[Federal Register Volume 74, Number 49 (Monday, March 16, 2009)]
[Rules and Regulations]
[Pages 11014-11017]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-5007]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0214; Directorate Identifier 2007-NM-343-AD; 
Amendment 39-15851; AD 2009-06-14]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.27 Mark 050 Airplanes

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

ACTION: Final rule; request for comments.

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[[Page 11015]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Fokker Model F.27 Mark 050 airplanes. This AD requires 
measuring the length of the extended portion of the sliding member of 
the main landing gear, performing an inspection for the presence of 
lockwiring, and doing corrective actions if necessary. This AD results 
from a report that the sliding member of the main landing gear has been 
overextended after landing. We are issuing this AD to detect and 
correct improper installation of the lockwire on the two lockbolts that 
hold the sliding member end stop, which could result in structural 
damage of the main gear and loss of control of the airplane during the 
landing roll, due to main landing gear overextension.

DATES: This AD becomes effective March 31, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 31, 
2009.
    We must receive comments on this AD by April 15, 2009.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Fokker 
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands; Telephone +31 (0)252-627-350; fax +31 (0)252-
627-211; e-mail <a href="/cdn-cgi/l/email-protection#394d5c5a5157505a58554a5c4b4f505a5c4a175f5652525c4b4a5c4b4f505a5c4a794a4d564b52175a5654"><span class="__cf_email__" data-cfemail="b8ccdddbd0d6d1dbd9d4cbddcaced1dbddcb96ded7d3d3ddcacbddcaced1dbddcbf8cbccd7cad396dbd7d5">[email protected]</span></a>; Internet 
http://www.myfokkerfleet.com.

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 this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The Civil Aviation Authority--The Netherlands (CAA-NL), which is 
the airworthiness authority for the Netherlands, notified us that an 
unsafe condition might exist on certain Fokker Model F.27 Mark 050 
airplanes. The CAA-NL advises that there has been a report that the 
sliding member of the main landing gear has been overextended after 
landing. During subsequent investigation, it was found that an end stop 
had unscrewed itself to a certain extent, and that there was no 
lockwiring present on the two lockbolts that hold the end stop. The 
unscrewed end stop caused the gear torque links of the main landing 
gear to come into an overextended position against the sliding member. 
This condition, if not corrected, could result in structural damage of 
the main gear and loss of control of the airplane during the landing 
roll, due to main landing gear overextension.

Relevant Service Information

    Fokker has issued Service Bulletin SBF50-32-039, dated July 2, 
2007, which describes procedures for measuring the length of the 
extended portion of the sliding member of the main landing gear, and 
performing an inspection for the presence of lockwiring on the lock 
bolts of the two end stops, and doing corrective actions if necessary. 
Corrective actions include applying lockwiring if not installed or 
installed incorrectly.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The CAA-NL 
mandated the service information and issued Dutch airworthiness 
directive NL-2007-002, dated October 31, 2007 (referred to after this 
as ``the MCAI''), to ensure the continued airworthiness of these 
airplanes in the Netherlands.
    Fokker Service Bulletin SBF50-32-039, dated July 2, 2007, refers to 
Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007, as an 
additional source of service information for measuring the length of 
the extended portion of the sliding member of the main landing gear, 
performing an inspection for the presence of lockwiring on the lock 
bolts of the two end stops, and installing new lockwiring when 
lockwiring is missing or installed incorrectly.

FAA's Determination and Requirements of This 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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    Therefore, we are issuing this AD to detect and correct improper 
installation of the lockwire on the two lockbolts that hold the sliding 
member end stop, which could result in structural damage of the main 
gear and loss of control of the airplane during the landing roll, due 
to main landing gear overextension. This AD requires accomplishing the 
actions specified in the service information described previously, 
except as discussed under ``Differences Between the AD and the MCAI.''

Differences Between the AD and the MCAI

    The MCAI specifies only to inspect for the presence of lockwiring 
if overextension is found. However, Messier-Dowty Service Bulletin F50-
32-62, dated January 17, 2007, also specifies to inspect if the 
measurement has increased between inspections. This AD requires 
inspection for the presence of lockwiring if overextension is found or 
the measurement of the repeat inspection has increased by 1.0 mm 
compared to a previous inspection. We have coordinated this difference 
with CAA-NL.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, the required actions would take about 8 work hours per 
airplane, at an average

[[Page 11016]]

labor rate of $80 per work hour. Required parts would cost about $1,082 
per airplane. Based on these figures, the estimated cost of the AD 
would be $1,722 per airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2009-0214; Directorate Identifier 2007-NM-343-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 have 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 that the 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 AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2009-06-14 Fokker Services B.V.: Amendment 39-15851. Docket No. FAA-
2009-0214; Directorate Identifier 2007-NM-343-AD.

Effective Date

    (a) This AD becomes effective March 31, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Fokker Model F.27 Mark 050 airplanes, 
certificated in any category.

Subject

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

Unsafe Condition

    (e) This AD results from a report that the sliding member of the 
main landing gear has been overextended after landing. We are 
issuing this AD to detect and correct improper installation of the 
lockwire on the two lockbolts that hold the sliding member end stop, 
which could result in structural damage of the main gear and loss of 
control of the airplane during the landing roll, due to main landing 
gear overextension.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Measurement, Inspection, and Corrective Actions

    (g) Within 500 flight cycles after the effective date of this 
AD, measure the length of the extended portion of the sliding member 
of the main landing gear in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF50-32-039, dated July 2, 
2007. Repeat the measurement at intervals not to exceed 500 flight 
cycles until the requirements of paragraph (g) have been completed.
    (h) At the applicable time in paragraph (h)(1) or (h)(2) of this 
AD, perform an inspection for the presence and correct installation 
of lockwiring on the two end stop lock bolts of the main landing 
gear, in accordance with the Accomplishment Instructions of Fokker 
Service Bulletin SBF50-32-039, dated July 2, 2007. If lockwiring is 
not present or is not installed correctly, install lockwiring before 
further flight in accordance with Fokker Service Bulletin SBF50-32-
039, dated July 2, 2007.
    (1) During any measurement required by paragraph (g) of this AD, 
if overextension is found, or the measurement has increased by 1.0 
millimeter (mm) or more compared to the previous measurement, 
inspect before further flight.
    (2) If no overextension is found and the measurement has not 
increased by 1.0 mm or more between measurements during the 
measurements required by paragraph (g) of this AD, inspect within 
4,000 flight hours after the effective date of this AD.

    Note 1: Fokker Service Bulletin SBF50-32-039, dated July 2, 
2007, refers to Messier-Dowty Service Bulletin F50-32-62, dated 
January 17, 2007, as an additional source of service information for 
measuring the length of the extended portion of the sliding member 
of the main landing gear, performing an inspection for the presence 
of lockwiring on the lock bolts of the two end stops, and installing 
new lockwiring.

    (i) If, during any measurement required by paragraph (g) of this 
AD, overextension is found or the measurement has increased by 1.0 
mm or more compared to the previous measurement; or if, during any 
inspection required by paragraph (h) of the AD, lockwiring is not 
present or is not installed correctly; submit a report to Fokker 
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE 
Nieuw-Vennep, the Netherlands; facsimile (31) 252-627-211; e-mail 
<a href="/cdn-cgi/l/email-protection#522637313a3c3b31333e213720243b3137217c343d39393720213720243b3137211221263d20397c313d3f"><span class="__cf_email__" data-cfemail="d4a0b1b7bcbabdb7b5b8a7b1a6a2bdb7b1a7fab2bbbfbfb1a6a7b1a6a2bdb7b1a794a7a0bba6bffab7bbb9">[email protected]</span></a>,

[[Page 11017]]

at the applicable time specified in paragraph (i)(1) or (i)(2) of 
this AD. The report must include any finding of overextension or 
incorrect lockwiring to Fokker Services B.V., Technical Services 
Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; 
facsimile (31) 252-627-211. 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 
contained in this AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection or measurement was done on or after the 
effective date of this AD: Submit the report within 30 days after 
the inspection or measurement, as applicable.
    (2) If the inspection or measurement was accomplished prior to 
the effective date of this AD: Submit the report within 30 days 
after the effective date of this AD.
    (j) As of 5 months after the effective date of this AD: No 
person may install a main landing gear on any airplane unless Part B 
of Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007, 
has been accomplished for that part.

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, International Branch, ANM-116, 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: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office.

Related Information

    (l) Civil Aviation Authority--The Netherlands (CAA-NL) 
Airworthiness Directive NL-2007-002, dated October 31, 2007, also 
addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use Fokker Service Bulletin SBF50-32-039, dated 
July 2, 2007; and Messier-Dowty Service Bulletin F50-32-62, dated 
January 17, 2007; as applicable; to perform the actions that are 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For Fokker service information identified in this AD, 
contact Fokker Services B.V., Technical Services Dept., P.O. Box 
231, 2150 AE Nieuw-Vennep, the Netherlands; Telephone +31 (0)252-
627-350; fax +31 (0)252-627-211; e-mail 
<a href="/cdn-cgi/l/email-protection#5f2b3a3c3731363c3e332c3a2d29363c3a2c71393034343a2d2c3a2d29363c3a2c1f2c2b302d34713c3032"><span class="__cf_email__" data-cfemail="067263656e686f65676a756374706f6563752860696d6d6374756374706f65637546757269746d2865696b">[email protected]</span></a>; Internet http://www.myfokkerfleet.com.
    (3) For Messier-Dowty service information identified in this AD, 
Messier-Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH, 
England; Telephone +44 (0) 1452 711732; fax +44 (0) 1452 713821.
    (4) You may review copies of this service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information that 
is incorporated by reference 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 Renton, Washington, on February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-5007 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P


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