[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