[Federal Register Volume 59, Number 21 (Tuesday, February 1, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-1228]
[[Page Unknown]]
[Federal Register: February 1, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-113-AD; Amendment 39-8800; AD 94-02-03]
Airworthiness Directives; Fokker Model F28 Mark 0100 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 certain Fokker Model F28 Mark 0100 series airplanes that
requires replacement of the existing attachment bolts on the horizontal
stabilizer with new, improved bolts having a longer fatigue life. This
amendment is prompted by a report that certain attachment bolts on the
horizontal stabilizer were not properly treated on the surface during
production, resulting in reduced fatigue life. The actions specified by
this AD are intended to prevent corrosion and subsequent fatigue-
related cracking of the attachment bolts on the horizontal stabilizer,
which could lead to loss of stabilizer control.
DATES: Effective March 3, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 3, 1994.
ADDRESSES: The service information referenced in this AD may be
obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street,
Alexandria, Virginia 22314. 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: Tim Dulin, Aerospace Engineer, ANM-
113, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington 98055-4056; telephone (206) 227-2141; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations to include an airworthiness directive (AD) that is
applicable to certain Fokker Model F28 Mark 0100 series airplanes was
published in the Federal Register on September 1, 1993 (58 FR 46136).
That action proposed to require replacement of the existing bolts that
attach the link assemblies on the dual actuator to the drive bracket on
the horizontal stabilizer with improved bolts having a longer fatigue
life, and performance of a functional test.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposed rule.
The Air Transport Association (ATA) of America, on behalf of one of
its members, requests withdrawal of the proposal. The commenter notes
that only 20 airplanes in the U.S.-registered fleet would be affected
by the proposed rule and that the proposed bolt replacement has already
been accomplished on 5 U.S.-registered airplanes. The commenter also
notes that the proposed actions will be performed on the 15 remaining
airplanes in the U.S.-registered fleet, prior to the proposed
compliance time of 13,500 total landings. Therefore, the commenter does
not believe that an AD is necessary. The FAA does not agree. Issuance
of this AD is necessary in order to ensure compliance for the remaining
unmodified airplanes in the U.S.-registered fleet. Also, although the
current U.S.-registered fleet size is relatively small, issuance of
this AD will ensure accomplishment of the requirements on any affected
airplane currently of foreign registry that is purchased by a U.S.
operator and placed on the U.S. register in the future. -
The same commenter also requests that an operational test of the
horizontal stabilizer be accepted as an alternative to the lengthy
proposed functional test, in the event that the FAA decides not to
withdraw the proposed AD. The commenter asserts that bolt replacement
would not affect horizontal stabilizer adjustment or rigging and
therefore, the proposed functional test procedure is unnecessary. The
commenter adds that Fokker has indicated that the operational test is
acceptable, in lieu of the proposed functional test. The FAA does not
concur, since the commenter did not submit enough data for the FAA to
evaluate the proposed alternative method of compliance. However, the
FAA may consider approval of an alternative method of compliance, in
accordance with paragraph (c) of this AD, if such data were provided to
justify the request and the operational test procedure is defined or
referenced.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 20 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 11 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $55 per work hour. Required parts will cost approximately
$1,100 per airplane. Based upon these figures, the total cost impact of
the AD on U.S. operators is estimated to be $34,100, or $1,705 per
airplane.
The FAA has been advised that 5 U.S.-registered airplanes have been
modified in accordance with the requirements of this AD. Therefore, the
future economic cost impact of this rule on U.S. operators is now only
$25,575.
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 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-02-03 Fokker: Amendment 39-8800. Docket 93-NM-113-AD.
Applicability: Model F28 Mark 0100 series airplanes, serial
numbers 11244 through 11300 inclusive, 11303, 11306, 11308, 11310,
and 11312 through 11314 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously. -To prevent corrosion and subsequent fatigue-related
cracking of the attachment bolts on the horizontal stabilizer, which
could lead to loss of stabilizer control, accomplish the following:
(a) Prior to the accumulation of 13,500 total landings or within
12 months after the effective date of this AD, whichever occurs
later, replace the two existing bolts, part number D03000-017, that
attach the link assemblies on the dual actuator to the drive bracket
of the horizontal stabilizer, with new, improved bolts, part number
DO3000-021; and perform a functional test; in accordance with Fokker
Service Bulletin SBF100-27-037, dated April 3, 1992.
(b) As of the effective date of this AD, no person shall install
an attachment bolt, part number D03000-017, on the horizontal
stabilizer on any airplane.
(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, Standardization Branch, ANM-113.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Standardization Branch, ANM-113.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) Special flight permits may be issued in accordance with FAR
21.197 and 21.199 to operate the airplane to a location where the
requirements of this AD can be accomplished.
(e) The replacement and function shall be done in accordance
with Fokker Service Bulletin SBF100-27-037, dated April 3, 1992.
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 Aircraft USA, Inc., 1199
North Fairfax Street, Alexandria, Virginia 22314. 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.
(f) This amendment becomes effective on March 3, 1994.
Issued in Renton, Washington, on January 12, 1994.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-1228 Filed 1-31-94; 8:45 am]
BILLING CODE 4910-13-U
