[Federal Register Volume 64, Number 202 (Wednesday, October 20, 1999)]
[Rules and Regulations]
[Pages 56422-56424]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26933]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-225-AD; Amendment 39-11379; AD 99-21-33]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.27 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 certain Fokker Model F.27 Mark 050 series airplanes. This
action requires a one-time inspection to detect improper installation
of countersunk screws used to attach the access panels to the bottom
skin of the center wing; and corrective action, if necessary. 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 detect and correct such improper
installation, which could result in fatigue cracking of the bottom skin
of the center wing and consequent reduced structural integrity of the
airplane.
DATES: Effective November 4, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 4, 1999.
Comments for inclusion in the Rules Docket must be received on or
before November 19, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-225-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 certain Fokker Model F.27 Mark 050
series airplanes. The RLD advises that, on a number of airplanes on the
production line, the heads of countersunk screws were found not to seat
properly in their countersinkings. The affected screws are used in the
attachment of access panels of the bottom skin of the center wing. This
condition, if not corrected, could result in fatigue cracking of the
bottom skin of the center wing and consequent reduced structural
integrity of the airplane.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF50-57-015, dated February 28,
1996, which describes procedures for a one-time detailed visual
inspection to detect improper installation (excessive gap) of the
countersunk screws in the access covers of the bottom skin of the
center wing.
Fokker has also issued Service Bulletin SBF50-57-018, dated
February 28, 1996, which describes procedures
[[Page 56423]]
for reaming of the fastener holes and an eddy current inspection to
detect cracks in the bottom skin of the center wing. This service
bulletin also describes procedures to repair any cracking that is
found.
The RLD classified these service bulletins as mandatory and issued
Dutch airworthiness directive 1996-042 (A), dated April 29, 1996, in
order to assure the continued airworthiness of these airplanes in the
Netherlands.
FAA's Conclusions
This airplane model is manufactured in the Netherlands and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral 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 detect and correct
improper installation of countersunk screws in the attachment of access
panels of the bottom skin of the center wing, which could result in
fatigue cracking of the bottom skin and consequent reduced structural
integrity of the airplane. This AD requires accomplishment of the
actions specified in the service bulletins described previously.
Differences Between Rule and Service Bulletin
Operators should note that, although Fokker Service Bulletin SBF50-
57-018 specifies that the manufacturer may be contacted for disposition
of certain repair conditions, this AD would require the repair of those
conditions to be accomplished in accordance with a method approved by
the FAA.
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 6 work hours to
accomplish the required inspection, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of this AD would be
$360 per airplane.
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-225-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:
99-21-33 Fokker Services B.V.: Amendment 39-11379. Docket 99-NM-
225-AD.
Applicability: Model F.27 Mark 050 series airplanes, serial
numbers 20103 through 20263 inclusive; 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
[[Page 56424]]
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 (c) 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 detect and correct improper installation of countersunk
screws in the attachment of access panels of the bottom skin of the
center wing, which could result in fatigue cracking of the bottom
skin of the center wing and consequent reduced structural integrity
of the airplane, accomplish the following:
Initial Inspection
(a) Prior to the accumulation of 24,000 total flight cycles,
perform a one-time detailed visual inspection to detect improper
installation (excessive gap) of the countersunk screws used to
attach the access panels to the bottom skin of the center wing, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF50-57-015, dated February 28, 1996.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
Inspection and Corrective Action
(b) If any improper installation (excessive gap) is found during
the inspection required by paragraph (a) of this AD: Prior to the
accumulation of 24,000 total flight cycles, ream the fastener holes
in the rabbet of the bottom skin of the center wing and perform an
eddy current inspection for cracking of the fastener holes in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF50-57-018, dated February 28, 1996.
Repair
(1) For any fastener hole for which no crack is found during the
eddy current inspection: Prior to further flight; accomplish
corrective actions for the fastener hole, in accordance with Step C.
of Repair Scheme No. 1 of Fokker Service Bulletin SBF50-57-018,
dated February 28, 1996.
(2) For any fastener hole for which a crack is found during the
eddy current inspection: Prior to further flight; repair and re-
inspect the fastener hole, in accordance with Steps A. and B. of
Repair Scheme No. 1 of Fokker Service Bulletin SBF50-57-018, dated
February 28, 1996. For any crack that is outside the limits
specified in the service bulletin, prior to further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Rijksluchtvaartdienst (RLD) (or its delegated agent). For a
repair method to be approved by the Manager, International Branch,
ANM-116, as required by this paragraph, the Manager's approval
letter must specifically reference this AD.
Alternative Methods of Compliance
(c) 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 3: 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
(d) Special flight permits may be issued in accordance with
Secs. 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
(e) Except as provided by paragraph (b)(2) of this AD, the
actions shall be done in accordance with Fokker Service Bulletin
SBF50-57-015, dated February 28, 1996, and Fokker Service Bulletin
SBF50-57-018, dated February 28, 1996. 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 4: The subject of this AD is addressed in Dutch
airworthiness directive 1996-042 (A), dated April 29, 1996.
(f) This amendment becomes effective on November 4, 1999.
Issued in Renton, Washington, on October 8, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-26933 Filed 10-19-99; 8:45 am]
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