[Federal Register Volume 64, Number 187 (Tuesday, September 28, 1999)]
[Rules and Regulations]
[Pages 52219-52221]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25021]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-346-AD; Amendment 39-11337; AD 99-20-07]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark
0100 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Fokker Model F.28 Mark 0070 and Mark 0100
series airplanes, that currently requires revising the Airplane Flight
Manual to provide the flightcrew with instructions not to arm the
liftdumper system prior to commanding the landing gear to extend. This
amendment requires modification of the grounds of the shielding of the
wheelspeed sensor wiring of the main landing gear (MLG) and
installation of new electrical grounds for the wheelspeed sensor
channel of the anti-skid control box of the MLG. This amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
this AD are intended to prevent electromagnetic interference generated
by electrical wiring that runs parallel to the wheelspeed sensor
wiring, which could result in inadvertent deployment of the liftdumpers
during approach for landing or reduced brake pressure during low speed
taxiing, and consequent reduced controllability and performance of the
airplane.
DATES: Effective November 2, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 2, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep,
The Netherlands. This information may be examined 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.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 98-11-02,
amendment 39-10529 (63 FR 27197, May 18, 1998), which is applicable to
all Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, was
published in the Federal Register on April 16, 1999 (64 FR 18840). The
action proposed to require revising the Airplane Flight Manual (AFM) to
provide the flightcrew with instructions not to arm the liftdumper
system prior to commanding the landing gear to extend. The action also
proposed to require modification of the grounds of the shielding of the
wheelspeed sensor wiring of the main landing gear (MLG) and
installation of new electrical grounds for the wheelspeed sensor
channel of the anti-skid control box of the MLG.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Support for the Proposal
One commenter supports the proposed AD and another commenter
generally supports the proposal.
Request To Extend the Compliance Time for the Modification
One commenter requests that the compliance time for accomplishment
of the modification action specified by Fokker Service Bulletin SBF100-
32-067, Revision 1, dated July 6, 1998 [as cited in paragraph (b) of
the proposed AD], be extended from 6 to 12 months. The commenter
contends that an extension of the compliance time is necessary to
coincide with the 12-month compliance time specified in paragraph (c)
of the proposed AD for accomplishment of the installation of new
electrical grounds for the wheelspeed sensor channel of the anti-skid
control box of the MLG. The commenter contends that failure to extend
the compliance time to 12 months would force operators to take
airplanes out of service specifically to accomplish the modification,
and result in unnecessary operational costs.
The FAA does not concur with the commenter's request. The
manufacturer has informed the FAA that its discussions with operators
indicated that the modification could be accomplished prior to the
compliance time recommended in Fokker Service Bulletin SBF100-32-067,
which is March 1, 1999. Also, the related Dutch airworthiness directive
specifies a parallel compliance time of 6 months. Therefore, the FAA
finds a 6-month compliance time for accomplishing the modification to
be warranted, in that it represents an appropriate interval of time
allowable for affected airplanes to continue to operate without
compromising safety. However, under the provisions of paragraph (d) of
the final rule, the FAA may consider requests for adjustments to the
compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety.
[[Page 52220]]
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 131 Model F.28 Mark 0070 and Mark 0100
series airplanes of U.S. registry that will be affected by this AD.
For all airplanes, the actions that are currently required by AD
98-11-02 take approximately 1 work hour per airplane to accomplish, at
an average labor rate of $60 per work hour. Based on these figures, the
cost impact of the previously required actions on U.S. operators is
estimated to be $7,860, or $60 per airplane.
There are approximately 127 airplanes of U.S. Registry that will
require the modification and installation, and the new actions that are
required by this new AD will take approximately 33 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Required parts will cost between $755 and $1,236 per airplane. Based on
these figures, the cost impact of the new requirements of this AD on
U.S. operators is estimated to be between $347,345 and $408,432, or
between $2,735 and $3,216 per airplane.
The 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.
Regulatory Impact
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 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 removing amendment 39-10529 (63 FR
27197, May 18, 1998), and by adding a new airworthiness directive (AD),
amendment 39-11337, to read as follows:
99-20-07 Fokker Services B.V.: Amendment 39-11337. Docket 98-NM-
346-AD. Supersedes AD 98-11-02, Amendment 39-10529.
Applicability: All Model F.28 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
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 electromagnetic interference generated by electrical
wiring that runs parallel to the wheelspeed sensor wiring, which
could result in inadvertent deployment of the liftdumpers during
approach for landing or reduced brake pressure during low speed
taxiing, and consequent reduced controllability and performance of
the airplane, accomplish the following:
Restatement of Requirements of AD 98-11-02, Amendment 39-10529
(a) Within 5 days after June 2, 1998 (the effective date of AD
98-11-02), revise the Limitations and Normal Procedures sections of
the FAA-approved Airplane Flight Manual (AFM) in accordance with
paragraphs (a)(1) and (a)(2) of this AD. This may be accomplished by
inserting a copy of this AD in the AFM.
(1) Add the following information to section 5--NORMAL
PROCEDURES, sub-Section APPROACH AND LANDING, after the subject
APPROACH:
``BEFORE LANDING
WARNING: DO NOT ARM THE LIFTDUMPER SYSTEM BEFORE LANDING GEAR DOWN
SELECTION.
Selecting Landing Gear DOWN after arming the liftdumper system
may result in inadvertent deployment of the liftdumpers, because the
liftdumper arming test may be partially ineffective.''
(2) Add the following information to the LIMITATIONS section:
LIFTDUMPER SYSTEM
DO NOT ARM THE LIFTDUMPER SYSTEM BEFORE LANDING GEAR DOWN
SELECTION.''
New Requirements of this AD
Corrective Actions
(b) For Model F.28 Mark 0100 series airplanes having serial
numbers as listed in Fokker Service Bulletin SBF100-32-067, Revision
1, dated July 6, 1998: Within 6 months after the effective date of
this AD, modify the grounds of the shielding of the wheelspeed
sensor wiring of the main landing gear (MLG) in accordance with Part
1, 2, 3, or 4 of the Accomplishment Instructions of the service
bulletin, as applicable.
Note 2: Modifications accomplished prior to the effective date
of this AD in accordance with Fokker Service Bulletin SBF100-32-067,
dated March 12, 1993, are considered acceptable for compliance with
the requirements of paragraph (b) of this AD.
(c) For Model F.28 Mark 0100 series airplanes having serial
numbers as listed in Fokker Service Bulletin SBF100-32-037, Revision
2, dated December 4, 1998: Within 12 months after the effective date
of this AD, install new electrical grounds for the wheelspeed sensor
channel of the anti-skid control box of the MLG in accordance with
Part 1, 2, or 3 of the Accomplishment Instructions of the service
bulletin, as applicable.
Note 3: Installations accomplished prior to the effective date
of this AD in accordance with Fokker Service Bulletin SBF100-32-037,
dated November 12, 1990, or Revision 1, dated November 16, 1998, are
considered acceptable for compliance with the requirements of
paragraph (c) of this AD.
Alternative Methods of Compliance
(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,
[[Page 52221]]
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 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.
Special Flight Permits
(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 directives BLA 1998-100, dated August 31, 1998, and
1998-100/2, dated November 30, 1998.
Incorporation by Reference
(f) The actions shall be done in accordance with the following
Fokker service bulletins, as applicable, which contain the specified
effective pages:
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Revision level shown on
Service bulletin referenced Page No. page Date shown on page
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SBF100-32-067...................... 1-6 1.......................... July 6, 1998.
7-54 Original................... March 12, 1993.
1-3 2.......................... Dec. 4, 1998.
4-18 1.......................... Nov. 16, 1998.
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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 Services B.V., P.O. Box 231,
2150 AE Nieuw-Vennep, The Netherlands. 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 November 2, 1999.
Issued in Renton, Washington, on September 21, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-25021 Filed 9-27-99; 8:45 am]
BILLING CODE 4910-13-U
