install the new steering jack piston rod using a torque 
setting of 175 lbf (pound force) inch or 20 Nm (Newton meters) when 
tightening the end fitting and stop bolt.
    (3) If no cracks are found, determine the torque setting of the 
steering jack piston rod end fitting and stop bolt.

New Requirements of This AD: Actions and Compliance

    (g) Unless already done, do the following actions:
    (1) Within 90 days after the effective date of this AD, 
recalculate the safe life of the steering jack piston rod and re-
torque the piston rod eye-end in accordance with APPH Ltd. Service 
Bulletin 32-76, Revision 1, dated August 2003, as referenced in 
paragraph 2, Part 2 of BAe Systems Service Bulletin 32-JA030644, 
dated October 6, 2003.
    (2) If the piston rod is found unserviceable when inspected in 
accordance with APPH Ltd. Service Bulletin 32-76, Revision 1, dated 
August 2003, as referenced in paragraph 2, Part 2 of BAe Systems 
Service Bulletin 32-JA030644, dated October 6, 2003, before further 
flight remove the steering jack and replace with a serviceable unit.
    (3) As of the effective date of this AD, before a steering jack 
piston rod is installed, it must be inspected and the safe life 
determined in accordance APPH Ltd. Service Bulletin 32-76, Revision 
1, dated August 2003, as referenced in paragraph 2 of BAe Systems 
Service Bulletin 32-JA030644, dated October 6, 2003.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Staff, FAA, Small Airplane Directorate, ATTN: Taylor 
Martin, Aerospace Engineer, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. 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) AMOCs approved for AD 2003-07-06 are not approved for this 
AD.
    (3) 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.
    (4) 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

    (i) Refer to MCAI Civil Aviation Authority AD No. G-2004-0029, 
dated December 20, 2004; BAE Systems British Aerospace Jetstream 
Series 3100 & 3200 Service Bulletin 32-JA030644, dated October 6, 
2003; BAe Systems British Aerospace Jetstream Mandatory Service 
Bulletin 32-JA020741, Original Issue: November 2, 2002; APPH Ltd. 
Service Bulletin 32-76, Revision 1, dated August 2003; and APPH Ltd. 
Service Bulletin 32-76 (pages 1, 2, and 4 through 7, dated October 
2002; and page 3, Erratum 1, dated November 2002, for related 
information.

    Issued in Kansas City, Missouri, on March 8, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-4739 Filed 3-14-07; 8:45 am]
BILLING CODE 4910-13-P

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