[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
