[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Proposed Rules]
[Pages 12133-12135]
From the Federal Register Online via the Government Publishing 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 http://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: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 http://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