[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