[Federal Register Volume 64, Number 168 (Tuesday, August 31, 1999)]
[Rules and Regulations]
[Pages 47382-47384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-22392]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-224-AD; Amendment 39-11278; AD 99-18-12]
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 a one-time inspection to detect cracking of the
fuselage between stations 15375 and 16275, at the skin splice above the
cabin windows; 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 cracking, which could
result in depressurization of the cabin and reduced structural
integrity of the airplane fuselage.
DATES: Effective September 15, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 15, 1999.
Comments for inclusion in the Rules Docket must be received on or
before September 30, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-224-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 a report was received of a crack that
had been discovered on the left-hand side of the fuselage between
stations 15375 and 16275, at the skin splice above the cabin windows.
Subsequent investigation of the skin splice revealed that the crack had
initiated at a scratch in the bonded doubler at the edge of the lower
skin. Fatigue caused the crack to grow to 21.3 inches (540 mm)
undetected, until the skin splice opened, due to overload. This
resulted in pressurization problems during climb of the airplane,
leading to the detection of the crack. This condition, if not
corrected, could result in depressurization of the cabin and reduced
structural integrity of the airplane fuselage.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF50-53-053, dated February 1,
1997, which describes procedures for a one-time eddy current inspection
to detect cracking of the fuselage between stations 15375 and 16275, at
the skin splice above the cabin windows. The RLD classified this
service bulletin as mandatory and issued Dutch airworthiness directive
1997-022 (A), dated February 28, 1997, 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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and
the
[[Page 47383]]
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
cracking of the fuselage between stations 15375 and 16275, at the skin
splice above the cabin windows, and corrective action, if necessary.
This AD requires accomplishment of the actions specified in the service
bulletin described previously, except as discussed below.
Differences Between Proposed Rule and Service Information/Dutch
Airworthiness Directive
Operators should note that, although the service bulletin and Dutch
airworthiness directive specify that the manufacturer may be contacted
for disposition of certain repair conditions, this proposal 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 2 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
$120 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-224-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:
99-18-12 Fokker Services B.V.: Amendment 39-11278. Docket 99-NM-224-
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 (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 cracking of the fuselage between stations 15375 and
16275, at the skin splice above the cabin windows, which could
result in depressurization of the cabin and reduced structural
integrity of the airplane fuselage, accomplish the following:
(a) Prior to the accumulation of 10,000 total flight cycles, or
within 6 months after the effective date of this AD, whichever
occurs later, perform a one-time eddy current inspection to detect
cracking of the fuselage
[[Page 47384]]
between stations 15375 and 16275, at the skin splice above the cabin
windows, in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF50-53-053, dated February 1, 1997.
(b) If any crack is found during the inspection required by
paragraph (a) of this AD: Prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate. 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.
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
(d) 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
(e) Except as provided by paragraph (b) of this AD, the actions
shall be done in accordance with Fokker Service Bulletin SBF50-53-
053, dated February 1, 1997. 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 1997-022 (A), dated February 28, 1997.
(f) This amendment becomes effective on September 15, 1999.
Issued in Renton, Washington, on August 23, 1999.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-22392 Filed 8-30-99; 8:45 am]
BILLING CODE 4910-13-U
