[Federal Register Volume 59, Number 76 (Wednesday, April 20, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-9340]
[[Page Unknown]]
[Federal Register: April 20, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-165-AD; Amendment 39-8885; AD 94-08-13]
Airworthiness Directives; Fokker Model F-28 Mark 0100 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Fokker Model F-28 Mark 0100 series airplanes,
that requires the installation of modified Flight Warning Computers and
Flight Augmentation Computers. This amendment is prompted by reports of
nuisance yaw-damper fault warnings and undetected horizontal trim
motion, and the development of improved computers that eliminate these
problems. The actions specified by this AD are intended to prevent
nuisance warnings in the cockpit and undetected trim motion, both of
which could compromise the safe takeoff of the airplane.
DATES: Effective May 20, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 20, 1994.
ADDRESSES: The service information referenced in this AD may be
obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street,
Alexandria, Virginia 22314. This information may be examined at the
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mark Quam, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)
227-2145; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations to include an airworthiness directive (AD) that is
applicable to certain Fokker Model F-28 Mark 0100 series airplanes was
published in the Federal Register on November 12, 1993 (58 FR 59968).
That action proposed to require the installation of modified Flight
Warning Computers (FWC) and Flight Augmentation Computers (FAC).
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposed rule.
Another commenter requests that the proposed rule be revised to
include an additional part-numbered FWC as an acceptable alternative
part for compliance. This commenter states that it has installed FWC's
having part number 80-0610-3-31, in accordance with Fokker Service
Bulletin SBF100-31-033, dated June 23, 1993, on its fleet of affected
airplanes. The FAA has reviewed this data and finds that FWC's having
part number 80-0610-3-31 are acceptable alternatives to those called
out in the proposal. The FAA has revised the final rule to indicate
that this.
This same commenter requests that the proposed rule be revised to
include the words ``or subsequent'' for all part numbers, so that
future designs of the components would be permitted to be installed as
alternatives to the specific part numbered components called out in the
AD. The FAA does not concur, since there would be no way to establish
that the inclusion of these words would prevent the installation of
incompatible components. For example, the ``Material Information''
portion of the referenced Fokker Service Bulletin SBF100-22-037,
concerning the replacement of FAC's, indicates that specific equipment
combinations (those having similar part numbers in the component
series) may not be compatible. For this reason, the FAA considers it
inappropriate to permit the indiscriminate installation of any future
component designs.
This same commenter requests that the proposed rule not require
accomplishment of the actions specifically in accordance with the
service bulletins; the service bulletins should be for reference only.
Although the commenter does not specify a particular reason for this
request, the FAA infers that (1) the commenter would like to install
improved or modified equipment versions of the same basic part number
series that may or may not be called out in a service bulletin; or (2)
the commenter would prefer that the rule permit installation of the
subject components in accordance with an operator's own methods. The
FAA does not concur. As for the first inference, the FAA has addressed
this in the previous paragraph. As for the second inference, the FAA
points out that the referenced service bulletins contain specific
wiring procedures necessary for installation of the components; the FAA
has determined that these procedures must be followed in order to
ensure proper installation.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 27 airplanes of U.S. registry will be
affected by this AD.
Installation of the new FWC will require approximately 46 work
hours to accomplish, at an average labor charge of $55 per work hour.
Required parts will cost approximately $450 per airplane. Based on
these figures, the total cost impact of the FWC installation on U.S.
operators is estimated to be $2,980 per airplane.
The requirement to replace the FAC will vary, depending upon the
configuration of the FAC installed. Additionally, operators have a
choice of two different FAC's to use as replacement installations:
Should an operator elect to install an FAC having part number 622-
7478-401MOD11, it will require approximately 1 work hour to accomplish,
at an average labor charge of $55 per work hour. Required parts will be
provided at no cost to the operator. Based on these figures, the total
cost impact of this specific installation requirement on U.S. operators
would be $55 per airplane.
Should an operator elect to install an FAC having part number 622-
7478-411, it will require approximately 52 work hours to accomplish, at
an average labor charge of $55 per work hour. Required parts will cost
approximately $2,515 per airplane. Based on these figures, the total
cost impact of this specific FAC installation requirement on U.S.
operators is estimated to be $5,375 per airplane.
Based on the figures discussed above, the total cost impact of this
proposed AD on U.S. operators would be between $3,005 and $8,355 per
airplane, or between $81,135 and $225,585 for the entire U.S. fleet.
The total cost impact figures discussed above are based on
assumptions that no operator has yet accomplished any of the
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted. However, the
FAA has been advised that at least one U.S. operator affected by the AD
has previously accomplished the required installations on most of its
fleet of airplanes. In light of this, the total future cost impact of
the rule is expected to be less than the figures indicated above.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-08-13 Fokker: Amendment 39-8885. Docket 93-NM-165-AD.
Applicability: Model F-28 Mark 0100 series airplanes; serial
numbers 11244 through 11348, inclusive; equipped with Flight Warning
Computer, P/N 80-0610-2-( ); or equipped with Flight Augmentation
Computer, part number (P/N) 622-7478-321 or P/N 622-7478-401;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent nuisance yaw-damper fault warnings and undetected
trim motion, accomplish the following:
(a) For airplanes having serial numbers 11244 through 11321
inclusive, 11323 through 11329 inclusive, 11331, and 11333; and
equipped with Flight Warning Computer (FWC) P/N 80-0610-2-( ):
Within one year after the effective date of this AD, remove the
currently installed FWC, modify the airplane, and install FWC P/N
80-0610-3-30, in accordance with Fokker Service Bulletin SBF100-31-
020, Revision 1, dated June 12, 1993.
Note 1: Installation accomplished prior to the effective date of
this AD in accordance with Fokker Service Bulletin SBF100-31-020,
dated May 24, 1991, is considered to be in compliance with this
paragraph.
Note 2: Installation of FWC P/N 80-0610-3-31, in accordance with
Fokker Service Bulletin SBF100-31-031, dated June 23, 1993, is
considered an acceptable alternative method of compliance with this
paragraph.
(b) For airplanes having serial numbers 11244 through 11339
inclusive, 11341, and 11342; and equipped with Flight Augmentation
Computer (FAC) P/N 622-7478-321: At the same time as, or prior to
further flight after, accomplishing the requirements of paragraph
(a) of this AD, remove the currently installed FAC and replace it
with either of the following:
(1) FAC P/N 622-7478-401MOD11, in accordance with Fokker Service
Bulletin SBF100-22-032, dated September 2, 1991; or
(2) FAC P/N 622-7478-411, in accordance with Fokker Service
Bulletin SBF100-22-037, dated May 31, 1993. Equipment combinations
listed in that service bulletin must be adhered to.
(c) For airplanes having serial numbers 11244 through 11348
inclusive, and equipped with FAC P/N 622-7478-401: Within one year
after the effective date of this AD, remove the currently installed
FAC and replace it with either of the following:
(1) FAC P/N 622-7478-401MOD11, in accordance with Fokker Service
Bulletin SBF100-22-032, dated September 2, 1991; or
(2) FAC P/N 622-7478-411, in accordance with Fokker Service
Bulletin SBF100-22-037, dated May 31, 1993. Equipment combinations
listed in that service bulletin must be adhered to.
(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, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(e) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(f) The installations shall be done in accordance with Fokker
Service Bulletin SBF100-22-032, dated September 2, 1991; Fokker
Service Bulletin SBF100-22-037, dated May 31, 1993, and Fokker
Service Bulletin SBF100-31-020, Revision 1, dated June 12, 1993,
which contains the following list of effective pages:
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Revision level Date shown on
Page No. shown on page page
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1, 2, 5-12, 17, 19A, 19B, 22-24, 32, 1............... June 12, 1993.
34, 36.
3, 4, 13-16, 18, 19, 20, 21, 25-31, Original........ May 24, 1991.
33, 35.
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This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199
North Fairfax Street, Alexandria, Virginia 22314. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on May 20, 1994.
Issued in Renton, Washington, on April 13, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-9340 Filed 4-19-94; 8:45 am]
BILLING CODE 4940-13-U
