Airworthiness Directives; Fokker Model F.27 Mark 050 Airplanes, 11014-11017 [E9-5007]
Download as PDF
<![CDATA[
11014
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I
certify that this AD:
(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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–06–02 Boeing: Amendment 39–15838.
Docket No. FAA–2008–1072; Directorate
Identifier 2008–NM–109–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective April 20, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
747–200C, 747–200F, 747–300, 747–400,
747SR, and 747SP series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 747–53A2682,
dated May 8, 2008.
Unsafe Condition
(d) This AD results from a wide-spread
fatigue damage assessment of Model 747
airplanes. We are issuing this AD to detect
and correct cracks in the fuselage skin that
can propagate and grow, resulting in a loss
of structural integrity and sudden
decompression of the airplane during flight.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Inspections/Repair
(f) Except as provided by paragraphs (g)
and (h) of this AD: At the applicable
compliance times specified in paragraph 1.E.
of Boeing Alert Service Bulletin 747–
53A2682, dated May 8, 2008 (‘‘the service
bulletin’’), do an external detailed inspection
or external high frequency eddy current
inspection for skin cracks at the shear tie end
fastener locations of the fuselage frames, and
repair any skin cracks before further flight, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of the service bulletin. Repeat
the applicable inspection thereafter at the
applicable interval specified in paragraph
1.E. of the service bulletin.
Exceptions to the Service Bulletin
(g) Where paragraph 1.E. of Boeing Alert
Service Bulletin 747–53A2682, dated May 8,
2008, specifies counting the compliance time
from ‘‘* * * the date on this service
bulletin,’’ this AD requires counting the
compliance time from the effective date of
this AD.
(h) If any crack is found in a structural
repair manual skin repair during any
inspection required by paragraph (f) of this
AD, and Boeing Alert Service Bulletin 747–
53A2682, dated May 8, 2008, specifies to
contact Boeing for repair: Before further
flight, repair using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Ivan
Li, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6437; fax (425) 917–6590.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Office. The AMOC approval letter must
specifically reference this AD.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(j) You must use Boeing Alert Service
Bulletin 747–53A2682, dated May 8, 2008, to
do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207; telephone 206–
544–9990; fax 206–766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–4973 Filed 3–13–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0214; Directorate
Identifier 2007–NM–343–AD; Amendment
39–15851; AD 2009–06–14]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.27 Mark 050 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
E:\FR\FM\16MRR1.SGM
16MRR1
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Fokker Model F.27 Mark 050 airplanes.
This AD requires measuring the length
of the extended portion of the sliding
member of the main landing gear,
performing an inspection for the
presence of lockwiring, and doing
corrective actions if necessary. This AD
results from a report that the sliding
member of the main landing gear has
been overextended after landing. We are
issuing this AD to detect and correct
improper installation of the lockwire on
the two lockbolts that hold the sliding
member end stop, which could result in
structural damage of the main gear and
loss of control of the airplane during the
landing roll, due to main landing gear
overextension.
DATES: This AD becomes effective
March 31, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 31, 2009.
We must receive comments on this
AD by April 15, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the
Netherlands; Telephone +31 (0)252–
627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices
@stork.com; Internet https://
www.myfokkerfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority—The
Netherlands (CAA–NL), which is the
airworthiness authority for the
Netherlands, notified us that an unsafe
condition might exist on certain Fokker
Model F.27 Mark 050 airplanes. The
CAA–NL advises that there has been a
report that the sliding member of the
main landing gear has been
overextended after landing. During
subsequent investigation, it was found
that an end stop had unscrewed itself to
a certain extent, and that there was no
lockwiring present on the two lockbolts
that hold the end stop. The unscrewed
end stop caused the gear torque links of
the main landing gear to come into an
overextended position against the
sliding member. This condition, if not
corrected, could result in structural
damage of the main gear and loss of
control of the airplane during the
landing roll, due to main landing gear
overextension.
Relevant Service Information
Fokker has issued Service Bulletin
SBF50–32–039, dated July 2, 2007,
which describes procedures for
measuring the length of the extended
portion of the sliding member of the
main landing gear, and performing an
inspection for the presence of
lockwiring on the lock bolts of the two
end stops, and doing corrective actions
if necessary. Corrective actions include
applying lockwiring if not installed or
installed incorrectly.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA–NL mandated the
service information and issued Dutch
airworthiness directive NL–2007–002,
dated October 31, 2007 (referred to after
this as ‘‘the MCAI’’), to ensure the
continued airworthiness of these
airplanes in the Netherlands.
Fokker Service Bulletin SBF50–32–
039, dated July 2, 2007, refers to
Messier-Dowty Service Bulletin F50–
32–62, dated January 17, 2007, as an
additional source of service information
for measuring the length of the extended
portion of the sliding member of the
main landing gear, performing an
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
11015
inspection for the presence of
lockwiring on the lock bolts of the two
end stops, and installing new
lockwiring when lockwiring is missing
or installed incorrectly.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Therefore, we are issuing this AD to
detect and correct improper installation
of the lockwire on the two lockbolts that
hold the sliding member end stop,
which could result in structural damage
of the main gear and loss of control of
the airplane during the landing roll, due
to main landing gear overextension.
This AD requires accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the AD and the MCAI.’’
Differences Between the AD and the
MCAI
The MCAI specifies only to inspect
for the presence of lockwiring if
overextension is found. However,
Messier-Dowty Service Bulletin F50–
32–62, dated January 17, 2007, also
specifies to inspect if the measurement
has increased between inspections. This
AD requires inspection for the presence
of lockwiring if overextension is found
or the measurement of the repeat
inspection has increased by 1.0 mm
compared to a previous inspection. We
have coordinated this difference with
CAA–NL.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required actions would take about 8
work hours per airplane, at an average
E:\FR\FM\16MRR1.SGM
16MRR1
11016
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
labor rate of $80 per work hour.
Required parts would cost about $1,082
per airplane. Based on these figures, the
estimated cost of the AD would be
$1,722 per airplane.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2009–0214; Directorate Identifier 2007–
NM–343–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect 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.
For the reasons discussed above, I
certify that the 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. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
■
2009–06–14 Fokker Services B.V.:
Amendment 39–15851. Docket No.
FAA–2009–0214; Directorate Identifier
2007–NM–343–AD.
Effective Date
(a) This AD becomes effective March 31,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model
F.27 Mark 050 airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
Unsafe Condition
(e) This AD results from a report that the
sliding member of the main landing gear has
been overextended after landing. We are
issuing this AD to detect and correct
improper installation of the lockwire on the
two lockbolts that hold the sliding member
end stop, which could result in structural
damage of the main gear and loss of control
of the airplane during the landing roll, due
to main landing gear overextension.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Measurement, Inspection, and Corrective
Actions
(g) Within 500 flight cycles after the
effective date of this AD, measure the length
of the extended portion of the sliding
member of the main landing gear in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF50–32–039, dated July 2, 2007. Repeat
the measurement at intervals not to exceed
500 flight cycles until the requirements of
paragraph (g) have been completed.
(h) At the applicable time in paragraph
(h)(1) or (h)(2) of this AD, perform an
inspection for the presence and correct
installation of lockwiring on the two end stop
lock bolts of the main landing gear, in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF50–32–039, dated July 2, 2007. If
lockwiring is not present or is not installed
correctly, install lockwiring before further
flight in accordance with Fokker Service
Bulletin SBF50–32–039, dated July 2, 2007.
(1) During any measurement required by
paragraph (g) of this AD, if overextension is
found, or the measurement has increased by
1.0 millimeter (mm) or more compared to the
previous measurement, inspect before further
flight.
(2) If no overextension is found and the
measurement has not increased by 1.0 mm or
more between measurements during the
measurements required by paragraph (g) of
this AD, inspect within 4,000 flight hours
after the effective date of this AD.
Note 1: Fokker Service Bulletin SBF50–32–
039, dated July 2, 2007, refers to MessierDowty Service Bulletin F50–32–62, dated
January 17, 2007, as an additional source of
service information for measuring the length
of the extended portion of the sliding
member of the main landing gear, performing
an inspection for the presence of lockwiring
on the lock bolts of the two end stops, and
installing new lockwiring.
(i) If, during any measurement required by
paragraph (g) of this AD, overextension is
found or the measurement has increased by
1.0 mm or more compared to the previous
measurement; or if, during any inspection
required by paragraph (h) of the AD,
lockwiring is not present or is not installed
correctly; submit a report to Fokker Services
B.V., Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the Netherlands;
facsimile (31) 252–627–211; e-mail
technicalservices.fokkerservices@stork.com,
E:\FR\FM\16MRR1.SGM
16MRR1
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
at the applicable time specified in paragraph
(i)(1) or (i)(2) of this AD. The report must
include any finding of overextension or
incorrect lockwiring to Fokker Services B.V.,
Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands;
facsimile (31) 252–627–211. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection or measurement was
done on or after the effective date of this AD:
Submit the report within 30 days after the
inspection or measurement, as applicable.
(2) If the inspection or measurement was
accomplished prior to the effective date of
this AD: Submit the report within 30 days
after the effective date of this AD.
(j) As of 5 months after the effective date
of this AD: No person may install a main
landing gear on any airplane unless Part B of
Messier-Dowty Service Bulletin F50–32–62,
dated January 17, 2007, has been
accomplished for that part.
Alternative Methods of Compliance
(AMOCs)
(k) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
Related Information
(l) Civil Aviation Authority—The
Netherlands (CAA–NL) Airworthiness
Directive NL–2007–002, dated October 31,
2007, also addresses the subject of this AD.
Material Incorporated by Reference
(m) You must use Fokker Service Bulletin
SBF50–32–039, dated July 2, 2007; and
Messier-Dowty Service Bulletin F50–32–62,
dated January 17, 2007; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For Fokker service information
identified in this AD, contact Fokker Services
B.V., Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the Netherlands;
Telephone +31 (0)252–627–350; fax +31
(0)252–627–211; e-mail
technicalservices.fokkerservices@stork.com;
Internet https://www.myfokkerfleet.com.
(3) For Messier-Dowty service information
identified in this AD, Messier-Dowty
Limited, Cheltenham Road, Gloucester, GL2
9QH, England; Telephone +44 (0) 1452
711732; fax +44 (0) 1452 713821.
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
(4) You may review copies of this service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(5) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5007 Filed 3–13–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
National Oceanic and Atmospheric
Administration
15 CFR Part 950
[Docket No: 090113018–9019–01]
RIN 0648–AX74
Schedule of Fees for Access to NOAA
Environmental Data, Information, and
Related Products and Services
AGENCY: National Environmental
Satellite, Data and Information Service
(NESDIS), National Oceanic and
Atmospheric Administration (NOAA),
Department of Commerce.
ACTION: Final rule.
SUMMARY: In this final rule, NESDIS
establishes a new schedule of fees for
the sale of its data, information, and
related products and services to users.
NESDIS is revising the fee schedule to
ensure that the fees accurately reflect
the costs of providing access to the
environmental data, information, and
related products and services. NESDIS
is authorized under 15 U.S.C. 1534 to
assess fees, up to fair market value, for
access to environmental data,
information, and products derived from,
collected, and/or archived by NOAA.
Other than depreciation, costs to
upgrade computer hardware and
software systems will not be included in
the fees charged to users.
DATES: Effective Date: May 1, 2009.
FOR FURTHER INFORMATION CONTACT:
Linda Neely (301) 713–3305.
SUPPLEMENTARY INFORMATION:
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
11017
Background
NESDIS operates NOAA’s National
Data Centers for Climate, Geophysics,
Oceans, and Coasts. Through these Data
Centers, NESDIS provides and ensures
timely access to global environmental
data from satellites and other sources,
provides information services, and
develops science products.
NESDIS maintains some 1,300 data
bases containing over 2,400
environmental variables at three
National Data Centers and seven World
Data Centers. These centers respond to
over 2,000,000 requests for these data
and products annually from over 70
countries. This collection of
environmental data and products is
growing exponentially, both in size and
sophistication.
Users have the ability to access the
data offline, online and through the
NESDIS e-Commerce System (NeS)
online store. Our ability to provide these
data, information, products and services
depends on user fees.
New Fee Schedule
The new fee schedule lists both the
current fee charged for each item and
the new fee to be charged to users that
will take effect beginning May 1, 2009.
The schedule applies to the listed
services provided by NESDIS on or after
this date, except for products and
services covered by a subscription
agreement in effect as of this date that
extends beyond this date. In those cases,
the increased fees will apply upon
renewal of the subscription agreement
or at the earliest amendment date
provided by the agreement.
NESDIS will continue to review the
user fees periodically, and will revise
such fees as necessary. Any future
changes in the user fees and their
effective date will be announced
through notice in the Federal Register.
Classification
This rule has been determined to be
not significant for purposes of E.O.
12866. The provisions of the
Administrative Procedure Act (5 U.S.C.
553) requiring notice of proposed
rulemaking and the opportunity for
public participation are inapplicable
because this rule falls within the
proprietary exception of subparagraph
(a)(2) of section 553. Further, no other
law requires that a notice of proposed
rulemaking and an opportunity for
public comment be given for this rule.
Because a notice of proposed
rulemaking and an opportunity for
public comment are not required to be
given for this rule under 5 U.S.C. 553 or
by any other law, the requirements of
E:\FR\FM\16MRR1.SGM
16MRR1
]]>Agencies
[Federal Register Volume 74, Number 49 (Monday, March 16, 2009)]
[Rules and Regulations]
[Pages 11014-11017]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-5007]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0214; Directorate Identifier 2007-NM-343-AD;
Amendment 39-15851; AD 2009-06-14]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.27 Mark 050 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
[[Page 11015]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Fokker Model F.27 Mark 050 airplanes. This AD requires
measuring the length of the extended portion of the sliding member of
the main landing gear, performing an inspection for the presence of
lockwiring, and doing corrective actions if necessary. This AD results
from a report that the sliding member of the main landing gear has been
overextended after landing. We are issuing this AD to detect and
correct improper installation of the lockwire on the two lockbolts that
hold the sliding member end stop, which could result in structural
damage of the main gear and loss of control of the airplane during the
landing roll, due to main landing gear overextension.
DATES: This AD becomes effective March 31, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 31,
2009.
We must receive comments on this AD by April 15, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Fokker
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands; Telephone +31 (0)252-627-350; fax +31 (0)252-
627-211; e-mail technicalservices.fokkerservices@stork.com; Internet
https://www.myfokkerfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority--The Netherlands (CAA-NL), which is
the airworthiness authority for the Netherlands, notified us that an
unsafe condition might exist on certain Fokker Model F.27 Mark 050
airplanes. The CAA-NL advises that there has been a report that the
sliding member of the main landing gear has been overextended after
landing. During subsequent investigation, it was found that an end stop
had unscrewed itself to a certain extent, and that there was no
lockwiring present on the two lockbolts that hold the end stop. The
unscrewed end stop caused the gear torque links of the main landing
gear to come into an overextended position against the sliding member.
This condition, if not corrected, could result in structural damage of
the main gear and loss of control of the airplane during the landing
roll, due to main landing gear overextension.
Relevant Service Information
Fokker has issued Service Bulletin SBF50-32-039, dated July 2,
2007, which describes procedures for measuring the length of the
extended portion of the sliding member of the main landing gear, and
performing an inspection for the presence of lockwiring on the lock
bolts of the two end stops, and doing corrective actions if necessary.
Corrective actions include applying lockwiring if not installed or
installed incorrectly.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA-NL
mandated the service information and issued Dutch airworthiness
directive NL-2007-002, dated October 31, 2007 (referred to after this
as ``the MCAI''), to ensure the continued airworthiness of these
airplanes in the Netherlands.
Fokker Service Bulletin SBF50-32-039, dated July 2, 2007, refers to
Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007, as an
additional source of service information for measuring the length of
the extended portion of the sliding member of the main landing gear,
performing an inspection for the presence of lockwiring on the lock
bolts of the two end stops, and installing new lockwiring when
lockwiring is missing or installed incorrectly.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Therefore, we are issuing this AD to detect and correct improper
installation of the lockwire on the two lockbolts that hold the sliding
member end stop, which could result in structural damage of the main
gear and loss of control of the airplane during the landing roll, due
to main landing gear overextension. This AD requires accomplishing the
actions specified in the service information described previously,
except as discussed under ``Differences Between the AD and the MCAI.''
Differences Between the AD and the MCAI
The MCAI specifies only to inspect for the presence of lockwiring
if overextension is found. However, Messier-Dowty Service Bulletin F50-
32-62, dated January 17, 2007, also specifies to inspect if the
measurement has increased between inspections. This AD requires
inspection for the presence of lockwiring if overextension is found or
the measurement of the repeat inspection has increased by 1.0 mm
compared to a previous inspection. We have coordinated this difference
with CAA-NL.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required actions would take about 8 work hours per
airplane, at an average
[[Page 11016]]
labor rate of $80 per work hour. Required parts would cost about $1,082
per airplane. Based on these figures, the estimated cost of the AD
would be $1,722 per airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2009-0214; Directorate Identifier 2007-NM-343-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2009-06-14 Fokker Services B.V.: Amendment 39-15851. Docket No. FAA-
2009-0214; Directorate Identifier 2007-NM-343-AD.
Effective Date
(a) This AD becomes effective March 31, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model F.27 Mark 050 airplanes,
certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Unsafe Condition
(e) This AD results from a report that the sliding member of the
main landing gear has been overextended after landing. We are
issuing this AD to detect and correct improper installation of the
lockwire on the two lockbolts that hold the sliding member end stop,
which could result in structural damage of the main gear and loss of
control of the airplane during the landing roll, due to main landing
gear overextension.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Measurement, Inspection, and Corrective Actions
(g) Within 500 flight cycles after the effective date of this
AD, measure the length of the extended portion of the sliding member
of the main landing gear in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF50-32-039, dated July 2,
2007. Repeat the measurement at intervals not to exceed 500 flight
cycles until the requirements of paragraph (g) have been completed.
(h) At the applicable time in paragraph (h)(1) or (h)(2) of this
AD, perform an inspection for the presence and correct installation
of lockwiring on the two end stop lock bolts of the main landing
gear, in accordance with the Accomplishment Instructions of Fokker
Service Bulletin SBF50-32-039, dated July 2, 2007. If lockwiring is
not present or is not installed correctly, install lockwiring before
further flight in accordance with Fokker Service Bulletin SBF50-32-
039, dated July 2, 2007.
(1) During any measurement required by paragraph (g) of this AD,
if overextension is found, or the measurement has increased by 1.0
millimeter (mm) or more compared to the previous measurement,
inspect before further flight.
(2) If no overextension is found and the measurement has not
increased by 1.0 mm or more between measurements during the
measurements required by paragraph (g) of this AD, inspect within
4,000 flight hours after the effective date of this AD.
Note 1: Fokker Service Bulletin SBF50-32-039, dated July 2,
2007, refers to Messier-Dowty Service Bulletin F50-32-62, dated
January 17, 2007, as an additional source of service information for
measuring the length of the extended portion of the sliding member
of the main landing gear, performing an inspection for the presence
of lockwiring on the lock bolts of the two end stops, and installing
new lockwiring.
(i) If, during any measurement required by paragraph (g) of this
AD, overextension is found or the measurement has increased by 1.0
mm or more compared to the previous measurement; or if, during any
inspection required by paragraph (h) of the AD, lockwiring is not
present or is not installed correctly; submit a report to Fokker
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE
Nieuw-Vennep, the Netherlands; facsimile (31) 252-627-211; e-mail
technicalservices.fokkerservices@stork.com,
[[Page 11017]]
at the applicable time specified in paragraph (i)(1) or (i)(2) of
this AD. The report must include any finding of overextension or
incorrect lockwiring to Fokker Services B.V., Technical Services
Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands;
facsimile (31) 252-627-211. Under the provisions of the Paperwork
Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and
Budget (OMB) has approved the information collection requirements
contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection or measurement was done on or after the
effective date of this AD: Submit the report within 30 days after
the inspection or measurement, as applicable.
(2) If the inspection or measurement was accomplished prior to
the effective date of this AD: Submit the report within 30 days
after the effective date of this AD.
(j) As of 5 months after the effective date of this AD: No
person may install a main landing gear on any airplane unless Part B
of Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007,
has been accomplished for that part.
Alternative Methods of Compliance (AMOCs)
(k) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
Related Information
(l) Civil Aviation Authority--The Netherlands (CAA-NL)
Airworthiness Directive NL-2007-002, dated October 31, 2007, also
addresses the subject of this AD.
Material Incorporated by Reference
(m) You must use Fokker Service Bulletin SBF50-32-039, dated
July 2, 2007; and Messier-Dowty Service Bulletin F50-32-62, dated
January 17, 2007; as applicable; to perform the actions that are
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of these documents in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For Fokker service information identified in this AD,
contact Fokker Services B.V., Technical Services Dept., P.O. Box
231, 2150 AE Nieuw-Vennep, the Netherlands; Telephone +31 (0)252-
627-350; fax +31 (0)252-627-211; e-mail
technicalservices.fokkerservices@stork.com; Internet https://
www.myfokkerfleet.com.
(3) For Messier-Dowty service information identified in this AD,
Messier-Dowty Limited, Cheltenham Road, Gloucester, GL2 9QH,
England; Telephone +44 (0) 1452 711732; fax +44 (0) 1452 713821.
(4) You may review copies of this service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-5007 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P
