[Federal Register Volume 60, Number 232 (Monday, December 4, 1995)]
[Proposed Rules]
[Pages 62051-62053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-29443]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-58-AD]
Airworthiness Directives; Fokker Model F28 Mark 0100 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Fokker Model F28 Mark 0100
series airplanes. This proposal would require modification of the
thrust reverser doors, and replacement of the Collins multifunction
display units (MFDU) with new MFDU's. This proposal would also require
installation of a placard, for certain airplanes. This proposal is
prompted by a report that cracks were found in the flanges of the main
hinge fittings of the horizontal stabilizer due to higher than
anticipated loads induced during thrust reverser operation. The actions
specified by the proposed AD are intended to ensure structural
integrity of the horizontal stabilizer by reducing the thrust reverser
loads on the horizontal stabilizer.
DATES: Comments must be received by January 16, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-58-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. Comments
[[Page 62052]]
may be inspected at this location between 9 a.m. and 3 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: 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:
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 95-NM-58-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. 95-NM-58-AD, 1601 Lind Avenue SW., Renton, Washington 98055-
4056.
Discussion
The Rijksluchtvaartdienst (RLD), which is the airworthiness
authority for the Netherlands, recently notified the FAA that an unsafe
condition may exist on certain Fokker Model F28 Mark 0100 series
airplanes. The RLD advises that, during full scale fatigue testing of
the horizontal and vertical stabilizers, cracks were found in the
flanges of the left- and right-hand main hinge fittings of the
horizontal stabilizer on a Model F28 Mark 0100 test article.
Investigation revealed that such cracking is the result of higher than
anticipated loads induced on the tail of the airplane during thrust
reverser operation. This condition, if not corrected, could lead to a
deteriorated fatigue life of the main hinge fitting structure on the
horizontal stabilizer and reduced structural integrity of the
horizontal stabilizer.
Fokker has issued Service Bulletin SBF100-78-010, Revision 1, dated
April 26, 1994, which describes procedures for modification of the
thrust reverser doors. This modification involves installation of
extended bumper fittings on the thrust reverser doors. Accomplishment
of this modification will reduce the reverse thrust at a given engine
pressure ratio by increasing the spillage gap.
Fokker has also issued Service Bulletin SBF100-31-036, dated
February 7, 1994, which describes procedures for replacement of the
Collins multifunction display units (MFDU) having part number (P/N)
622-8047-412 or 622-8047-422 with new MFDU's having P/N 622-8047-414 or
622-8047-423, respectively. Accomplishment of this replacement will
reduce thrust reverser loads on the horizontal stabilizer.
Additionally, Fokker has issued Service Bulletin SBF100-31-038,
dated April 26, 1994, which describes procedures for installation of a
placard on the main instrument panel, if the replacement of the MFDU is
accomplished prior to modification of the thrust reverser door. The
placard provides current engine limits for these airplanes.
The RLD classified these service bulletins as mandatory and issued
Netherlands airworthiness directive BLA 94-062(A), dated April 29,
1994, in order to assure the continued airworthiness of these airplanes
in the Netherlands.
This airplane model is manufactured in the Netherlands and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the RLD has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
RLD, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require modification of the
thrust reverser doors. The proposed AD would also require replacement
of certain Collins multifunction display units (MFDU) with certain new
MFDU's, and installation of a placard, if the replacement of the MFDU
is accomplished prior to modification of the thrust reverser door. The
actions would be required to be accomplished in accordance with the
service bulletins described previously.
The FAA estimates that 102 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 127 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 $19,000 per airplane. Based on these figures, the cost
impact of the proposed AD on U.S. operators is estimated to be
$2,715,240, or $26,620 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.
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.
[[Page 62053]]
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 U.S.C. 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Fokker: Docket 95-NM-58-AD.
Applicability: Model F28 Mark 0100 series airplanes; serial
numbers 11244 through 11460 inclusive, 11463 through 11469
inclusive, 11471, 11474, 11476, 11478, and 11479; 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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To ensure structural integrity of the horizontal stabilizer by
reducing the thrust reverser loads on the horizontal stabilizer,
accomplish the following:
(a) Prior to the accumulation of 15,000 total flight cycles, or
within 1 year after the effective date of this AD, whichever occurs
later, accomplish the requirements of paragraphs (a)(1) and (a)(2)
of this AD concurrently, except as provided by paragraph (b) of this
AD.
(1) Modify the thrust reverser doors in accordance with Fokker
Service Bulletin SBF100-78-010, Revision 1, dated April 26, 1994;
and
(2) Replace the Collins multifunction display units (MFDU)
having part number (P/N) 622-8047-412 or 622-8047-422 with new
MFDU's having P/N 622-8047-414 or 622-8047-423, respectively; as
applicable; in accordance with Fokker Service Bulletin SBF100-31-
036, dated February 7, 1994.
(b) Paragraph (a)(2) of this AD may be accomplished prior to
paragraph (a)(1) of this AD provided that a placard is installed on
the main instrument panel in accordance with Fokker Service Bulletin
SBF100-31-038, dated April 26, 1994, and removed, prior to further
flight, after accomplishment of the requirements of paragraph (a)(1)
of this AD.
(c) For airplanes that have been modified in accordance with
paragraphs (a)(1) and (a)(2) of this AD: No person may install a
Grumman Aerospace aft engine cowling having part number 1159P41440
on any airplane unless it has been previously modified in accordance
with Fokker Component Service Bulletin P41440-78-02, dated December
17, 1993, as revised by Fokker Component Service Bulletin Change
Notification P41440-78-02/001, dated February 25, 1995.
(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 2: Information concerning the existence of approved
alternative methods of 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.
Issued in Renton, Washington, on November 28, 1995.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-29443 Filed 12-1-95; 8:45 am]
BILLING CODE 4910-13-U
