[Federal Register Volume 61, Number 64 (Tuesday, April 2, 1996)]
[Proposed Rules]
[Pages 14515-14517]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7985]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 92-NM-71-AD]


Airworthiness Directives; Fokker Model F28 Mark 0100 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to certain Fokker Model F28 Mark 0100 series 
airplanes, that would have required reinforcing the lower right-hand 
wing skin at the fueling adapter. That proposal was prompted by results 
of tests, which revealed that fatigue cracks can develop in the lower 
right-hand wing skin at the attachment bolt holes of the fueling 
adapter. This action revises the proposed rule by citing the latest 
service information. This action also revises the applicability of the 
proposed AD. The actions specified by this proposed AD are intended to 
prevent reduced structural capability of the wing and fuel leakage.

DATES: Comments must be received by April 26, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 92-NM-71-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, 
Alexandria, Virginia 22314. This information may be examined at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Ruth E. Harder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-1721; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 92-NM-71-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 92-NM-71-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to 
certain Fokker Model F28 Mark 0100 series airplanes, was published as a 
notice of proposed rulemaking (NPRM) in the Federal Register on June 4, 
1992 (57 FR 23552). That NPRM would have required reinforcing the lower 
right-hand wing skin at the fueling adapter. That NPRM was prompted by 
results of tests, which revealed that fatigue cracks can develop in the 
lower right-hand wing skin at the attachment bolt holes of the fueling 
adapter. That condition, if not corrected, could result in reduced

[[Page 14516]]
structural capability of the wing and fuel leakage.
    Since the issuance of that NPRM, Fokker issued Service Bulletin 
SBF100-57-008, Revision 1, dated March 29, 1992, and Revision 2, dated 
September 22, 1995. (The original issue of the service bulletin, dated 
November 1, 1991, was cited in the NPRM as the appropriate source of 
service information.) Revision 1 of the service bulletin provides 
procedures for reinforcing the lower right-hand wing skin at the 
fueling adapter that are significantly revised beyond the procedures 
specified in the original issue of the service bulletin. Revision 2 of 
the service bulletin provides additional procedures for reinforcement 
that include installation of eight hilok bolts and cold sleeve 
expansion of the fueling adapter attachment holes. In addition, the 
effectivity of Revision 2 has been revised to include additional 
airplanes that are subject to the addressed unsafe condition; certain 
other airplanes have been removed from the effectivity listing.
    The Rijksluchtvaartdienst (RLD), which is the airworthiness 
authority for the Netherlands, classified these service bulletins as 
mandatory, and issued Dutch airworthiness directive BLA 1991-131/3 (A), 
dated October 31, 1995, in order to assure the continued airworthiness 
of these airplanes in the Netherlands.
    The FAA examined the findings of the RLD and reviewed the revised 
service information. The FAA finds that the NPRM must be revised to 
require that the reinforcement be accomplished in accordance with 
Revision 2 of the service bulletin. Paragraph (a) of this supplemental 
NPRM has been revised accordingly. In addition, a note has been added 
to this supplemental NPRM to specify that no further action is required 
for airplanes on which the reinforcement has been accomplished in 
accordance with Revision 1 of the service bulletin prior to the 
effective date of this proposed AD.
    In addition, the applicability of the proposed AD has been revised 
to include additional airplanes that are subject to the addressed 
unsafe condition and to remove certain other airplanes.
    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.
    The FAA also has revised the economic impact information, below, to 
reflect the current number of airplanes of U.S. registry that would be 
affected by this proposed AD. This information also has been revised to 
reflect an increase in the cost for required parts from $880 to $950 
per airplane based on the latest information from the manufacturer. 
Additionally, the labor rate used in these calculations has been 
increased from $55 per work hour to $60 per work hour to account for 
the various inflationary costs in the airline industry.
    The FAA estimates that 18 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 20 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $950 per airplane. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $38,700, 
or $2,150 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.
    However, the FAA has been advised that 14 U.S.-registered airplanes 
have already been modified in accordance with the requirements of this 
proposed AD. Therefore, the future economic cost impact of this 
proposed rule on U.S. operators is now only $8,600.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Fokker: Docket 92-NM-71-AD.

    Applicability: Model F28 Mark 0100 series airplanes; serial 
numbers 11244 through 11286 inclusive, 11289, 11290 through 11293 
inclusive, 11295, 11297, 11300, 11303, 11306, 11308, 11310, and 
11312; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (b) 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 reduced structural capability of the wing and fuel 
leakage, accomplish the following:
    (a) Prior to the accumulation of 12,000 total landings, or 
within 60 days after the effective date of this AD, whichever occurs 
later, reinforce the lower right-hand wing skin at the fueling 
adapter by installing a new stringer and new internal and external 
doubler plates, in accordance with Fokker Service Bulletin SBF100-
57-008, Revision 2, dated September 22, 1995.

    Note 2: Accomplishment of the reinforcement in accordance with 
Fokker Service Bulletin SBF100-57-008, Revision 1, dated March 29, 
1992, prior to the effective date of this AD is acceptable for 
compliance with the requirement of paragraph (a) of this AD.
    (b) 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,

[[Page 14517]]
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 compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) 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.

    Issued in Renton, Washington, on March 27, 1996.
Darrell M. Pederson,
 Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-7985 Filed 4-1-96; 8:45 am]
BILLING CODE 4910-13-P