[Federal Register Volume 70, Number 237 (Monday, December 12, 2005)]
[Rules and Regulations]
[Pages 73347-73351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23779]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23214; Directorate Identifier 2001-NM-338-AD; 
Amendment 39-14399; AD 2005-25-06]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Fokker Model F27 Mark 050 series airplanes. 
The existing AD currently requires using a torque wrench to 
repetitively tighten the screws for the attachment of the leading edges 
of the elevators, rudder, and ailerons. This new AD requires the same 
actions as those of the existing AD, but with reductions in the 
intervals for repetitive actions. This AD also requires modifying the 
elevator, rudder, and aileron leading edge attachments with additional 
locking devices. This AD results from a report of an in-flight 
vibration caused by a loose leading edge section of the elevator. We 
are issuing this AD to prevent binding of the flight controls caused by 
loose attachment screws, which could result in reduced controllability 
of the airplane.

DATES: This AD becomes effective December 27, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 27, 
2005.
    On January 21, 2000 (65 FR 695, January 6, 2000), the Director of 
the Federal Register approved the incorporation by reference of certain 
other publications listed in the regulations.
    We must receive comments on this AD by February 10, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.

[[Page 73348]]

     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9:00 
a.m. and 5:00 p.m., Monday through Friday, except Federal holidays.
    Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, 
the Netherlands, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On December 28, 1999, we issued AD 99-27-13, amendment 39-11494 (65 
FR 695, January 6, 2000), for all Fokker Model F27 Mark 050 series 
airplanes. That AD requires using a torque wrench to repetitively 
tighten the screws for the attachment of the leading edges of the 
elevators, rudder, and ailerons. That AD resulted from an issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. We issued that AD to prevent loose attachment 
screws on the leading edges of the elevators, rudder, and ailerons due 
to vibration, which could result in interference with adjacent 
structure and consequent reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 99-27-13, the Civil Aviation Authority--The 
Netherlands (CAA-NL), which is the airworthiness authority for the 
Netherlands, notified us that an additional further unsafe condition 
may exist on all Fokker Model F27 Mark 050 airplanes. The CAA-NL 
advises that an operator reported in-flight vibration, which was caused 
by one loose elevator leading edge section. The airplane was found to 
have been inspected only seven months before the incident, which was 
within the original 12-month inspection interval of the existing AD. 
Further investigation by the manufacturer showed that the self-locking 
properties of the attachment screws gradually decrease when tightened 
repeatedly as required by the procedures in the existing AD. This 
condition, if not corrected, could result in binding of the flight 
controls caused by loose attachment screws, which could cause reduced 
controllability of the airplane.

Relevant Service Information

    Fokker Services B.V. has issued bulletins in the following table.

                        Fokker Service Bulletins
------------------------------------------------------------------------
  Fokker Services Bulletin--           Describes procedures for--
------------------------------------------------------------------------
SBF50-55-007, Revision 2,      Tightening the attachment screws of the
 dated June 17, 2002.           elevators' leading edges.
SBF50-55-008, Revision 3,      Modifying the elevator attachments by
 dated June 17, 2002.           installing additional locking devices
                                for the elevators' leading edges.
SBF50-55-009, Revision 2,      Tightening the attachment screws for the
 dated June 17, 2002.           rudder's leading edge.
SBF50-55-010, Revision 2,      Modifying the rudder attachments by
 dated June 17, 2002.           installing additional locking devices
                                for the rudder's leading edge.
SBF50-57-020, Revision 2,      Tightening the attachment screws for the
 dated June 17, 2002.           ailerons' leading edges.
SBF50-57-021, Revision 2,      Modifying the aileron attachments by
 dated June 17, 2002.           installing additional locking devices
                                for the ailerons' leading edges.
------------------------------------------------------------------------

    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 2000-131/2, dated July 31, 2002, to ensure the continued 
airworthiness of these airplanes in the Netherlands.
    Fokker Service Bulletin SBF50-55-010, Revision 2, refers to Fokker 
Service Bulletin SBF50-55-011, dated October 29, 2001, as an additional 
source of service information for modifying the rudder attachments.
    Fokker Service Bulletin SBF50-57-021, Revision 2, refers to Fokker 
Service Bulletin SBF50-57-025, dated October 29, 2001, as an additional 
source of service information for modifying the aileron attachments.

FAA's Determination and Requirements of this AD

    This airplane model is manufactured in the Netherlands and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the CAA-NL has kept the FAA informed 
of the situation described above. We have examined the CAA-NL's 
findings, evaluated all pertinent information, and determined that we 
need to issue an AD for products of this type design that are 
certificated for operation in the United States.
    Therefore, we are issuing this AD to prevent binding of the flight 
controls caused by loose attachment screws, which could result in 
reduced controllability of the airplane. This AD requires accomplishing 
the actions specified in the service information described previously.
    This AD supersedes AD 99-27-13. This AD continues to require the 
same actions as the existing AD, but at reduced repetitive intervals. 
This AD also requires a new modification for the elevators, rudder, and 
aileron attachments, which terminates the repetitive inspection 
requirements of this AD. This AD requires accomplishing the actions 
specified in the service bulletins described previously.

Change To Existing AD

    This AD will retain all requirements of AD 99-27-13. Since AD 99-
27-13 was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers

[[Page 73349]]

have changed in this AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                            Corresponding requirement in
        Requirement in AD 99-27-13                this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
------------------------------------------------------------------------

Explanation of Change to Applicability

    We have revised the applicability of the proposed AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

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.
    The following table provides the estimated costs to comply with 
this AD for any affected airplane that might be imported and placed on 
the U.S. Register in the future.

                                                                     Estimated Costs
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                                          Work     Average labor
                Action                    hours    rate per hour                  Parts cost                               Cost per airplane
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Tightening (required by AD 99-27-13)..        12             $65  None......................................  $780, per inspection cycle
Modification (new action).............        37              65  $1,025 to 3,372...........................  $3,430 to 5,777
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23214; Directorate Identifier 2001-NM-338-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    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 with FAA 
personnel concerning this AD. Using the search function of that web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

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 
removing amendment 39-11494 (65 FR 695, January 6, 2000) and by adding 
the following new airworthiness directive (AD):


[[Page 73350]]


2005-25-06 Fokker Services B.V.: Amendment 39-14399. Docket No. FAA-
2005-23214; Directorate Identifier 2001-NM-338-AD.

Effective Date

    (a) This AD becomes effective December 27, 2005.

Affected ADs

    (b) This AD supersedes AD 99-27-13.

Applicability

    (c) This AD applies to all Fokker Model F27 Mark 050 airplanes, 
certificated in any category.

Unsafe Condition

    (d) This AD results from a report of an in-flight vibration 
caused by a loose leading edge section of the elevator. We are 
issuing this AD to prevent binding of the flight controls caused by 
loose attachment screws, which could result in reduced 
controllability of the airplane.

Compliance

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

Restatement of the Requirements of AD 99-27-13

Repetitive Corrective Action

    (f) Within 30 days after January 21, 2000 (the effective date of 
AD 99-27-13), use a torque wrench to tighten the screws for the 
attachment of the leading edges of the elevators in accordance with 
Fokker Service Bulletin SBF50-55-007, dated June 5, 1998; or 
Revision 2, dated June 17, 2002. After the effective date of this 
AD, only Revision 2 may be used. Repeat the tightening thereafter at 
intervals not to exceed 12 months until the initial tightening 
required by paragraph (i) of this AD is accomplished.
    (g) Within 24 months after January 21, 2000, use a torque wrench 
to tighten the screws for the attachment of the leading edges of the 
rudder in accordance with Fokker Service Bulletin SBF50-55-009, 
Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. 
After the effective date of this AD, only Revision 2 may be used. 
Repeat the tightening thereafter at intervals not to exceed 4,000 
flight hours, or 24 months, whichever occurs first, until the 
initial tightening required by paragraph (j) of this AD is 
accomplished.
    (h) Within 6 months after January 21, 2000, use a torque wrench 
to tighten the screws for the attachment of the leading edges of the 
ailerons in accordance with Fokker Service Bulletin SBF50-57-020, 
Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. 
After the effective date of this AD, only Revision 2 may be used. 
Repeat the tightening thereafter at intervals not to exceed 12 
months until the initial tightening required by paragraph (k) of 
this AD is accomplished.

New Requirements of This AD

New Repetitive Intervals

    (i) Within 6 months after the effective date of this AD or 12 
months after accomplishing the action in paragraph (f) of this AD, 
whichever occurs earlier: Use a torque wrench to tighten the screws 
for the attachment of the leading edges of the elevators in 
accordance with Fokker Service Bulletin SBF50-55-007, Revision 2, 
dated June 17, 2002. Repeat the tightening thereafter at intervals 
not to exceed 6 months until the modification required by paragraph 
(l) of this AD is accomplished. Doing the actions in this paragraph 
terminates the repetitive actions of paragraph (f) of this AD.
    (j) Within 12 months after the effective date of this AD or 24 
months after accomplishing the action in paragraph (g) of this AD, 
whichever occurs earlier: Use a torque wrench to tighten the screws 
for the attachment of the leading edge of the rudder in accordance 
with Fokker Service Bulletin SBF50-55-009, Revision 2, dated June 
17, 2002. Repeat the tightening thereafter at intervals not to 
exceed 12 months until the modification required by paragraph (l) of 
this AD is accomplished. Doing the actions in this paragraph 
terminates the repetitive actions of paragraph (g) of this AD.
    (k) Within 6 months after the effective date of this AD or 6 
months after accomplishing the action in paragraph (h) of this AD, 
whichever occurs earlier: Use a torque wrench to tighten the screws 
for the attachment of the leading edges of the ailerons in 
accordance with Fokker Service Bulletin SBF50-57-020, Revision 2, 
dated June 17, 2002. Repeat the tightening thereafter at intervals 
not to exceed 6 months until the modification required by paragraph 
(l) of this AD is accomplished. Doing the actions in this paragraph 
terminates the repetitive actions of paragraph (h) of this AD.

Terminating Modification

    (l) At the earlier of the times in paragraph (l)(1) and (l)(2) 
of this AD, modify the elevator, rudder, and aileron leading edge 
attachments by installing additional locking devices in accordance 
with the Accomplishment Instructions of the service bulletins in 
Table 1 of this AD. Doing the modifications terminates the 
applicable repetitive actions in paragraphs (f), (g), (h), (i), (j), 
and (k) of this AD, as specified in Table 1.
    (1) Within 24 months after the effective date of this AD.
    (2) Within 180 months since the date of issuance of the original 
Airworthiness Certificate or the date of issuance of the original 
Export Certificate of Airworthiness.

                         Table 1.--Fokker Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                                                             Terminates the actions  required in
      Fokker service bulletin                      Location                              paragraph--
----------------------------------------------------------------------------------------------------------------
SBF50-55-008, Revision 3, dated     Elevator leading edge.................  (f) and (i).
 June 17, 2002.
SBF50-55-010, Revision 2, dated     Rudder leading edge...................  (g) and (j).
 June 17, 2002.
SBF50-57-021, Revision 2, dated     Aileron leading edge..................  (h) and (k).
 June 17, 2002.
----------------------------------------------------------------------------------------------------------------


    Note 1: Fokker Service Bulletin SBF50-55-010, Revision 2, refers 
to Fokker Service Bulletin SBF50-55-011, dated October 29, 2001, as 
an additional source of service information for modifying the rudder 
attachments. Fokker Service Bulletin SBF50-57-021, Revision 2, 
refers to Fokker Service Bulletin SBF50-57-025, dated October 29, 
2001, as an additional source of service information for modifying 
the aileron attachments.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, ANM-116, International Branch, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (n) Dutch airworthiness directive 2000-131/2, dated July 31, 
2002, also addresses the subject of this AD.

Material Incorporated by Reference

    (o) You must use the service information that is specified in 
Table 2 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise.

                                Table 2.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Fokker service bulletin                    Revision level                          Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007.............................  Original.......................  June 5, 1998.

[[Page 73351]]

 
SBF50-55-007.............................  2..............................  June 17, 2002.
SBF50-55-008.............................  3..............................  June 17, 2002.
SBF50-55-009.............................  1..............................  July 23, 1999.
SBF50-55-009.............................  2..............................  June 17, 2002.
SBF50-55-010.............................  2..............................  June 17, 2002.
SBF50-57-020.............................  1..............................  July 23, 1999.
SBF50-57-020.............................  2..............................  June 17, 2002.
SBF50-57-021.............................  2..............................  June 17, 2002.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of the service bulletins in 
Table 3 of this AD is approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                                Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Fokker service bulletin                    Revision level                          Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007.............................  Revision 2.....................  June 17, 2002.
SBF50-55-008.............................  Revision 3.....................  June 17, 2002.
SBF50-55-009.............................  Revision 2.....................  June 17, 2002.
SBF50-55-010.............................  Revision 2.....................  June 17, 2002.
SBF50-57-020.............................  Revision 2.....................  June 17, 2002.
SBF50-57-021.............................  Revision 2.....................  June 17, 2002.
----------------------------------------------------------------------------------------------------------------

    (2) The incorporation by reference of the service bulletins in 
Table 4 of this AD was approved previously by the Director of the 
Federal Register as of January 21, 2000, (65 FR 695, January 6, 
2000).

                             Table 4.--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Fokker service bulletin                    Revision level                          Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007.............................  Original.......................  June 5, 1998.
SBF50-55-009.............................  Revision 1.....................  July 23, 1999.
SBF50-57-020.............................  Revision 1.....................  July 23, 1999.
----------------------------------------------------------------------------------------------------------------

    (3) Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands, for copies of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the 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 November 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23779 Filed 12-9-05; 8:45 am]
BILLING CODE 4910-13-P