[Federal Register Volume 64, Number 49 (Monday, March 15, 1999)]
[Proposed Rules]
[Pages 12772-12774]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-6210]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-328-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).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Fokker Model F.28 Mark 0070
and 0100 series airplanes. This proposal would require modification of
the electrical wiring of the flight warning computer (FWC), and
installation of upgraded computer software into the FWC. 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 certain nuisance
alerts generated by the FWC and to ensure annunciation of certain
flight alerts by the FWC during initial climb. Such nuisance alerts or
failures to annunciate certain alerts could result in an improper
response by the flight crew and consequent reduced controllability of
the airplane.
DATES: Comments must be received by April 14, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-328-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-328-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-328-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 F.28 Mark 0070 and 0100 series
airplanes. The RLD advises that in-service experience has indicated
that certain nuisance flight alerts may be generated by the flight
warning computer (FWC) during critical flight phases. Investigation
revealed that the nuisance flight alerts are a result of certain
conditions established in an earlier version of the computer software
of the FWC, which allows a flight-phase transitional delay (in some
cases up to 8 seconds) between the moment all relevant input conditions
are met and the moment the actual flight-phase switching occurs. Such
nuisance flight alerts could prompt the flight crew to unnecessarily
abort takeoffs at high speeds.
The RLD also advises that annunciation of the REVERSER ENG 1(2)
alerts is suppressed during initial climb between 400 and 1,000 feet
off the ground. During this flight phase, there is no warning to the
flight crew enabling them to distinguish between a perceived
autothrottle malfunction and an actual thrust reverser deployment.
These conditions (nuisance alerts and failures to annunciate flight
alerts), if not corrected, could result in an improper response by the
flight crew and consequent reduced controllability of the airplane.
Explanation of Relevant Service Information
The manufacturer has issued Fokker Service Bulletin SBF100-31-047,
Revision 1, dated March 21, 1997, which describes, among other things,
procedures for modification of the electrical wiring of the FWC. The
modification involves removing the FWC and installing additional
electrical wiring to accommodate the revised configuration of the FWC.
Fokker also has issued Service Bulletin SBF100-31-051, dated August
15, 1998, which describes procedures for installation of an upgraded
computer software version (V11.45) into the FWC. (Fokker Service
Bulletin SBF100-31-051 refers to AlliedSignal Grimes Aerospace Service
Bulletin 80-0610-31-0031, dated May 14, 1998, as an additional source
of service information for installation of the upgraded computer
software version into the FWC.)
Accomplishment of the actions specified in the Fokker service
bulletins described above is intended to
[[Page 12773]]
adequately address the identified unsafe condition. The RLD classified
these service bulletins as mandatory and issued Dutch airworthiness
directive BLA 1998-110, dated August 31, 1998, 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 Sec. 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 Fokker service bulletins described
previously, except as discussed below.
Differences Between Proposed AD and Relevant Service Information
Operators should note that Fokker Service Bulletin SBF100-31-047,
Revision 1, recommends, in addition to the procedures described
previously, the installation of computer software version V10.40 into
the FWC. However, the only procedure of that service bulletin proposed
by this AD is modification of the electrical wiring of the FWC. In
developing the appropriate requirements for this proposed AD, the FAA
has determined that it is not necessary to install computer software
version V10.40, since the later version V11.45 is available and is
required to be installed by this proposed AD.
Cost Impact
The FAA estimates that 129 airplanes of U.S. registry would be
affected by this proposed AD, and that it would take approximately 6
work hours per airplane to accomplish the proposed modification, and
that the average labor rate is $60 per work hour. Required parts would
cost approximately $93 per airplane. Based on these figures, the cost
impact of the modification proposed by this AD on U.S. operators is
estimated to be $58,437, or $453 per airplane.
It also would take approximately 1 work hour per airplane to
accomplish the proposed installation, at an average labor rate of $60
per work hour. Required parts would cost approximately $1,500 per
airplane. Based on these figures, the cost impact of the installation
proposed by this AD on U.S. operators is estimated to be $201,240, or
$1,560 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 Services B.V.: Docket 98-NM-328-AD.
Applicability: All Model F.28 Mark 0070 and 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
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 certain nuisance alerts generated by the flight
warning computer (FWC) and to ensure annunciation of certain flight
alerts by the FWC during initial climb, which could result in an
improper response by the flight crew and consequent reduced
controllability of the airplane, accomplish the following:
(a) Within 18 months after the effective date of this AD, modify
the electrical wiring of the FWC in accordance with Part 1 or 2, as
applicable, of the Accomplishment Instructions of Fokker Service
Bulletin SBF100-31-047, Revision 1, dated March 21, 1997.
Note 2: It is not necessary to install computer software version
V10.40 into the FWC, since a later version is available and is
required to be installed by this AD.
(b) Concurrent with the accomplishment of the requirements of
paragraph (a) of this AD, install upgraded computer software version
V11.45 into the FWC in accordance with Fokker Service Bulletin
SBF100-31-051, dated August 15, 1998.
Note 3: AlliedSignal Grimes Aerospace has issued Service
Bulletin 80-0610-31-0031, dated May 14, 1998, as an additional
source of service information for installation of the upgraded
computer software version into the FWC.
(c) As of the effective date of this AD, no person shall install
on any airplane a flight warning computer, unless it has been
modified in accordance with 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
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send it to the Manager, International Branch, ANM-116.
Note 4: 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 5: The subject of this AD is addressed in Dutch
airworthiness directive BLA 1998-110, dated August 31, 1998.
Issued in Renton, Washington, on March 9, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-6210 Filed 3-12-99; 8:45 am]
BILLING CODE 4910-13-U
