[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34569-34571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16451]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-16-AD; Amendment 39-10616; AD 98-13-25]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 1000, 2000,
3000, and 4000 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 1000, 2000, 3000,
and 4000 series airplanes, that currently requires an inspection to
detect free movement of the actuator servo-valve sub-assembly of the
horizontal stabilizer actuator, and replacement, if necessary. This
amendment adds a one-time inspection to determine the residual strength
of the servo-valve sub-assembly of the horizontal stabilizer actuator,
and replacement of the actuator with a new or serviceable actuator, if
necessary; and eventual replacement of the horizontal stabilizer
actuator with an improved actuator. 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 uncommanded trimming or failure of the trim system
of the horizontal stabilizer, and consequent reduced controllability of
the airplane.
DATES: Effective July 30, 1998.
The incorporation by reference of Fokker Service Bulletin F28/27-
183, dated November 21, 1994, as listed in the regulations, is approved
by the Director of the Federal Register as of July 30, 1998.
The incorporation by reference of Fokker Service Bulletin F28/27-
180, dated July 3, 1992, as listed in the regulations, was approved by
the Director of the Federal Register as of September 9, 1992 (57 FR
38432, August 25,1992).
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,
[[Page 34570]]
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 92-18-04,
amendment 39-8348 (57 FR 38432, August 25, 1992), which is applicable
to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series
airplanes, was published in the Federal Register on April 27, 1998 (63
FR 20554). The action proposed to continue to require an inspection to
detect free movement of the actuator servo-valve sub-assembly of the
horizontal stabilizer actuator, and replacement, if necessary. The
action proposed to add a one-time inspection to determine the residual
strength of the servo-valve sub-assembly of the horizontal stabilizer
actuator, and replacement of the actuator with a new or serviceable
actuator, if necessary; and eventual replacement of the horizontal
stabilizer actuator with an improved actuator.
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 approximately 27 airplanes of U.S. registry that will be
affected by this AD.
The inspection that is currently required by AD 92-18-04 takes
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 previously required inspection on U.S. operators is
estimated to be $1,620, or $60 per airplane.
The inspection that is required in this new AD action will take
approximately 2 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 new inspection requirements of this AD on U.S. operators
is estimated to be $3,240, or $120 per airplane.
The replacement required in this new AD action will take
approximately 8 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operator. Based on these figures, the
cost impact of the replacement required by this AD on U.S. operators is
estimated to be $12,960, or $480 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 39-8348 (57 FR
38432, August 25, 1992), and by adding a new airworthiness directive
(AD), amendment 39-10616 to read as follows:
98-13-25 Fokker: Amendment 39-10616. Docket 98-NM-16-AD. Supersedes
AD 92-18-04, Amendment 39-8348.
Applicability: Model F.28 Mark 1000, 2000, 3000, and 4000 series
airplanes; equipped with Menasco horizontal stabilizer actuators
having part number (P/N) 11100-
( ); 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 (e) 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 uncommanded trimming or failure of the trim system of
the horizontal stabilizer, and consequent reduced controllability of
the airplane, accomplish the following:
(a) Within 20 days after September 9, 1992 (the effective date
of AD 92-18-04, amendment 39-8348), perform an inspection of the
servo-valve sub-assembly rod-end bearing and servo-valve sub-
assembly for movement, in accordance with Fokker Service Bulletin
F28/27-180, dated July 3, 1992.
(1) If the servo-valve sub-assembly rod-end bearing and servo-
valve sub-assembly move freely within the load limits specified in
the service bulletin, reassemble and conduct a functional test, in
accordance with the service bulletin.
(2) If the servo-valve sub-assembly rod-end bearing or servo-
valve sub-assembly require higher loads for movement than specified
in the service bulletin, prior to further flight, remove and replace
the horizontal stabilizer control unit with a serviceable control
unit that has been inspected and found to be within the load limits
of the service bulletin, or that has been inspected and repaired in
accordance with Chapter 27-42-4 of the Menasco Overhaul Manual
(OHM), as revised by Temporary Revision Number 3, dated July 10,
1992.
(b) Within 6 months after the effective date of this AD, perform
a one-time inspection to determine the residual strength of the
servo-valve sub-assembly of the horizontal stabilizer actuator, in
accordance with Part 1 of the Accomplishment Instructions of
[[Page 34571]]
Fokker Service Bulletin F28/27-183, dated November 21, 1994. If any
discrepancy is found, prior to further flight, replace the actuator
with a new or serviceable actuator in accordance with the service
bulletin.
(c) Within 3 years after the effective date of this AD, replace
the horizontal stabilizer actuator with an actuator that has been
modified and re-marked in accordance with Part 2 of the
Accomplishment Instructions of Fokker Service Bulletin F28/27-183,
dated November 21, 1994.
(d) As of the effective date of this AD, no person shall install
a horizontal stabilizer control unit on any airplane, unless the
horizontal stabilizer actuator has been modified and re-marked in
accordance with Part 2 of the Accomplishment Instructions of Fokker
Service Bulletin F28/27-183, dated November 21, 1994.
(e) 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.
(f) 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.
(g) The actions shall be done in accordance with Fokker Service
Bulletin F28/27-180, dated July 3, 1992, and Fokker Service Bulletin
F28/27-183, dated November 21, 1994.
(1) The incorporation by reference of Fokker Service Bulletin
F28/27-183, dated November 21, 1994, 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
F28/27-180, dated July 3, 1992, was approved previously by the
Director of the Federal Register as of September 9, 1992 (57 FR
38432, August 25, 1992).
(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 1992-007/2(A), dated January 31, 1995.
(h) This amendment becomes effective on July 30, 1998.
Issued in Renton, Washington, on June 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-16451 Filed 6-24-98; 8:45 am]
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