[Federal Register Volume 65, Number 4 (Thursday, January 6, 2000)]
[Rules and Regulations]
[Pages 695-697]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-46]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-236-AD; Amendment 39-11494; AD 99-27-13]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 050 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Fokker Model F27 Mark 050 series airplanes. This 
action requires using a torque wrench to repetitively tighten the 
screws for the attachment of the leading edges of the elevators, 
rudder, and ailerons. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified in this AD are intended 
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.

DATES: Effective January 21, 2000.

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 21, 2000.

    Comments for inclusion in the Rules Docket must be received on or 
before February 7, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-236-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.

    The service information referenced in this AD may be obtained from 
Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, The 
Netherlands. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Rijksluchtvaartdienst (RLD), which is 
the airworthiness authority for the Netherlands, notified the FAA that 
an unsafe condition may exist on all Fokker Model F27 Mark 050 series 
airplanes. The RLD advises that, after an airplane landed, the elevator 
control was found binding in the fully ``UP'' position. Subsequent 
investigation of the elevator revealed that an attachment screw had 
come loose and moved out of the elevator leading edge section against 
the horizontal stabilizer. The leading edges of the elevators are 
attached by screws in anchor nuts on the elevator front spar. The 
screws are thought to have come loose due to vibration. The subject 
screws on the leading edge of the rudder and ailerons are identical to 
those on the affected elevators.

    Loose attachment screws on the leading edges of the elevators, 
rudder, or ailerons, if not corrected, could result in interference of 
the leading edges with adjacent structure and consequent reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    Fokker has issued Service Bulletin SBF50-55-007, dated June 5, 
1998, which describes procedures for using a torque wrench to 
repetitively tighten the screws for the attachment of the leading edges 
of the elevator.

    Fokker also has issued Service Bulletin SBF50-57-020, Revision 1, 
dated July 23, 1999, which describes procedures for using a torque 
wrench to repetitively tighten the screws for the attachment of the 
leading edges of the aileron.

    In addition, Fokker has issued Service Bulletin SBF50-55-009, 
Revision 1, dated July 23, 1999, which describes procedures for using a 
torque wrench to repetitively tighten the screws for the attachment of 
the leading edges of the rudder.

    The RLD classified these service bulletins as mandatory and issued 
Dutch airworthiness directive 1998-070/3, dated August 31, 1999, in 
order to assure the continued airworthiness of these airplanes in the 
Netherlands.

FAA's Conclusions

    These airplane models are manufactured in the Netherlands and are 
type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.19) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral

[[Page 696]]

airworthiness agreement, the RLD has kept the FAA informed of the 
situation described above. The FAA has examined the findings of the 
RLD, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD is being issued 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. This AD requires accomplishment of the actions specified in 
the service bulletins described previously.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.

    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 12 work hours to 
accomplish the required tightening, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$720 per airplane, per inspection cycle.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register. 

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.

    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.

    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-236-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.

    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

99-27-13  Fokker Services B.V.: Amendment 39-11494. Docket 99-NM-
236-AD.

    Applicability: All Model F27 Mark 050 series airplanes, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loose attachment screws on the leading edges of the 
elevators, rudder, and ailerons due to vibration, which could result 
in interference of the leading edges with adjacent structure and 
consequent reduced controllability of the airplane; accomplish the 
following:

Repetitive Corrective Action

    (a) Within 30 days after the effective date of this AD, 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. Repeat the tightening 
thereafter at intervals not to exceed 12 months.
    (b) Within 24 months after the effective date of this AD, 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. Repeat the 
tightening thereafter at intervals not to

[[Page 697]]

exceed 4,000 flight hours or 24 months, whichever occurs first.
    (c) Within 6 months after the effective date of this AD, 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. Repeat the 
tightening thereafter at intervals not to exceed 12 months.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (f) The actions shall be done in accordance with the following 
Fokker service bulletins, which contain the specified effective 
pages:

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                                                        Revision level shown
Service bulletin referenced and date      Page No.             on page                 Date shown on page
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SBF50-55-007, June 5, 1998..........  1-5............  Original..............  June 5, 1998.
SBF50-55-009, Revision 1, July 23,    1-4, 7, 5, 6...  1, Original...........  July 23, 1999, April 23, 1999.
 1999.
SBF50-57-020, Revision 1, July 23,    1-4, 6, 5, 7...  1, Original...........  July 23, 1999, April 23, 1999.
 1999.
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Fokker Services B.V., P.O. Box 231, 
2150 AE Nieuw-Vennep, The Netherlands. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in Dutch 
airworthiness directive 1998-070/3, dated August 31, 1999.

    (g) This amendment becomes effective on January 21, 2000.

    Issued in Renton, Washington, on December 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-46 Filed 1-5-00; 8:45 am]
BILLING CODE 4910-13-U