[Federal Register Volume 63, Number 193 (Tuesday, October 6, 1998)]
[Rules and Regulations]
[Pages 53556-53558]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-26395]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-92-AD; Amendment 39-10810; AD 98-21-02]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F27 Mark 050, 100, 200, 
300, 400, 500, 600, and 700 Rough Field Version (RFV) 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 F27 Mark 100, 200, 300, 400, 
500, 600, and 700 Rough Field Version (RFV) series airplanes, that 
currently requires inspection of the main landing gear (MLG) legs to 
determine if parts are missing or damaged, and modification, if 
necessary; and periodic measurements of the extension of each MLG shock 
absorber sliding member. That AD also provides for the accomplishment 
of a certain modification as optional terminating action for the 
periodic measurements. This amendment requires accomplishment of the 
previously optional terminating action, and revises the applicability 
of the existing AD to add an airplane model. This amendment is prompted 
by issuance of mandatory continuing airworthiness information by a 
foreign civil airworthiness authority. The actions specified by this AD 
are intended to prevent loss of the MLG sliding member, which could 
result in reduced structural integrity of the MLG.

DATES: Effective November 10, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 10, 1998.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of December 16, 1993 (58 FR 60370, November 16, 
1993).

ADDRESSES: The service information referenced in this AD 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 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 93-22-02, 
amendment 39-8727 (58 FR 60370, November 16, 1993), which is applicable 
to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 
Rough Field Version (RFV) series airplanes, was published in the 
Federal Register on August 13, 1998 (63 FR 43342). The action proposed 
to continue to require inspection of the main landing gear (MLG) legs 
to determine if parts are missing or damaged, and modification, if 
necessary; and periodic measurements of the extension of each MLG shock 
absorber sliding member. That action also provides for the 
accomplishment of a certain modification as optional terminating action 
for the periodic measurements. The action also proposed to require 
accomplishment of the previously optional terminating action, and to 
revise the applicability of the existing AD to add an airplane model.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are 34 Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, 
and 700 RFV series airplanes, and no Fokker Model F27 Mark 050 series 
airplanes, of U.S. registry that will be affected by this AD.
    The actions that are currently required by AD 93-22-02, and 
retained in this AD, will take approximately 3 work hours per airplane 
to accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required inspections on 
U.S. operators is estimated to be $6,120, or $180 per airplane, per 
inspection cycle.

[[Page 53557]]

    The new modification that is required in this AD action will take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the modification required by this AD on U.S. operators 
is estimated to be $4,080, or $120 per airplane.
    The cost impact figures discussed above are 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.

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 39-8727 (58 FR 
60370, November 16 1993), and by adding a new airworthiness directive 
(AD), amendment 39-10810, to read as follows:

98-21-02  Fokker Services B.V.: Amendment 39-10810. Docket 98-NM-92-
AD. Supersedes AD 93-22-02, Amendment 39-8727.

    Applicability: Model F27 Mark 050, 100, 200, 300, 400, 500, 600, 
and 700 Rough Field Version (RFV) series airplanes, equipped with 
Dowty Aerospace MLG Legs, part and serial numbers as listed in Dowty 
Aerospace Landing Gear Service Bulletin 32-77W, Revision 4, dated 
February 3, 1993, or Dowty Aerospace Landing Gear Service Bulletin 
F50-32-27, Revision 4, dated December 18, 1992; 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 (g) 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 loss of the MLG sliding member, which could result in 
reduced structural integrity of the MLG, accomplish the following:

Restatement of Requirements of AD 93-22-02

    (a) For Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 RFV 
series airplanes, equipped with Dowty Aerospace MLG, part numbers 
200563001, 200679001, 200679002, 200679003, or 200679004: Within 30 
days after December 16, 1993 (the effective date of AD 93-22-02, 
amendment 39-8727), inspect the MLG legs to confirm the correct 
installation of the sliding member out-stop installation, in 
accordance with Fokker Service Bulletin F27-32-165, Revision 1, 
dated April 28, 1993, and paragraph 2.C. (``Part A Procedure'') of 
Dowty Aerospace Landing Gear Service Bulletin 32-81W, Revision 2, 
dated February 3, 1993. If any parts are determined to be missing or 
damaged, prior to further flight, modify the MLG assembly, in 
accordance with Dowty Aerospace Landing Gear Service Bulletin 32-
77W, Revision 4, dated February 3, 1993.
    (b) For Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 RFV 
series airplanes, equipped with Dowty Aerospace MLG, part numbers 
200563001, 200679001, 200679002, 200679003, or 200679004: Within 30 
days after December 16, 1993, measure and record the extension of 
the MLG sliding member when the landing gear is fully extended, in 
accordance with paragraph 2.D. (``Part B Procedure'') of Dowty 
Aerospace Landing Gear Service Bulletin 32-81W, Revision 2, dated 
February 3, 1993.
    (1) If the extension dimension exceeds 410.2 mm (16.15 inches), 
prior to further flight, modify the MLG assembly in accordance with 
Dowty Aerospace Landing Gear Service Bulletin 32-77W, Revision 4, 
dated February 3, 1993.
    (2) If the extension dimension is equal to or less than 410.2 mm 
(16.15 inches), repeat the measurement thereafter at intervals not 
to exceed 500 flight cycles.
    (3) If the extension dimension increases by more than 1.0 mm 
(0.40 inch) above the initially recorded dimension during any 
measurement required by this paragraph, prior to further flight, 
inspect the MLG in accordance with paragraph (a) of this AD.

New Requirements of This AD

    (c) For airplanes other than those identified in paragraph (a) 
of this AD: Within 30 days after the effective date of this AD, 
inspect the MLG legs to confirm the correct installation of the 
sliding member out-stop installation, in accordance with paragraph 
2.C. (``Part A Procedure'') of Messier-Dowty Service Bulletin F50-
32-48, Revision 4, dated June 21, 1995. If any parts are determined 
to be missing or damaged, prior to further flight, modify the MLG 
assembly, in accordance with Dowty Aerospace Landing Gear Service 
Bulletin F50-32-27, Revision 4, dated December 18, 1992.
    (d) For airplanes other than those identified in paragraph (a) 
of this AD: Within 30 days after the effective date of this AD, 
measure and record the extension of the MLG sliding member when the 
landing gear is fully extended, in accordance with paragraph 2.D. 
(``Part B Procedure'') of Messier-Dowty Service Bulletin F50-32-48, 
Revision 4, dated June 21, 1995.
    (1) If the extension dimension exceeds 410.2 mm (16.15 inches), 
prior to further flight, modify the MLG assembly in accordance with 
Dowty Aerospace Landing Gear Service Bulletin F50-32-27, Revision 4, 
dated December 18, 1992.
    (2) If the extension dimension is equal to or less than 410.2 mm 
(16.15 inches), repeat the measurement thereafter at intervals not 
to exceed 500 flight cycles.
    (3) If the extension dimension increases by more than 1.0 mm 
(0.40 inch) above the initially recorded dimension during any 
measurement required by this paragraph, prior to further flight, 
inspect the MLG in accordance with paragraph (c) of this AD.
    (e) For all airplanes: Within 5,000 flight cycles or 24 months 
after the effective date of this AD, whichever occurs earlier, 
modify the MLG piston rod assembly, in accordance with Dowty 
Aerospace Landing Gear Service Bulletin 32-77W, Revision 4, dated 
February 3, 1993 (for Model F27 Mark 100, 200, 300, 400, 500, 600, 
and 700 series airplanes), or Dowty Aerospace Landing Gear Service 
Bulletin F50-32-27, Revision 4, dated December 18, 1992 (for Model 
F27 Mark 050 series airplanes), as applicable. Accomplishment of 
this modification constitutes terminating action for the repetitive 
actions required by this AD.

[[Page 53558]]

    (f) As of the effective date of this AD, no person shall install 
on any airplane, an MLG piston rod assembly, unless it has been 
modified in accordance with Dowty Aerospace Landing Gear Service 
Bulletin 32-77W, Revision 4, dated February 3, 1993 (for Model F27 
Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes), or 
Dowty Aerospace Landing Gear Service Bulletin F50-32-27, Revision 4, 
dated December 18, 1992 (for Model F27 Mark 050 series airplanes), 
as applicable.
    (g) 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, FAA, 
Transport Airplane Directorate. 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.

    (h) 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.
    (i) The actions shall be done in accordance with Fokker Service 
Bulletin F27-32-165, Revision 1, dated April 28, 1993; Dowty 
Aerospace Landing Gear Service Bulletin 32-81W, Revision 2, dated 
February 3, 1993; Dowty Aerospace Landing Gear Service Bulletin 32-
77W, Revision 4, dated February 3, 1993; Messier-Dowty Service 
Bulletin F50-32-48, Revision 4, dated June 21, 1995; and Dowty 
Aerospace Landing Gear Service Bulletin F50-32-27, Revision 4, dated 
December 18, 1992, which contains the specified list of effective 
pages:

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                                                   Revision
           Page number shown on page             level shown                  Date shown on page
                                                   on page
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1, 5, 6........................................            4  December 18, 1992.
2-4, 7-9.......................................            3  September 29, 1992.
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    (1) The incorporation by reference of Dowty Aerospace Landing 
Gear Service Bulletin F50-32-27, Revision 4, dated December 18, 
1992; and Messier-Dowty Service Bulletin F50-32-48, Revision 4, 
dated June 21, 1995; is approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Fokker Service Bulletin 
F27-32-165, Revision 1, dated April 28, 1993; Dowty Aerospace 
Landing Gear Service Bulletin 32-81W, Revision 2, dated February 3, 
1993; and Dowty Aerospace Landing Gear Service Bulletin 32-77W, 
Revision 4, dated February 3, 1993; was approved previously by the 
Director of the Federal Register as of December 16, 1993 (58 FR 
60370, November 16, 1993).
    (3) Copies may be obtained from Fokker Services B.V., Technical 
Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, 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 3: The subject of this AD is addressed in Dutch 
airworthiness directive 1996-159/2 (A), dated July 31, 1997.

    (j) This amendment becomes effective on November 10, 1998.

    Issued in Renton, Washington, on September 28, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-26395 Filed 10-5-98; 8:45 am]
BILLING CODE 4910-13-U