
[Federal Register: April 14, 2010 (Volume 75, Number 71)]
[Rules and Regulations]               
[Page 19209-19212]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ap10-8]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0056; Directorate Identifier 2009-CE-051-AD; 
Amendment 39-16259; AD 2010-08-04]
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: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This AD results from mandatory 
continuing airworthiness information (MCAI) issued 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:

    Cracks have been found in the NLG steering jack piston rod 
adjacent to the eye-end. This was caused by excessive torque which 
had been applied to the eye-end during assembly of the unit. Severe 
cracking, if not detected and corrected, can cause the jack to fail 
during operation, which may lead to loss of directional control of 
the aeroplane during critical phases of take-off and landing.


[[Page 19210]]


We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective May 19, 2010.
    On May 19, 2010, the Director of the Federal Register approved the 
incorporation by reference of British Aerospace Jetstream Series 3100 & 
3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated August 19, 
2008; British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 
No. 32-JM5414, dated August 6, 2004; and APPH Ltd. Bulletin 32-77, 
dated October 2003, listed in this AD.
    As of June 26, 2007 (72 FR 28587, May 22, 2007), the Director of 
the Federal Register approved the incorporation by reference of BAE 
Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 
32-JA030644, dated October 6, 2003; and APPH Ltd. Service Bulletin 32-
76, Revision 1, dated August 2003, listed in this AD.
    As of May 22, 2003 (68 FR 16195, April 3, 2003), the Director of 
the Federal Register approved the incorporation by reference of British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JA020741, dated November 2, 2002.

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

FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, ACE-112, Kansas 
City, Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090.

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 January 21, 2010 (75 
FR 3418), and proposed to supersede AD 2007-10-14, Amendment 39-15055 
(72 FR 28587, May 22, 2007). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states that:

    Cracks have been found in the NLG steering jack piston rod 
adjacent to the eye-end. This was caused by excessive torque which 
had been applied to the eye-end during assembly of the unit. Severe 
cracking, if not detected and corrected, can cause the jack to fail 
during operation, which may lead to loss of directional control of 
the aeroplane during critical phases of take-off and landing.
    To address this unsafe condition, the UK CAA issued AD 003-11-
2002 (which references BAE Systems Service Bulletin (SB) 32-
JA020741), requiring an inspection for cracks and a measurement of 
the release torque of the piston rod end fitting to determine a new 
safe life (remaining fatigue life) for individual units. The revised 
safe life was calculated in accordance with the formula provided in 
associated APPH Ltd (the NLG Jack manufacturer) SB 32-76.
    Following the completion of testing, APPH determined that the 
remaining fatigue life needed further reduction and 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 APPH SB 32-76 Revision 1. As a result, 
pistons which were previously calculated to have significant 
remaining life could possibly be unserviceable.
    In response to this development, BAE Systems issued SB 32-
JA030644 so that a revised calculation could be performed to 
establish the safe life of NLG steering jack pistons. Where not 
previously accomplished, the SB also recognised the need to inspect 
the piston for cracking and to measure the torque loading of the 
piston to eye-end joint so that safe life calculation could be 
performed. This SB superseded the earlier SB 32-JA020741 that 
produced an overly optimistic assessment of the component's safe 
life. The CAA UK issued AD G-2004-0029, superseding AD 003-11-2002, 
to require the accomplishment of these corrective actions.
    Subsequent to the original issue of BAE Systems SB 32-JA030644, 
APPH introduced a modified unit (optionally installed on aeroplanes 
by application of BAE Systems SB 32-JM5414) that incorporates a 
strengthened piston with a defined safe life. This safe life is not 
calculated in accordance with the instructions of BAE Systems SB 32-
JA030644, but is already declared in BAE Systems SB 32-JA981042, 
currently at revision 7. In response to requests for clarification, 
BAE Systems has revised SB 32-JA030644 to exclude those aeroplanes 
from the `Effectivity' that have the modified steering jack assembly 
installed in accordance with BAE modification JM5414.
    For the reasons described above, this new AD retains the 
requirements of UK CAA AD G-2004-0029, which is superseded, and 
confirms that for aeroplanes incorporating BAE modification JM5414, 
no further action is required.

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 FAA policies. Any such differences are 
highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 190 products of U.S. registry. 
We also estimate that it will take about 2 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour.
    Based on these figures, we estimate the cost of this AD to the U.S. 
operators to be $32,300, or $170 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.

[[Page 19211]]

    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 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 http://
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 the NPRM, 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.

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 removing Amendment 39-15055 (72 FR 
28587; May 22, 2007), and adding the following new AD:

2010-08-04 British Aerospace Regional Aircraft:Amendment 39-16259; 
Docket No. FAA-2010-0056; Directorate Identifier 2009-CE-051-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 19, 
2010.

Affected ADs

    (b) This AD supersedes AD 2007-10-14, Amendment 39-15055.

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, that are:
    (1) Equipped with steering jack part number (P/N) 6182-2, P/N 
6182-3, or P/N 6182-4; and
    (2) 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:
    Cracks have been found in the NLG steering jack piston rod 
adjacent to the eye-end. This was caused by excessive torque which 
had been applied to the eye-end during assembly of the unit. Severe 
cracking, if not detected and corrected, can cause the jack to fail 
during operation, which may lead to loss of directional control of 
the aeroplane during critical phases of take-off and landing.
    To address this unsafe condition, the UK CAA issued AD 003-11-
2002 (which references BAE Systems Service Bulletin (SB) 32-
JA020741), requiring an inspection for cracks and a measurement of 
the release torque of the piston rod end fitting to determine a new 
safe life (remaining fatigue life) for individual units. The revised 
safe life was calculated in accordance with the formula provided in 
associated APPH Ltd (the NLG Jack manufacturer) SB 32-76.
    Following the completion of testing, APPH determined that the 
remaining fatigue life needed further reduction and 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 APPH SB 32-76 Revision 1. As a result, 
pistons which were previously calculated to have significant 
remaining life could possibly be unserviceable.
    In response to this development, BAE Systems issued SB 32-
JA030644 so that a revised calculation could be performed to 
establish the safe life of NLG steering jack pistons. Where not 
previously accomplished, the SB also recognised the need to inspect 
the piston for cracking and to measure the torque loading of the 
piston to eye-end joint so that safe life calculation could be 
performed. This SB superseded the earlier SB 32-JA020741 that 
produced an overly optimistic assessment of the component's safe 
life. The CAA UK issued AD G-2004-0029, superseding AD 003-11-2002, 
to require the accomplishment of these corrective actions.
    Subsequent to the original issue of BAE Systems SB 32-JA030644, 
APPH introduced a modified unit (optionally installed on aeroplanes 
by application of BAE Systems SB 32-JM5414) that incorporates a 
strengthened piston with a defined safe life. This safe life is not 
calculated in accordance with the instructions of BAE Systems SB 32-
JA030644, but is already declared in BAE Systems SB 32-JA981042, 
currently at revision 7. In response to requests for clarification, 
BAE Systems has revised SB 32-JA030644 to exclude those aeroplanes 
from the `Effectivity' that have the modified steering jack assembly 
installed in accordance with BAE modification JM5414.
    For the reasons described above, this new AD retains the 
requirements of UK CAA AD G-2004-0029, which is superseded, and 
confirms that for aeroplanes incorporating BAE modification JM5414, 
no further action is required.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) For airplanes where the actions in British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA020741, dated 
November 2, 2002 (APPH Ltd. Service Bulletin 32-76, Revision 1, 
dated August 2003), have not already been done:
    (i) Within 2 months after June 26, 2007 (the effective date 
retained from AD 2007-10-14), inspect the steering jack piston rod, 
check the torque of the end fitting, and determine the safe life of 
the steering jack piston rod following BAE Systems British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin 32-JA030644, dated 
October 6, 2003. You may do the actions required in this paragraph 
following paragraph 2, Part 1 of British Aerospace Jetstream Series 
3100 & 3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated 
August 19, 2008, to comply with this AD.
    (ii) If the piston rod is found cracked or unserviceable during 
the inspection required in paragraph (f)(1)(i) of this AD, before 
further flight, remove the steering jack and replace it with a 
serviceable unit.
    (2) For airplanes where the actions in BAE British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA020741, dated 
November 2, 2002 (APPH Ltd. Service Bulletin 32-76, Revision 1, 
dated August 2003), have already been done:
    (i) Within 3 months after June 26, 2007 (the effective date 
retained from AD 2007-10-14), recalculate the safe life of the 
steering jack piston rod and re-torque the piston rod eye-end 
following BAE Systems British Aerospace Jetstream Series 3100 & 3200 
Service Bulletin 32-JA030644, dated October 6, 2003. You may do the 
actions required in this paragraph following paragraph 2, Part 2 of 
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 
32-JA030644, Revision No. 1, dated August 19, 2008, to comply with 
this AD.
    (ii) If the piston rod is found unserviceable during the 
inspection required in paragraph (f)(2)(i) of this AD, before 
further flight, remove the steering jack and replace it with a 
serviceable unit.
    (3) For airplanes equipped with steering jack part number (P/N) 
6182-2, P/N 6182-3, or P/N 6182-4 incorporating Strike-off 4, 
installed by BAE Systems modification JM5414 (refer to British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JM5414, dated August 6, 2004; and APPH Ltd. Bulletin 32-77, dated 
October 2003): the actions specified in paragraph (f)(1), (f)(1)(i), 
(f)(1)(ii), (f)(2), (f)(2)(i), or (f)(2)(ii) of this AD are not 
required.
    (4) For all airplanes: After June 26, 2007 (the effective date 
retained from AD 2007-10-14), do not install a steering jack piston 
rod with P/N 6182-2, P/N 6182-3, or P/N 6182-4, unless it has been 
inspected and the safe life recalculated following BAE Systems

[[Page 19212]]

British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-
JA030644, dated October 6, 2003. You may inspect and recalculate the 
safe life of the steering jack piston rod following paragraph 2 of 
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 
32-JA030644, Revision No. 1, dated August 19, 2008, to comply with 
this AD.

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 European Aviation Safety Agency (EASA) AD No.: 
2009-0135, dated June 23, 2009; British Aerospace Jetstream Series 
3100 & 3200 Service Bulletin No. 32-JA020741, dated November 2, 
2002; BAE Systems British Aerospace Jetstream Series 3100 & 3200 
Service Bulletin 32-JA030644, dated October 6, 2003; British 
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JA030644, Revision No. 1, dated August 19, 2008; British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JM5414, dated 
August 6, 2004; APPH Ltd. Service Bulletin 32-76, Revision 1, dated 
August 2003; and APPH Ltd. Service Bulletin 32-77, dated October 
2003, for related information.

Material Incorporated by Reference

    (i) You must use British Aerospace Jetstream Series 3100 & 3200 
Service Bulletin No. 32-JA020741, dated November 2, 2002; BAE 
Systems British Aerospace Jetstream Series 3100 & 3200 Service 
Bulletin 32-JA030644, dated October 6, 2003; British Aerospace 
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA030644, 
Revision No. 1, dated August 19, 2008; British Aerospace Jetstream 
Series 3100 & 3200 Service Bulletin No. 32-JM5414, dated August 6, 
2004; APPH Ltd. Service Bulletin 32-76, Revision 1, dated August 
2003; and APPH Ltd. Service Bulletin 32-77, dated October 2003, 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 British Aerospace Jetstream Series 
3100 & 3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated 
August 19, 2008; British Aerospace Jetstream Series 3100 & 3200 
Service Bulletin No. 32-JM5414, dated August 6, 2004; and APPH Ltd. 
Bulletin 32-77, dated October 2003, under 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) On June 26, 2007 (72 FR 28587, May 22, 2007), the Director 
of the Federal Register previously approved the incorporation by 
reference of BAE Systems British Aerospace Jetstream Series 3100 & 
3200 Service Bulletin 32-JA030644, dated October 6, 2003; and APPH 
Ltd. Service Bulletin 32-76, Revision 1, dated August 2003.
    (3) On May 22, 2003 (68 FR 16195, April 3, 2003), the Director 
of the Federal Register previously approved the incorporation by 
reference of British Aerospace Jetstream Series 3100 & 3200 Service 
Bulletin No. 32-JA020741, dated November 2, 2002.
    (4) For service information identified in this AD, contact BAE 
Systems (Operations) Ltd, Customer Information Department, Prestwick 
International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; 
Telephone +44 1292 675207, Facsimile +44 1292 675704; E-mail: 
RApublications@baesystems.com.
    (5) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (6) You may also review copies of the service information 
incorporated by reference for this AD 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: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Kansas City, Missouri, on March 31, 2010.
Steven R. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-7918 Filed 4-13-10; 8:45 am]
BILLING CODE 4910-13-P

