[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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:
----------------------------------------------------------------------------------------------------------------
Revision level shown
Service bulletin referenced and date Page No. on page Date shown on page
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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
