[Federal Register Volume 62, Number 229 (Friday, November 28, 1997)]
[Proposed Rules]
[Pages 63294-63296]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-31161]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-264-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Mark 0070 and 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 all Fokker Model F28 Mark 0070 and
Mark 0100 series airplanes. This proposal would require a one-time
visual inspection to detect cracking of the brake torque tube lever,
and corrective action, if necessary. This proposal is prompted by the
issuance of mandatory continuing airworthiness information by a foreign
civil airworthiness authority. The actions specified by the proposed AD
are intended to prevent failure of the brake torque tube lever, which
could result in a disconnection between the brake pedal and brake
system, and consequent reduced directional controllability of the
airplane during landing.
DATES: Comments must be received by December 29, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-264-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 Service B.V., Technical Support Department, P.O.
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information
may be examined at the
[[Page 63295]]
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2110; fax (425) 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 97-NM-264-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. 97-NM-264-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Rijksluchtvaartdienst (RLD), which is the airworthiness
authority for the Netherlands, notified the FAA that an unsafe
condition may exist on all Fokker Model F28 Mark 0070 and Mark 0100
series airplanes. The RLD advises that it has received a report of the
failure of a brake torque tube lever, which occurred while the operator
of a Fokker Model F28 Mark 0100 series airplane was attempting to set
the parking brake. Subsequent inspection during routine maintenance on
two other airplanes in the fleet revealed small cracks in the same
lever. Such cracking, if not corrected, could result in failure of the
captain's left-hand brake torque tube lever, which could result in a
disconnection between the captain's left-hand brake pedal and left-hand
brake system, and consequent reduced directional controllability of the
airplane during landing.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF100-32-108, dated February 7,
1997, which describes procedures for a one-time visual inspection using
a mirror or borescope to detect cracking of the captain's left-hand
brake torque tube lever. The service bulletin also describes procedures
for replacement of any cracked lever with a new or serviceable lever,
or, as an alternative, replacement of the entire brake torque tube
assembly with a new or serviceable assembly. The RLD classified this
service bulletin as mandatory and issued Dutch airworthiness directive
1997-025 (A), dated February 28, 1997, in order to assure the continued
airworthiness of these airplanes in the Netherlands.
FAA's Conclusions
These airplane models are manufactured in the Netherlands and are
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.
Explanation of Requirements of Proposed Rule
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 accomplishment of
the actions specified in the service bulletin described previously.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Cost Impact
The FAA estimates that 131 Fokker Model F28 Mark 0070 and Mark 0100
series airplanes of U.S. registry would be affected by this proposed
AD, that it would take approximately 3 work hours per airplane to
accomplish the inspection proposed by this AD, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the proposed inspection of this AD on U.S. operators is
estimated to be $23,580, or $180 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.
Regulatory Impact
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:
[[Page 63296]]
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:
Fokker: Docket 97-NM-264-AD.
Applicability: All Model F28 Mark 0070 and Mark 0100 series
airplanes, 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 failure of the captain's left-hand brake torque tube
lever, which could result in a disconnection between the captain's
left-hand brake pedal and left-hand brake system, and consequent
reduced directional controllability of the airplane during landing,
accomplish the following:
(a) Perform a one-time visual inspection using a mirror or
borescope to detect cracking of the brake torque tube lever having
part number (P/N) D75669-001, in accordance with Fokker Service
Bulletin SBF100-32-108, dated February 7, 1997, at the time
specified in paragraph (a)(1) or (a)(2), as applicable, of this AD.
If any crack is detected, prior to further flight, replace either
the lever or the entire assembly with a new or serviceable
component, in accordance with the Accomplishment Instructions of the
service bulletin.
(1) For airplanes that have accumulated 15,000 or more total
flight cycles as of the effective date of this AD: Inspect within 30
days after the effective date of this AD.
(2) For airplanes that have accumulated fewer than 15,000 total
flight cycles as of the effective date of this AD: Inspect prior to
the accumulation of 10,000 total flight cycles, or within 2 months
after the effective date of this AD, whichever occurs later.
(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, International Branch, ANM-116, 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, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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.
Note 3: The subject of this AD is addressed in Dutch
airworthiness directive 1997-025 (A), dated February 28, 1997.
Issued in Renton, Washington, on November 20, 1997.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-31161 Filed 11-26-97; 8:45 am]
BILLING CODE 4910-13-U
