[Federal Register Volume 66, Number 210 (Tuesday, October 30, 2001)]
[Rules and Regulations]
[Pages 54661-54663]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-27069]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-208-AD; Amendment 39-12487; AD 2001-22-08]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 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 all Fokker Model F.28 series airplanes, that requires 
replacing the main landing gear (MLG) torque link dampers with modified 
and reidentified dampers. This action is necessary to prevent 
degradation of the dampers, which could result in MLG high amplitude 
oscillation in a lateral torsional mode, and consequent MLG damage or 
separation of the MLG from the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective December 4, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 4, 2001.

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 all Fokker Model F.28 series 
airplanes was published in the Federal Register on August 17, 2001 (66 
FR 43124). That action proposed to require replacing the main landing 
gear (MLG) torque link dampers with modified and reidentified dampers.

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.

Allow Use of New-Configuration Dampers

    The commenter requests that the FAA revise paragraph (a) of the 
proposed rule to allow an operator to install a torque link damper with 
a dash number higher than (23700)-5. The commenter states that it has 
already modified its entire inventory of torque link dampers to the 
configuration of part number 23700-7. The commenter states that 
revising the proposed AD to allow installation of parts modified to a 
configuration subsequent to that of part number 23700-5 would relieve 
it and other operators of the need to request approval of alternative 
methods of compliance (AMOCs).
    The FAA partially concurs with the commenter's request. Because we 
cannot approve installation of dampers that do not exist, we do not 
concur to revise paragraph (a) of the proposed AD in the specific way 
the commenter suggests.
    However, since the issuance of the proposed rule, we have reviewed 
Fokker

[[Page 54662]]

Service Bulletins SBF28/32-159, dated October 1, 1999 (for Models F.28 
Mark 1000 through 4000 series airplanes), and SBF100-32-116, dated 
February 1, 2000 (for Model F.28 Mark 0070/0100 series airplanes). 
Those service bulletins specify replacement of existing torque link 
dampers with modified dampers, and refer to Menasco Aerospace Service 
Bulletin 23700-32-15, dated September 3, 1999, as an appropriate source 
of service information for modifying torque link dampers with part 
number 23700-1, -3, or -5, to part number 23700-7. In consideration of 
these service bulletins, we have added a new Note 2 to this final rule 
to state that installation of torque link dampers with part number 
23700-7 in accordance with Fokker Service Bulletin SBF28/32-159 or 
SBF100-32-116, as applicable, is acceptable for compliance with 
paragraph (a) of this AD.
    Operators should note that, for installation of dampers with part 
numbers other than 23700-5 or -7, they must submit a request for 
approval of an AMOC in accordance with paragraph (c) of this AD.

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 as proposed.

Cost Impact

    The FAA estimates that 147 Model F.28 series airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 6 
work hours per airplane to accomplish the required replacement, and 
that the average labor rate is $60 per work hour. Required parts will 
cost approximately $1,910 per airplane. Based on these figures, the 
cost impact of this AD on U.S. operators is estimated to be $333,690, 
or $2,270 per airplane.
    The cost impact figure discussed above is 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. 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 adding the following new 
airworthiness directive:

2001-22-08  Fokker Services B.V.: Amendment 39-12487. Docket 2001-
NM-208-AD.

    Applicability: All Model F.28 series airplanes, 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.
    To prevent separation of the main landing gear (MLG) from the 
airplane due to performance degradation of the torque link damper, 
accomplish the following:

Modification and Reidentification

    (a) Replace MLG torque link dampers having part numbers (P/N) 
23700-1 or -3 with dampers having P/N 23700-5, in accordance with 
the Accomplishment Instructions of Fokker Service Bulletin (SB) 
SBF28/32-157 (for Models F.28 Mark 1000 through 4000 series 
airplanes) or Fokker Service Bulletin SBF100-32-114 (for Model F.28 
Mark 0070/0100 series airplanes), both dated October 1, 1999, as 
applicable; at the times specified in the following table:

                                           Table 1.--Compliance Times
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                                                                                      Compliance required after
      Fokker F.28 model (mark)         MLG manufactured by      MLG mod. status      the effective date of this
            designation                                                                          AD
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(1) Mk.0100........................  Dowty Aerospace; MD...  Pre-Mod SB F100-32-50  Within 15 months.
(2) Mk.0100........................  Dowty Aerospace; MD...  Post-Mod SB F100-32-   Within 21 months.
                                                              50.
(3) Mk.0100........................  Menasco Aerospace.....  [Reserved]...........  Within 24 months.
(4) Mk.0070........................  Menasco Aerospace.....  [Reserved]...........  Within 24 months.
(5) Mk.1000 through Mk.4000 series.  Dowty Aerospace; MD...  [Reserved]...........  Within 24 months.
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    Note 2: Installation of torque link dampers with P/N 23700-7 in 
accordance with Fokker Service Bulletin SBF28/32-159, dated October 
1, 1999 (for Models F.28 Mark 1000 through 4000 series airplanes), 
or SBF100-32-116, dated February 1, 2000 (for Model

[[Page 54663]]

F.28 Mark 0070/0100 series airplanes), as applicable, is acceptable 
for compliance with paragraph (a) of this AD.

Spares

    (b) As of the effective date of this AD, no person shall install 
torque link damper having P/N 23700-1 or -3, on any airplane.

Alternative Methods of Compliance

    (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, 
Transport Airplane Directorate, FAA. 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.

Special Flight Permits

    (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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Fokker Service 
Bulletin SBF28/32-157, dated October 1, 1999; or Fokker Service 
Bulletin SBF100-32-114, dated October 1, 1999; as applicable. 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 4: The subject of this AD is addressed in Dutch 
airworthiness directive 1999-138, dated October 29, 1999.

Effective Date

    (f) This amendment becomes effective on December 4, 2001.

    Issued in Renton, Washington, on October 22, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-27069 Filed 10-29-01; 8:45 am]
BILLING CODE 4910-13-P