Document ID: FAA-2008-0369-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200 and 3101, and Jetstream Model 3201 Airplanes
Posted Date: 2008-06-11T04:00Z

[Federal Register: June 11, 2008 (Volume 73, Number 113)]
[Rules and Regulations]               
[Page 32988-32990]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11jn08-3]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0369; Directorate Identifier 2008-CE-015-AD; 
Amendment 39-15545; AD 2008-12-02]
RIN 2120-AA64

 
Airworthiness Directives; British Aerospace Regional Aircraft 
Model HP.137 Jetstream Mk.1, Jetstream Series 200 and 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 adopting a new 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

[[Page 32989]]

product. The MCAI describes the unsafe condition as:

    A failure mode has been identified following the examination of 
parts from another aircraft type (Jetstream 4100 series) that can 
lead to the loss of a nose-wheel. The Jetstream (HP.137) Mk1, 200, 
3100 and 3200 series use a similar method for retaining the wheel 
assemblies on the landing gear axle and can therefore experience the 
same type of failure, i.e. a combination of excessive wear and/or 
adverse tolerances on the axle inner cone, outer cone or wheel hub 
splined sleeve cones resulting in the loss of the critical gap 
between the inner flange face of the wheel outer cone and the axle 
end face. If this gap is lost, it results in the wheel having free 
play along the length of the axle. This condition, if not corrected, 
can cause the wheel nut lock plate to break, leading to the wheel 
retention nut unscrewing and subsequent separation of the nose wheel 
from the landing gear axle.

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

DATES: This AD becomes effective July 16, 2008.
    On July 16, 2008, the Director of the Federal Register approved the 
incorporation by reference of certain publications listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at Document 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, 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 March 31, 2008 (73 
FR 16790). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A failure mode has been identified following the examination of 
parts from another aircraft type (Jetstream 4100 series) that can 
lead to the loss of a nose-wheel. The Jetstream (HP.137) Mk1, 200, 
3100 and 3200 series use a similar method for retaining the wheel 
assemblies on the landing gear axle and can therefore experience the 
same type of failure, i.e. a combination of excessive wear and/or 
adverse tolerances on the axle inner cone, outer cone or wheel hub 
splined sleeve cones resulting in the loss of the critical gap 
between the inner flange face of the wheel outer cone and the axle 
end face. If this gap is lost, it results in the wheel having free 
play along the length of the axle. This condition, if not corrected, 
can cause the wheel nut lock plate to break, leading to the wheel 
retention nut unscrewing and subsequent separation of the nose wheel 
from the landing gear axle.
    For the reasons described above, this AD requires repetitive 
inspections of the nose landing gear to ensure that the wheels are 
correctly retained and, depending on findings, replacement of worn 
parts.

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

Comments

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

Conclusion

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

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect 190 products of U.S. registry. We also estimate that it will 
take about 1 work-hour per product to comply with basic requirements of 
this AD. The average labor rate is $80 per work-hour.
    Based on these figures, we estimate the cost of this AD to the U.S. 
operators to be $15,200 or $80 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 1 work-hour and require parts costing $250, for a cost of 
$330 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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.

[[Page 32990]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-12-02 British Aerospace Regional Aircraft: Amendment 39-15545; 
Docket No. FAA-2008-0369; Directorate Identifier 2008-CE-015-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 16, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model HP.137 Jetstream Mk.1, Jetstream 
Series 200 and 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:
    A failure mode has been identified following the examination of 
parts from another aircraft type (Jetstream 4100 series) that can 
lead to the loss of a nose-wheel. The Jetstream (HP.137) Mk1, 200, 
3100 and 3200 series use a similar method for retaining the wheel 
assemblies on the landing gear axle and can therefore experience the 
same type of failure, i.e. a combination of excessive wear and/or 
adverse tolerances on the axle inner cone, outer cone or wheel hub 
splined sleeve cones resulting in the loss of the critical gap 
between the inner flange face of the wheel outer cone and the axle 
end face. If this gap is lost, it results in the wheel having free 
play along the length of the axle. This condition, if not corrected, 
can cause the wheel nut lock plate to break, leading to the wheel 
retention nut unscrewing and subsequent separation of the nose wheel 
from the landing gear axle.
    For the reasons described above, this AD requires repetitive 
inspections of the nose landing gear to ensure that the wheels are 
correctly retained and, depending on findings, replacement of worn 
parts.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 3 months after July 16, 2008 (the effective 
date of this AD), initially inspect the left and right nose wheel 
attachments to the axle following British Aerospace Jetstream Series 
3100 and 3200 Service Bulletin 32-JA070241, dated July 13, 2007.
    (2) Repetitively thereafter inspect the left and right nose 
wheel attachments to the axle at the intervals specified in Table 1 
of this AD following British Aerospace Jetstream Series 3100 and 
3200 Service Bulletin 32-JA070241, dated July 13, 2007. If during 
any repetitive inspection the gap measurement changes from the 
previous inspection measurement, adjust the repetitive inspection 
interval as necessary based on Table 1 of this AD.

                Table 1.--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                           Then repetitively inspect at
      If the measured gap size is:           the following intervals:
------------------------------------------------------------------------
0.002 through 0.005 inches (0.05         Within 500 hours time-in-
 through 0.13 mm).                        service (TIS).
More than 0.005 through 0.010 inches     Within 1,000 hours TIS.
 (0.13 through 0.25 mm).
More than 0.010 through 0.020 inches     Within 2,000 hours TIS.
 (0.25 through 0.51 mm).
More than 0.020 inches (0.51 mm).......  Within 3,000 hours TIS.
------------------------------------------------------------------------

    (3) Before further flight, if during any of the inspections 
required in paragraphs (f)(1) or (f)(2) of this AD you find the gap 
between the inner flange of the outer cone and the axle end face is 
less than 0.002 inches (0.05 mm), replace all worn parts.

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

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: 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: 
2008-0037, dated February 22, 2008; and British Aerospace Jetstream 
Series 3100 and 3200 Service Bulletin 32-JA070241, dated July 13, 
2007, for related information.

Material Incorporated by Reference

    (i) You must use British Aerospace Jetstream Series 3100 and 
3200 Service Bulletin 32-JA070241, dated July 13, 2007, to do the 
actions required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Project Management Group, Customer Information Department, BAE 
SYSTEMS (OPERATIONS), Prestwick International Airport, Ayrshire, KA9 
2RW, Scotland; telephone: +44 1292 675207; fax: +44 1292 675704; e-
mail: RApublications@baesystems.com.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106; or 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/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on May 28, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-12412 Filed 6-10-08; 8:45 am]

BILLING CODE 4910-13-P