[Federal Register Volume 65, Number 51 (Wednesday, March 15, 2000)]
[Proposed Rules]
[Pages 13923-13926]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6331]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-02-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0100 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Fokker Model F.28 
Mark 0100 series airplanes, that currently requires a one-time visual 
inspection and a one-time eddy current and/or dye penetrant inspection 
of the nose landing gear (NLG) main fitting to detect cracking; and 
rework of the NLG main fitting, if necessary. This action would require 
new inspections (one-time detailed visual inspection and repetitive 
eddy current or dye penetrant inspections) to detect cracking of the 
NLG main fitting subassembly, and corrective actions, if necessary. 
This action also would revise the applicability of the existing AD. 
This proposal is prompted by the 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 NLG main fitting, which could lead to collapse of the 
NLG during takeoff and landing, and possible injury to the flightcrew 
and passengers.

DATES: Comments must be received by April 14, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-02-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

[[Page 13924]]

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.

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 2000-NM-02-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. 2000-NM-02-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On October 13, 1998, the FAA issued AD 98-22-01, amendment 39-10847 
(63 FR 58625, November 2, 1998), applicable to certain Fokker Model 
F.28 Mark 0100 series airplanes, to require a one-time visual 
inspection and a one-time eddy current and/or dye penetrant inspection 
of the nose landing gear (NLG) main fitting to detect cracking; and 
rework of the NLG main fitting, if necessary. That action was prompted 
by issuance of mandatory continuing airworthiness information by a 
foreign civil airworthiness authority. The requirements of that AD are 
intended to prevent cracking of the NLG main fitting, which could lead 
to collapse of the NLG during takeoff and landing, and possible injury 
to the flightcrew and passengers.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the Rijksluchtvaartdienst (RLD), 
which is the airworthiness authority for the Netherlands, has advised 
the FAA that, during maintenance, several additional occurrences of 
cracking of the main fitting subassembly (MFSA) of the downlock plunger 
support webs of the NLG were found. The cracks initiated on the inner 
side of both the left-hand and right-hand support webs of the downlock 
plunger. In light of the recent events, the manufacturer has released 
new service information and the FAA has determined that it is necessary 
to perform a new, one-time detailed visual inspection and repetitive 
eddy current or dye penetrant inspections to enable early detection of 
cracking in the affected area.

Issuance of New Service Information

    The manufacturer has issued Fokker Service Bulletin SBF100-32-118, 
dated October 8, 1999, which describes procedures for a one-time 
detailed visual inspection and repetitive eddy current or dye penetrant 
inspections of the NLG main fitting subassembly to detect cracking, and 
rework of the main fitting, if necessary. 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 BLA 1997-116/2 
(A), dated October 29, 1999, in order to assure the continued 
airworthiness of these airplanes in the Netherlands.
    The Fokker service bulletin references Messier-Dowty Service 
Bulletin F100-32-92, Revision 1, dated October 8, 1999, as an 
additional source of service information for accomplishing the 
inspections and rework of the NLG main fitting subassembly.

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 21.29) 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 supersede the requirements 
of AD 98-22-01. This proposed AD would require a new, one-time detailed 
visual inspection, and a new eddy current or dye penetrant inspection 
to be accomplished repetitively. This proposed AD would revise the 
applicability of the existing AD to include airplanes on which a 
certain main fitting subassembly is installed. The actions would be 
required to be accomplished in accordance with the Fokker service 
bulletin described previously, except as described below. The proposed 
AD also would require that operators report all findings of the one-
time detailed visual inspection and the initial eddy current or dye 
penetrant inspection to Fokker Services.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the Fokker service bulletin 
specifies that the manufacturer may be contacted for disposition of 
certain cracking conditions, this proposal would require the repair of 
those conditions to be accomplished in accordance with a method 
approved by either the FAA, or the RLD (or its delegated agent). In 
light of the type of repair that would be required to address the 
identified unsafe condition, and in consonance with existing bilateral 
airworthiness agreements, the FAA has determined that, for this 
proposed AD, a repair approved by either the FAA or the RLD would be 
acceptable for compliance with this proposed AD.

Cost Impact

    There are approximately 87 airplanes of U.S. registry that would be 
affected by this proposed AD.
    The one-time detailed visual inspection proposed by this AD action 
would take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact

[[Page 13925]]

of the one-time inspection proposed by this AD on U.S. operators is 
estimated to be $5,220, or $60 per airplane.
    The repetitive eddy current or dye penetrant inspections proposed 
by this AD action would take approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the repetitive inspection proposed by 
this AD on U.S. operators is estimated to be $5,220, or $60 per 
airplane, per inspection cycle.
    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 a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 removing amendment 39-10847 (63 FR 
58625, November 2, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Fokker Services B.V.: Docket 2000-NM-02-AD. Supersedes AD 98-22-01, 
Amendment 39-10847.

    Applicability: Model F.28 Mark 0100 series airplanes, 
certificated in any category; equipped with Messier-Dowty nose 
landing gear (NLG) having part number (P/N) 201071001 or 201071002, 
on which a main fitting subassembly (MFSA) having P/N 201071200, 
201071228, 201071248, or 201071249 is installed.

    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 (f) 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 NLG main fitting, which could lead to 
collapse of the NLG during takeoff and landing, and possible injury 
to the flightcrew and passengers, accomplish the following:

One-time Detailed Visual Inspection

    (a) Prior to the accumulation of 7,500 total flight cycles or 
within 50 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a one-time detailed visual 
inspection of the NLG main fitting subassembly to detect cracking, 
in accordance with Part 1 of the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-32-118, dated October 8, 1999.
    (1) If no cracking is detected, no further action is required by 
this paragraph.
    (2) If any cracking is detected, prior to further flight, 
accomplish the actions required by paragraph (b) of this AD.

    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 mirrors, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Actions accomplished prior to the effective date of this 
AD, in accordance with Fokker Service Bulletin SBF100-32-112, dated 
November 14, 1997, which was cited in AD 98-22-01, amendment 39-
10847, are not considered acceptable for compliance with any 
requirements of this AD.

Repetitive Eddy Current and/or Dye Penetrant Inspections

    (b) Except as required by paragraph (a)(2) of this AD: Prior to 
the accumulation of 7,875 total flight cycles or within 375 flight 
cycles after the effective date of this AD, whichever occurs later, 
perform an eddy current or dye penetrant inspection of the NLG main 
fitting subassembly to detect cracking, in accordance with Part 2 of 
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
32-118, dated October 8, 1999. Such inspection within the compliance 
time required by paragraph (a) of this AD terminates the 
requirements of paragraph (a) of this AD. Repeat the inspection 
thereafter, using an eddy current or dye penetrant technique, at 
intervals not to exceed 750 flight cycles.
    (c) If any cracking is detected during any inspection required 
by paragraph (b) of this AD: Prior to further flight, rework the 
main fitting of the NLG, in accordance with Part 3 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
118, dated October 8, 1999. If, after rework, any cracking remains 
that exceeds the limits specified in the service bulletin, prior to 
further flight, accomplish the actions specified by either paragraph 
(c)(1) or (c)(2) of this AD.
    (1) Replace the NLG in accordance with the service bulletin; and 
within 7,875 flight cycles after such replacement, perform the 
inspection as specified in paragraph (b) of this AD, and repeat the 
inspection thereafter at intervals not to exceed 750 flight cycles. 
Or
    (2) 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.

    Note 4: The Fokker service bulletin references Messier-Dowty 
Service Bulletin F100-32-92, Revision 1, dated October 8, 1999, as 
an additional source of service information for accomplishing the 
inspections and rework of the NLG main fitting subassembly.

Reporting Requirements

    (d) Submit a report of the detailed visual inspection findings 
(positive and negative) required by paragraph (a) and a report of 
the initial eddy current or dye penetrant inspection findings 
(positive and negative) required by paragraph (b) to Fokker Services 
B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; at the 
applicable time specified in paragraph (d)(1) or (d)(2). Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMP) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C.

[[Page 13926]]

3501 et seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the detailed visual inspection 
specified by paragraph (a) of this AD and the initial repetitive 
eddy current or dye penetrant inspection specified by paragraph (b) 
of this AD are accomplished after the effective date of this AD: 
Submit each report within 7 days after performing the applicable 
inspection.
    (2) For airplanes on which the detailed visual inspection 
specified by paragraph (a) of this AD and the initial repetitive 
eddy current or dye penetrant inspection specified in paragraph (b) 
of this AD have been accomplished prior to the effective date of 
this AD: Submit the reports within 7 days after the effective date 
of this AD.

Spares

    (e) As of the effective date of this AD, no person shall install 
a NLG having P/N 201071001 or 201071002 unless the installed MFSA 
has been inspected, by means of an eddy current or dye penetrant 
inspection, in accordance with paragraph (b) of this AD.

Alternative Methods of Compliance

    (f) 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 5: 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

    (g) 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 6: The subject of this AD is addressed in Dutch 
airworthiness directive BLA 1997-116/2 (A), dated October 29, 1999.


    Issued in Renton, Washington, on March 9, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-6331 Filed 3-14-00; 8:45 am]
BILLING CODE 4910-13-U