[Federal Register Volume 65, Number 168 (Tuesday, August 29, 2000)]
[Rules and Regulations]
[Pages 52298-52301]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-21459]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-02-AD; Amendment 39-11876; AD 2000-17-03]
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 supersedes 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

[[Page 52299]]

nose landing gear (NLG) main fitting to detect cracking; and rework of 
the NLG main fitting, if necessary. This amendment requires 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 
amendment also revises the applicability of the existing AD. This 
amendment is prompted by the 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 NLG main fitting, which could lead to collapse of the NLG during 
takeoff and landing, and possible injury to the flightcrew and 
passengers.

DATES: Effective October 3, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 3, 2000.

ADDRESSES: 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 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) by superseding AD 98-22-01, 
amendment 39-10847 (63 FR 58625, November 2, 1998), which is applicable 
to certain Fokker Model F.28 Mark 0100 series airplanes, was published 
in the Federal Register on March 15, 2000 (65 FR 13923). The action 
proposed to require new inspections (one-time detailed visual 
inspection and repetitive eddy current or dye penetrant inspections) to 
detect cracking of the nose landing gear (NLG) main fitting 
subassembly, and corrective actions, if necessary. The action also 
proposed to revise the applicability of the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    One commenter states that it has completed the inspections and has 
a repetitive inspection program already in place to comply with the 
requirements of this AD.

Type Certificate Holder

    One commenter requests that the Explanation of Relevant Service 
Information section of the AD be revised to refer to the current type 
certificate holder (Fokker Services B.V.), rather than the now defunct 
airplane manufacturer, as the issuer of the relevant service 
information. The FAA acknowledges the accuracy of this information; 
however, since this section is not repeated in the final rule, no 
change is made to the AD.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 87 airplanes of U.S. registry that will be 
affected by this AD.
    The one-time detailed visual inspection required by this AD action 
will 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 one-time inspection required 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 required 
by this AD action will 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 required 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 requirements of this 
AD, and that no operator would accomplish those actions in the future 
if this AD were not adopted. The cost impact figures discussed in AD 
rulemaking actions represent only the time necessary to perform the 
specific actions actually required by the AD. These figures typically 
do not include incidental costs, such as the time required to gain 
access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-10847 (63 FR 
58625, November 2, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-11876, to read as follows:

2000-17-03 Fokker Services B.V.: Amendment 39-11876. 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

[[Page 52300]]

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) of this AD and a 
report of the initial eddy current or dye penetrant inspection 
findings (positive and negative) required by paragraph (b) of this 
AD 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) of this AD. 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. 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.

Incorporation by Reference

    (h) Except as provided by paragraph (c)(2) of this AD, the 
actions shall be done in accordance with Fokker Service Bulletin 
SBF100-32-118, dated October

[[Page 52301]]

8, 1999. 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 6: The subject of this AD is addressed in Dutch 
airworthiness directive BLA 1997-116/2 (A), dated October 29, 1999.

Effective Date

    (i) This amendment becomes effective on October 3, 2000.

    Issued in Renton, Washington, on August 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-21459 Filed 8-28-00; 8:45 am]
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