[Federal Register Volume 61, Number 167 (Tuesday, August 27, 1996)]
[Proposed Rules]
[Pages 44004-44006]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-21745]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-80-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300,
400, 500, 600, and 700 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 F27 Mark 100,
200, 300, 400, 500, 600, and 700 series airplanes. This proposal would
require replacement of certain rudder horn assemblies with a new
assembly. For certain airplanes, the proposed AD also would require
replacement of certain rudder control rods with a new rod. This
proposal is prompted by reports of cracked rudder horns and a cracked
rudder control rod, caused by impact overload. The actions specified by
the proposed AD are intended to prevent such an overload and consequent
cracking of the subject parts, which could result in reduced structural
integrity of the rudder horn assembly or loss of rudder control; this
condition could lead to reduced controllability of the airplane.
[[Page 44005]]
DATES: Comments must be received by October 7, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-80-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 96-NM-80-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. 96-NM-80-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 all Fokker Model F27 Mark 100, 200, 300, 400,
500, 600, and 700 series airplanes. The RLD advises it has received
reports of cracked rudder horns and a cracked rudder control rod found
on these airplanes. Investigation revealed the cause of such cracking
has been attributed to an impact overload on the rudder horn assembly.
The existing design of the rudder horn assembly allows the rudder to
swing around in heavy gust conditions. The inertia of the rudder
swinging movement can cause an impact overload when one of the rudder
limit stops is hit. This condition, if not corrected, could result in
reduced structural integrity of the rudder horn assembly or loss of
rudder control, and, consequently, lead to reduced controllability of
the airplane.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin F27/27-131, Revision 1, dated
June 15, 1994, which describes procedures for replacement of the rudder
horn assembly, having part number (P/N) 3401-042-901 or -401, with a
new rudder horn assembly, having P/N F3402-070-407. The new rudder horn
is made of a stronger aluminum alloy material. Additionally, for
certain airplanes, the service bulletin recommends replacement of the
rudder control rod, having P/N 5233-018-xxx, with a new rudder control
rod, having P/N F8507-052-403. The new control rod contains regreasable
bearings which are less sensitive to seizure. The RLD classified this
service bulletin as mandatory and issued Dutch airworthiness directive
BLA 94-105 (A), dated August 5, 1994, in order to assure the continued
airworthiness of these airplanes in the Netherlands.
FAA's Conclusion
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.
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, the
proposed AD would require replacement of certain rudder horn assemblies
with a new rudder horn assembly. For certain airplanes, the proposed AD
also would require replacement of certain rudder control rods with a
new rudder control rod. The actions would be required to be
accomplished in accordance with the service bulletin described
previously.
Cost Impact
The FAA estimates that 34 Fokker Model F27 Mark 100, 200, 300, 400,
500, 600, and 700 series airplanes of U.S. registry would be affected
by this proposed AD.
It would take approximately 7 work hours per airplane to accomplish
the proposed replacement of the rudder horn assembly, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $2,565 per airplane. Based on these figures, the cost
impact of the replacement of the rudder horn assembly proposed by this
AD on U.S. operators is estimated to be $101,490, or $2,985 per
airplane.
There currently are no Fokker Model F27 Mark 100, 200, 300, 400,
500, 600, or 700 series airplanes on the U.S. Register that would
require the replacement of the rudder control rod. The only airplanes
that would require this replacement currently are operated by non-U.S.
operators under foreign registry; therefore, they are not directly
affected by this AD action. However, the FAA considers that inclusion
of that requirement in this proposed rule is necessary to ensure that
the unsafe condition is addressed in the event that any of these
airplanes are imported and placed on the U.S. Register in the future.
Should any of those airplanes (having serial numbers 10102, and
10105 through 10165, inclusive) be imported and placed on the U.S.
Register in the future, it would take approximately 5 work hours per
airplane to accomplish the proposed replacement of the rudder control
rod, at an average labor rate of $60 per work hour. Required parts
would cost approximately $635 per
[[Page 44006]]
airplane. Based on these figures, the cost impact of the replacement of
the rudder control rod proposed by this AD on U.S. operators is
estimated to be $935 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:
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 96-NM-80-AD.
Applicability: All Model F27 Mark 100, 200, 300, 400, 500, 600,
and 700 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 an impact overload and consequent cracking of the
subject parts, which could result in reduced structural integrity of
the rudder horn assembly or loss of rudder control, and,
consequently, lead to reduced controllability of the airplane,
accomplish the following:
(a) Within 18 months after the effective date of this AD,
accomplish paragraph (a)(1) and (a)(2) of this AD, as applicable, in
accordance with Fokker Service Bulletin F27/27-131, Revision 1,
dated June 15, 1994.
(1) For all airplanes: Replace the rudder horn assembly, having
part number (P/N) 3401-042-901 or 3401-042-401, with a new rudder
horn assembly, having P/N F3402-070-407, in accordance with Part 1
of the Accomplishment Instructions of the service bulletin.
(2) For airplanes having serial numbers 10102, and 10105 through
10165 inclusive: Replace the rudder control rod, having P/N 5233-
018-xxx, with a new rudder control rod, having P/N F8507-052-403, in
accordance with Part 2 of the Accomplishment Instructions of the
service bulletin.
(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, 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.
(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 August 20, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-21745 Filed 8-26-96; 8:45 am]
BILLING CODE 4910-13-U
