[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]
BILLING CODE 4910-13-U