[Federal Register Volume 63, Number 63 (Thursday, April 2, 1998)]
[Proposed Rules]
[Pages 16165-16167]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-8578]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-329-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Mark 0100 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Fokker Model F28 Mark 0100
series airplanes. This proposal would require interim inspections to
detect discrepancies of the main fitting subassembly of the main
landing gear, and follow-on corrective actions, if necessary. This
proposal would also require 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. This proposal is prompted by
issuance of mandatory continuing airworthiness information by a foreign
civil airworthiness authority. The actions specified by the proposed 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.
DATES: Comments must be received by May 4, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-329-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Fokker Services B.V., Technical Support Department, P.O.
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information
may be examined at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-329-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 97-NM-329-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Rijksluchtvaartdienst (RLD), which is the airworthiness
authority for the Netherlands, notified the FAA that an unsafe
condition may exist on certain Fokker Model F28 Mark 0100 series
airplanes. The RLD advises that an operator has reported in-service
cracking in the main fitting subassembly of the main landing gear. This
cracking resulted from corrosion at the side stay attachment fitting.
Investigation revealed that the corrosion initiated after the surface
protection was damaged during honing of the bushes. Such cracking, if
not corrected, could result in collapse of the main landing gear.
[[Page 16166]]
Explanation of Relevant Service Information
Messier-Dowty, the landing gear manufacturer, has issued Service
Bulletin F100-32-86, Revision 2, dated July 3, 1997, which describes
procedures for interim repetitive visual and eddy current inspections
to detect paint damage, corrosion, or cracking of the main fitting
subassembly of the main landing gear.
The service bulletin also describes procedures for a one-time
detailed visual and a one-time eddy current inspection to detect
discrepancies (paint damage, corrosion, or cracking) of the fitting;
repair of the fitting, if necessary; and application of new surface
protection on the fitting. Accomplishment of these actions would
eliminate the need for the interim repetitive inspections.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition. The RLD
classified this service bulletin as mandatory and issued Dutch
airworthiness directive 1996-133/2(A), dated January 31, 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 21.29) 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 Proposed 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, the proposed AD would require accomplishment of
the actions specified in the service bulletin described previously,
except as discussed below.
Difference Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
discrepancies where the repair cannot be accomplished within the limits
specified in the service bulletin, this proposal would require such
repairs to be accomplished in accordance with a method approved by the
FAA.
Differences Between Proposed Rule and Foreign AD
Operators should note that this AD proposes to mandate the
repetitive inspections described in Appendix B of Messier-Dowty Service
Bulletin F100-32-86 as interim action, prior to the accomplishment of
the terminating actions (detailed inspections, repair, and application
of surface protection) described in the Accomplishment Instructions of
the service bulletin. [Accomplishment of the interim inspections
specified in this service bulletin is optional in Dutch airworthiness
directive 1996-133/2(A).] The FAA has determined that mandating the
interim inspections will maintain continued operational safety while
allowing U.S. operators an opportunity to schedule the terminating
action.
Cost Impact
The FAA estimates that 127 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 2 work hours per airplane to accomplish
the proposed interim inspections. Based on an average labor rate of $60
per work hour, the cost impact of the proposed interim inspections on
U.S. operators is estimated to be $15,240, or $120 per airplane, per
inspection cycle.
It would take approximately 14 work hours per airplane to
accomplish the proposed terminating actions. Based on an average labor
rate of $60 per work hour, the cost impact of the proposed 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 proposed 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Fokker: Docket 97-NM-329-AD.
Applicability: Model F28 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; 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.
[[Page 16167]]
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
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. Accomplishment
of the actions required by this paragraph constitute 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.
(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.
(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.
Note 3: The subject of this AD is addressed in Dutch
airworthiness directive 1996-133/2(A), dated January 31, 1997.
Issued in Renton, Washington, on March 25, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-8578 Filed 4-1-98; 8:45 am]
BILLING CODE 4910-13-U
