[Federal Register Volume 63, Number 219 (Friday, November 13, 1998)]
[Proposed Rules]
[Pages 63423-63425]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30333]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-276-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
[[Page 63424]]
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Fokker Model F.28 Mark
0070 and 0100 series airplanes. This proposal would require a one-time
visual inspection to detect discrepancies of the components of the
torque link apex joint and shimmy damper attachments of the main
landing gear (MLG), and repair or replacement of any discrepant
component with a new or serviceable component. This proposal is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
the proposed AD are intended to prevent heavy vibration and possible
damage to the components of the MLG, and consequent reduced
controllability of the airplane during takeoff and landing.
DATES: Comments must be received by December 14, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-276-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 Services B.V., Technical Support Department, P.O.
Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information
may be examined at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
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 98-NM-276-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-114, Attention: Rules
Docket No. 98-NM-276-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 certain Fokker Model F.28 Mark 0070 and 0100
series airplanes. The RLD advises that it received a report of heavy
vibration coming from the main landing gear (MLG) during landing.
Investigation revealed that the cause of the heavy vibration was
attributed to the nut of the apex bolt becoming detached from the apex
pin, which resulted in disconnection of the upper and lower torque
links of the right-hand MLG at the apex joint. Subsequent
investigations of other Fokker Model F.28 series airplanes, equipped
with Menasco MLG's, revealed loss of torque of the apex pin of the
torque links and, in some cases, loss of torque of the shimmy damper
attachment bolts. These conditions, if not corrected, could result in
heavy vibration and possible damage to the components of the MLG, and
consequent reduced controllability of the airplane during takeoff or
landing.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF100-32-113, dated May 28,
1998, which describes procedures for a one-time visual inspection to
detect discrepancies of the components of the torque link apex joint
and shimmy damper attachments of the MLG, and repair or replacement of
any discrepant component with a new or serviceable component.
Discrepancies may include incorrect positioning of the apex pin,
misalignment of the slotted locking nut, loss of torque of the bolts,
or damage to the locking plate and apex bolt. The service bulletin also
recommends informing Fokker Services of inspection results.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition. The RLD
classified this service bulletin as mandatory and issued Dutch
airworthiness directive BLA 1998-058 (A), dated May 29, 1998, in order
to assure the continued airworthiness of these airplanes in the
Netherlands.
Other Relevant Rulemaking
On October 7, 1998, the FAA issued AD 98-21-33, amendment 39-10841
(63 FR 55527, October 16, 1998), applicable to all Fokker Model F.28
Mark 0070 and 0100 series airplanes, to require a one-time inspection
of the torque links of the MLG assemblies to determine if the lockwire
is present on the apex bolt, and corrective action, if necessary.
However, this proposed AD would not affect the current requirements of
that previously issued AD.
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.
Cost Impact
The FAA estimates that 131 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 2 work
hours per
[[Page 63425]]
airplane to accomplish the proposed inspection, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the proposed AD on U.S. operators is estimated to be $15,720,
or $120 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.
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:
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 Services B.V.: Docket 98-NM-276-AD.
Applicability: Model F.28 Mark 0070 and 0100 series airplanes,
as listed in Fokker Service Bulletin SBF100-32-113, dated May 28,
1998; 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 request approval for an
alternative method of compliance in accordance with paragraph (d) 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 heavy vibration and possible damage to the components
of the main landing gear (MLG), and consequent reduced
controllability of the airplane during takeoff or landing,
accomplish the following:
(a) Within 45 days after the effective date of this AD, perform
a one-time visual inspection to detect discrepancies of the
components of the torque link apex joint and shimmy damper
attachments of the MLG, in accordance with Fokker Service Bulletin
SBF100-32-113, dated May 28, 1998. If any discrepancy is detected,
prior to further flight, repair or replace any discrepant component
with a new or serviceable component, in accordance with the service
bulletin.
Note 2: In paragraph 2.F.(10) of the Accomplishment Instructions
of Fokker Service Bulletin SBF100-32-113, dated May 28, 1998, the
parenthetical phrase that recommends the size of torque wrench to
use, should read ``* * * (0 to 75 lbf ft),'' rather than ``* * * (0
to 75 lbf in)''.
(b) Submit a report of the inspection findings (positive or
negative) to Fokker Services B.V., Technical Services, Attn.:
Manager Airline Support, P.O. Box 75047, 1117 ZN Schiphol-Oost, the
Netherlands; Fax No. 3120605200; at the time specified in paragraph
(b)(1) or (b)(2) of this AD, as applicable. Information collection
requirements contained in this regulation have been approved by the
Office of Management and Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have
been assigned OMB Control Number 2120-0056.
(1) For airplanes on which the inspection required by paragraph
(a) of this AD is accomplished after the effective date of this AD:
Submit a report within 10 days after accomplishing the inspection
required by paragraph (a) of this AD.
(2) For airplanes on which the inspection required by paragraph
(a) of this AD has been accomplished prior to the effective date of
this AD: Submit a report within 30 days after the effective date of
this AD.
(c) As of the effective date of this AD, no person shall install
on any airplane a Menasco MLG having part number (P/N) 41050-5, -6,
-7, or -8; or P/N 41060-1 or -2; unless it has been inspected in
accordance with paragraph (a) of this AD.
(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, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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.
Note 4: The subject of this AD is addressed in Dutch
airworthiness directive BLA 1998-058(A), dated May 29, 1998.
Issued in Renton, Washington, on November 5, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-30333 Filed 11-12-98; 8:45 am]
BILLING CODE 4910-13-P
