[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34581-34583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16498]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-329-AD; Amendment 39-10623; AD 98-13-32]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0100 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Fokker Model F.28 Mark 0100 series airplanes,
that requires interim inspections to detect discrepancies of the main
fitting subassembly of the main landing gear, and follow-on corrective
actions, if necessary. This amendment also requires a one-time
inspection to detect discrepancies of the fitting, repair of the
fitting, if necessary, and application of new surface protection on the
fitting, which would terminate the interim inspections. This amendment
is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified by this AD are intended to prevent cracking of the main
fitting subassembly of the main landing gear, which could result in
collapse of the main landing gear.
[[Page 34582]]
DATES: Effective July 30, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 30, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Fokker Services B.V., Technical Support Department, P.O.
Box 75047, 1117 ZN Schiphol Airport, the Netherlands; or from Messier-
Dowty Ltd., Cage: K0654, Cheltenham Road, Gloucester, GL2 9QH, England.
This information may be examined at the Federal Aviation Administration
(FAA), Transport Airplane Directorate, Rules Docket, 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Fokker Model F.28 Mark
0100 series airplanes was published in the Federal Register on April 2,
1998 (63 FR 16165). That action proposed to require interim inspections
to detect discrepancies of the main fitting subassembly of the main
landing gear, and follow-on corrective actions, if necessary. That
action also proposed to require a one-time inspection to detect
discrepancies of the fitting, repair of the fitting, if necessary, and
application of new surface protection on the fitting. Accomplishment of
these actions would terminate the interim inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
Request to Cite Earlier Revision of Service Information
One commenter requests that provisions be added to allow
accomplishment of inspection and rework required by paragraph (b) of
the proposed AD in accordance with Revision 1 of Messier-Dowty Service
Bulletin F100-32-86 in addition to Revision 2, as proposed in the NPRM.
The FAA concurs. Since Revision 2 of the service bulletin contains no
substantive differences from Revision 1, the FAA has determined that
the actions required by paragraph (b) of this AD may be accomplished in
accordance with Messier-Dowty Service Bulletin F100-32-86, including
Appendix A and Appendix B; all Revision 1, all dated November 1, 1996.
A ``NOTE'' has been added to the final rule to give credit to operators
who may have previously accomplished the required actions in accordance
with the earlier revision of the service bulletin.
Explanation of Changes Made to Proposal
In the proposal, the FAA inadvertently omitted references to
Appendices A and B, both Revision 1, both dated November 1, 1996, of
Messier-Dowty Service Bulletin F100-32-86, Revision 2, dated July 3,
1997. Therefore, the FAA has revised the final rule accordingly.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 127 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 2 work hours per airplane to accomplish
the required interim inspections. Based on an average labor rate of $60
per work hour, the cost impact of the required interim inspections on
U.S. operators is estimated to be $15,240, or $120 per airplane, per
inspection cycle.
It will take approximately 14 work hours per airplane to accomplish
the required terminating actions. Based on an average labor rate of $60
per work hour the cost impact of the required terminating actions on
U.S. operators is estimated to be $106,680, or $840 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted.
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:
98-13-32 Fokker: Amendment 39-10623. Docket 97-NM-329-AD.
Applicability: Model F.28 Mark 0100 series airplanes, equipped
with Messier-Dowty main landing gear units having the part numbers
and serial numbers specified in Messier-Dowty Service Bulletin F100-
32-86, Revision 2, dated July 3, 1997, including Appendix A,
Revision 1, dated November 1, 1996, and Appendix B, Revision 1,
dated November 1, 1996; 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
[[Page 34583]]
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 prevent cracking of the main fitting subassembly of the main
landing gear, which could result in collapse of the main landing
gear, accomplish the following:
(a) Within 60 days after the effective date of this AD, perform
a visual and an eddy current inspection to detect discrepancies
(paint damage, corrosion or cracking) of the main fitting
subassembly of the main landing gear, in accordance with Appendix B,
Revision 1, dated November 1, 1996, of Messier-Dowty Service
Bulletin F100-32-86, Revision 2, dated July 3, 1997.
(1) If no discrepancy is detected, or if any discrepancy is
detected that is within the limits specified in Appendix B of the
service bulletin: Repeat the inspections required by paragraph (a)
of this AD thereafter at intervals not to exceed 60 days.
(2) If any discrepancy is detected that is outside the limits
specified in Appendix B of the service bulletin: Prior to further
flight, accomplish the requirements of paragraph (b) of this AD.
(b) Within 6 months after the effective date of this AD, perform
a one-time eddy current inspection and a one-time visual inspection
to detect discrepancies (paint damage, corrosion, or cracking) of
the main fitting subassembly of the main landing gear, in accordance
with the Accomplishment Instructions of Messier-Dowty Service
Bulletin F100-32-86, Revision 2, dated July 3, 1997, including
Appendix A, Revision 1, dated November 1, 1996, and Appendix B,
Revision 1, dated November 1, 1996. Accomplishment of the actions
required by this paragraph constitutes terminating action for the
requirements of this AD.
(1) If no discrepancy is detected, prior to further flight,
apply a protective treatment to the main fittings in accordance with
the service bulletin.
(2) If any discrepancy is detected that can be repaired within
the limits specified in the service bulletin, prior to further
flight, repair the discrepancy, and apply a protective treatment to
the main fittings, in accordance with the service bulletin.
(3) If any discrepancy is detected that cannot be repaired
within the limits specified in the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate.
Note 2: Accomplishment of the terminating actions required by
paragraph (b) of this AD in accordance with Messier-Dowty Service
Bulletin F100-32-86, including Appendix A and Appendix B; all
Revision 1, all dated November 1, 1996; prior to the effective date
of this AD, is acceptable for compliance with the requirements of
this paragraph.
(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 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.
(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.
(e) Except as provided by paragraph (b)(3) of this AD, the
actions shall be done in accordance with Messier-Dowty Service
Bulletin F100-32-86, Revision 2, dated July 3, 1997, including
Appendix A, Revision 1, dated November 1, 1996, and Appendix B,
Revision 1, dated November 1, 1996, which contains the following
list of effective pages:
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Revision
level
Page No. shown on Date shown on page
page
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1, 5, 6......................... 2 July 3, 1997.
2-4, 7-17....................... 1 November 1, 1996.
Appendix A
1-3............................. 1 November 1, 1996.
Appendix B
1-5............................. 1 November 1, 1996.
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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., Technical
Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the
Netherlands; or from Messier-Dowty Ltd., Cage: K0654, Cheltenham
Road, Gloucester, GL2 9QH, England. 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 1996-133/2(A), dated January 31, 1997.
(f) This amendment becomes effective on July 30, 1998.
Issued in Renton, Washington, on June 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-16498 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U
