[Federal Register Volume 61, Number 13 (Friday, January 19, 1996)]
[Proposed Rules]
[Pages 1294-1295]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-492]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-164-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 installation of
reinforcement plates under each hook latch fitting on the frame of each
large cargo door. For some airplanes, this proposal would require
inspection to detect cracking in the area around each hook latch
fitting, and repair, if necessary. This proposal is prompted by the
results of stress analyses and destructive tests which revealed that
fatigue-related cracking may develop in the vicinity of the hook latch
fittings on the frame of the large cargo doors. The actions specified
by the proposed AD are intended to prevent reduced structural integrity
of the frames of the cargo door due to fatigue cracking, which may lead
to the cargo door(s) opening while the airplane is in flight.
DATES: Comments must be received by February 21, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-164-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 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 95-NM-164-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-164-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 the results of stress analyses and
destructive tests on the frames of Model F28 Mark 0100 large cargo
doors have shown that fatigue-related cracking may develop in the area
of the hook latch fittings. Test data have shown that such cracking is
most likely to develop after 11,000 flight cycles. This condition, if
not detected and corrected in a timely manner, could result in reduced
structural integrity of the frames of the large cargo door, which may
lead to the cargo door(s) opening while the airplane is in flight.
Fokker has issued Service Bulletin SBF100-52-050, Revision 1, dated
September 14, 1994, which describes procedures for installing
reinforcement plates under each hook latch fitting on the frame of each
large cargo door. The RLD classified this service bulletin as mandatory
and issued Dutch airworthiness directive BLA 94-157 (A), dated November
24, 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, the
proposed AD would require installation of two reinforcement plates
under each hook latch fitting on the frame of each large cargo door.
The installation would be required to be accomplished in accordance
with the service bulletin described previously.
This AD also proposes to require, for certain airplanes, an
inspection to detect cracking in the area around each hook latch
fitting on the frame of each large cargo door and repair of any
cracking found, in accordance with a method approved by the FAA.
The FAA estimates that 100 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 4.5 work
hours per airplane to accomplish the proposed installation, and that
the average labor rate is $60 per work hour. Required parts would cost
approximately $10,000 per airplane. Based on these figures, the cost
impact of the proposed installation on U.S. operators is estimated to
be $1,027,000, or $10,270 per airplane.
The FAA estimates that it would take approximately 4.5 work hours
per airplane to accomplish the proposed inspection (that is required
for certain airplanes), and that the average labor
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rate is $60 per work hour. Based on these figures, the cost impact of
the proposed inspection is estimated to be $270 per airplane.
The cost impact figures discussed above are 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. 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 95-NM-164-AD.
Applicability: Model F28 Mark 0100 series airplanes, as listed
in Fokker Service Bulletin SBF100-52-050, Revision 1, dated
September 14, 1994, 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 use the authority
provided in paragraph (c) 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 prevent reduced structural integrity of the frame of the
large cargo door, which may lead to the cargo door(s) opening while
the airplane is in flight, accomplish the following:
(a) Prior to the accumulation of 11,000 total flight cycles or
within 500 flight cycles after the effective date of this AD,
whichever occurs later, install two reinforcement plates under each
hook latch fitting on the frame of each large cargo door, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-52-050, Revision 1, dated September 14, 1994.
(b) For airplanes that have accumulated 11,000 or more total
flight cycles at the time of compliance with paragraph (a) of this
AD: Concurrent with the accomplishment of the requirements of
paragraph (a) of this AD, perform an inspection to detect cracking
in the area around each hook latch fitting on the frame of each
large cargo door, in accordance with a method approved by the
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(1) If no cracking is detected, no further action is required by
this paragraph.
(2) If any cracking is detected, prior to completing the
requirements of paragraph (a) of this AD, repair in accordance with
a method approved by the Manager, Standardization Branch, ANM-113.
(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 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.
(d) 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 January 10, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-492 Filed 1-18-96; 8:45 am]
BILLING CODE 4910-13-U
