[Federal Register Volume 61, Number 121 (Friday, June 21, 1996)]
[Rules and Regulations]
[Pages 31825-31827]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-15602]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-151-AD; Amendment 39-9674; AD 96-13-06]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Series Airplanes
(Excluding 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 series airplanes, that requires
replacement of junction fittings of the horizontal stabilizer with
improved fittings. For certain airplanes, this amendment also requires
replacement of the drive-fitting bushings and bolts of the horizontal
stabilizer with improved bushings and bolts. This amendment is prompted
by reports of stress corrosion cracking in a junction fitting lug of
the horizontal stabilizer. The actions specified by this AD are
intended to prevent such cracking, which could result in failure of a
lug and uncommanded movement of the horizontal stabilizer. This
condition, if not corrected, could result in reduced controllability of
the airplane.
DATES: Effective July 26, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 26, 1996.
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,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2141; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Fokker Model F28 series
airplanes was published in the Federal Register on
[[Page 31826]]
April 1, 1996 (61 FR 14273). That action proposed to require
replacement of aluminum 7079 junction fittings (left and right) of the
horizontal stabilizer with improved fittings made from aluminum 7075.
For certain airplanes, that action also proposed to require replacement
of the drive-fitting bushings and bolts of the horizontal stabilizer
with new bushings and bolts made from a different material having
improved resistance to corrosion.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Support for the Proposal
Both commenters support the proposed rule.
Conclusion
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.
Cost Impact
The FAA estimates that 14 airplanes of U.S. registry will be
affected by this AD.
For airplanes on which the replacement of aluminum 7079 junction
fittings with improved fittings is required, the FAA estimates that it
will take approximately 430 work hours per airplane to accomplish the
replacement, at an average labor rate of $60 per work hour. Required
parts will cost approximately $40,000 per airplane. Based on these
figures, the cost impact of the AD on U.S. operators for replacement of
aluminum 7079 fittings is estimated to be $65,800 per airplane.
For airplanes on which replacement of the drive-fitting bushings
and bolts on the horizontal stabilizer with new bushings and bolts is
required, the FAA estimates that it will take approximately 10 work
hours per airplane to accomplish the replacement, at an average labor
rate of $60 per work hour. Required parts will cost approximately
$2,100 per airplane. Based on these figures, the cost impact of the AD
on U.S. operators for replacement of the drive-fitting bushings and
bolts is estimated to be $2,700 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 adding the following new
airworthiness directive:
96-13-06 Fokker: Amendment 39-9674. Docket 95-NM-151-AD.
Applicability: Model F28 series airplanes; serial numbers 11003
through 11151 inclusive, 11991, and 11992; certificated in any
category.
Note 1: Fokker Model F28 Mark 0100 series airplanes are not
subject to the requirements of this AD.
Note 2: 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 (d) 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 stress corrosion cracking of the junction fitting lug
of the horizontal stabilizer, which could result in failure of the
lug and uncommanded movement of the horizontal stabilizer, and
subsequent reduced controllability of the airplane, accomplish the
following:
(a) Within 18 months after the effective date of this AD,
replace the aluminum 7079 junction fittings (left and right) of the
horizontal stabilizer with improved fittings made from aluminum
7075, in accordance with Part 1 of the Accomplishment Instructions
of Fokker Service Bulletin F28/55-029, Revision 1, dated January 23,
1993.
(b) For airplanes on which the drive-fitting bushings and bolts
of the horizontal stabilizer have not been replaced in accordance
with Fokker Service Bulletin F28/55-24: Within 18 months after the
effective date of this AD, replace the drive-fitting bushings and
bolts of the horizontal stabilizer with new bushings and bolts, in
accordance with Part 2 of the Accomplishment Instructions of Fokker
Service Bulletin F28/55-029, Revision 1, dated January 23, 1993.
(c) Accomplishment of the replacements required by paragraphs
(a) and (b) of this AD constitute terminating action for the
inspections identified as item 55-50-05 in the Fokker Structural
Integrity Program (SIP) Document 28438, Part 1, revised up through
October 15, 1992, which are required by AD 93-13-04, amendment 39-
8617 (58 FR 38513, July 19, 1993). Once these replacements are
accomplished, the life limits of the fitting lugs (identified as
items 55-50-01 and 55-50-02 in the SIP Document) no longer apply.
(d) 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,
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,
Standardization Branch, ANM-113.
Note 3: Information concerning the existence of approved
alternative methods of
[[Page 31827]]
compliance with this AD, if any, may be obtained from the
Standardization Branch, ANM-113.
(e) 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.
(f) The replacements shall be done in accordance with Fokker
Service Bulletin F28/55-029, Revision 1, dated January 23, 1993,
which contains the following list of effective pages:
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Revision level
Page No. shown on page Date shown on page
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1-3............................ 1.............. Jan. 23, 1993.
4-45........................... Original....... Sep. 20, 1992.
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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.
(g) This amendment becomes effective on July 26, 1996.
Issued in Renton, Washington, on June 13, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-15602 Filed 6-20-96; 8:45 am]
BILLING CODE 4910-13-U
