Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes, 73347-73351 [05-23779]
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73347
Rules and Regulations
Federal Register
Vol. 70, No. 237
Monday, December 12, 2005
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
List of Subjects in 7 CFR Part 1902
DEPARTMENT OF TRANSPORTATION
Accounting, banks, banking, grant
programs-housing and community
development, loan programsagriculture, loan programs-housing and
community development.
Federal Aviation Administration
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
I
DEPARTMENT OF AGRICULTURE
PART 1902–SUPERVISED BANK
ACCOUNTS
For reasons set forth in the preamble,
Chapter XVIII, title 7, Code of Federal
Regulations is amended as follows:
Rural Housing Service
1. The authority citation for part 1902
continues to read as follows:
I
Rural Business-Cooperative Service;
Rural Utilities Service
Farm Service Agency
Authority: 5 U.S.C. 301; 7 U.S.C. 1989; 7
U.S.C. 6991, et seq.; 42 U.S.C. 1480;
Reorganization Plan No. 2 of 1953 (5 U.S.C.
App.).
7 CFR Part 1902
Disbursement of Funds; Correction
Rural Housing Service, Rural
Business-Cooperative Service, Rural
Utilities Service, and Farm Service
Agency, USDA.
Subpart A—Supervised Bank
Accounts of Loan, Grant, and Other
Funds
I
AGENCY:
ACTION:
2. Section 1902.4 is amended by
revising paragraph (a)(5) to read as
follows:
Final rule, correction.
This action corrects a final
rule that was published in the Federal
Register on Wednesday, October 12,
2005.
SUMMARY:
DATES:
December 12, 2005.
FOR FURTHER INFORMATION CONTACT:
Renita Bolden, Management Analyst,
Regulations and Paperwork
Management Branch, Support Services
Division, U.S. Department of
Agriculture, Stop 0742, 1400
Independence Avenue, SW.,
Washington, DC 20250–0742;
Telephone: 202–692–0035.
SUPPLEMENTARY INFORMATION:
Background
In FR rule document 05–20357
published October 12, 2005 (70 FR
59224), the Agencies published a final
rule revising their disbursement of
funds regulations to reflect current
disbursement methodologies.
§ 1902.4 Establishing MFH reserve
accounts in a supervised bank account.
(a) * * *
(5) Financial institutions. The reserve
account must be maintained in
authorized financial institutions set out
in 7 CFR part 3560, subpart G; e.g.,
banks, savings associations, credit
unions, brokerage firms, mutual funds.
Generally, any financial institution may
be used provided invested or deposited
funds are insured to protect against theft
and dishonesty. The reserve account
funds need not be Federally insured, but
must be otherwise covered by nonFederal insurance against theft and
dishonesty.
*
*
*
*
*
Dated: December 6, 2005.
Russell T. Davis,
Administrator, Rural Housing Service.
[FR Doc. 05–23886 Filed 12–9–05; 8:45 am]
BILLING CODE 3410–XV–P
Need for Correction
As published, the final rule contained
an incorrect reference that may prove to
be misleading. This action will correct
the error to insure that the accurate
information is received.
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14 CFR Part 39
[Docket No. FAA–2005–23214; Directorate
Identifier 2001–NM–338–AD; Amendment
39–14399; AD 2005–25–06]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F27 Mark 050 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Fokker Model F27
Mark 050 series airplanes. The existing
AD currently requires using a torque
wrench to repetitively tighten the
screws for the attachment of the leading
edges of the elevators, rudder, and
ailerons. This new AD requires the same
actions as those of the existing AD, but
with reductions in the intervals for
repetitive actions. This AD also requires
modifying the elevator, rudder, and
aileron leading edge attachments with
additional locking devices. This AD
results from a report of an in-flight
vibration caused by a loose leading edge
section of the elevator. We are issuing
this AD to prevent binding of the flight
controls caused by loose attachment
screws, which could result in reduced
controllability of the airplane.
DATES: This AD becomes effective
December 27, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 27, 2005.
On January 21, 2000 (65 FR 695,
January 6, 2000), the Director of the
Federal Register approved the
incorporation by reference of certain
other publications listed in the
regulations.
We must receive comments on this
AD by February 10, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
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• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9:00 a.m. and 5:00 p.m.,
Monday through Friday, except Federal
holidays.
Contact Fokker Services B.V., P.O.
Box 231, 2150 AE Nieuw-Vennep, the
Netherlands, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 28, 1999, we issued AD
99–27–13, amendment 39–11494 (65 FR
695, January 6, 2000), for all Fokker
Model F27 Mark 050 series airplanes.
That AD requires using a torque wrench
to repetitively tighten the screws for the
attachment of the leading edges of the
elevators, rudder, and ailerons. That AD
resulted from an issuance of mandatory
continuing airworthiness information by
a foreign civil airworthiness authority.
We issued that AD to prevent loose
attachment screws on the leading edges
of the elevators, rudder, and ailerons
due to vibration, which could result in
interference with adjacent structure and
consequent reduced controllability of
the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 99–27–13, the
Civil Aviation Authority—The
Netherlands (CAA–NL), which is the
airworthiness authority for the
Netherlands, notified us that an
additional further unsafe condition may
exist on all Fokker Model F27 Mark 050
airplanes. The CAA–NL advises that an
operator reported in-flight vibration,
which was caused by one loose elevator
leading edge section. The airplane was
found to have been inspected only
seven months before the incident,
which was within the original 12-month
inspection interval of the existing AD.
Further investigation by the
manufacturer showed that the selflocking properties of the attachment
screws gradually decrease when
tightened repeatedly as required by the
procedures in the existing AD. This
condition, if not corrected, could result
in binding of the flight controls caused
by loose attachment screws, which
could cause reduced controllability of
the airplane.
Relevant Service Information
Fokker Services B.V. has issued
bulletins in the following table.
FOKKER SERVICE BULLETINS
Fokker Services Bulletin—
Describes procedures for—
SBF50–55–007,
2002.
SBF50–55–008,
2002.
SBF50–55–009,
2002.
SBF50–55–010,
2002.
SBF50–57–020,
2002.
SBF50–57–021,
2002.
Revision 2, dated June 17,
Tightening the attachment screws of the elevators’ leading edges.
Revision 3, dated June 17,
Modifying the elevator attachments by installing additional locking devices for the elevators’
leading edges.
Tightening the attachment screws for the rudder’s leading edge.
Revision 2, dated June 17,
Revision 2, dated June 17,
Revision 2, dated June 17,
Revision 2, dated June 17,
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 2000–131/2,
dated July 31, 2002, to ensure the
continued airworthiness of these
airplanes in the Netherlands.
Fokker Service Bulletin SBF50–55–
010, Revision 2, refers to Fokker Service
Bulletin SBF50–55–011, dated October
29, 2001, as an additional source of
service information for modifying the
rudder attachments.
Fokker Service Bulletin SBF50–57–
021, Revision 2, refers to Fokker Service
Bulletin SBF50–57–025, dated October
29, 2001, as an additional source of
service information for modifying the
aileron attachments.
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Modifying the rudder attachments by installing additional locking devices for the rudder’s leading edge.
Tightening the attachment screws for the ailerons’ leading edges.
Modifying the aileron attachments by installing additional locking devices for the ailerons’ leading edges.
FAA’s Determination and Requirements
of this AD
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 CAA–NL
has kept the FAA informed of the
situation described above. We have
examined the CAA–NL’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
for products of this type design that are
certificated for operation in the United
States.
Therefore, we are issuing this AD to
prevent binding of the flight controls
caused by loose attachment screws,
which could result in reduced
controllability of the airplane. This AD
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requires accomplishing the actions
specified in the service information
described previously.
This AD supersedes AD 99–27–13.
This AD continues to require the same
actions as the existing AD, but at
reduced repetitive intervals. This AD
also requires a new modification for the
elevators, rudder, and aileron
attachments, which terminates the
repetitive inspection requirements of
this AD. This AD requires
accomplishing the actions specified in
the service bulletins described
previously.
Change To Existing AD
This AD will retain all requirements
of AD 99–27–13. Since AD 99–27–13
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifiers
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Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations
have changed in this AD, as listed in the
following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
99–27–13
paragraph (a) ............
paragraph (b) ............
paragraph (c) ............
Corresponding requirement in this proposed AD
paragraph (f).
paragraph (g).
paragraph (h).
Explanation of Change to Applicability
We have revised the applicability of
the proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
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.
73349
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.
The following table provides the
estimated costs to comply with this AD
for any affected airplane that might be
imported and placed on the U.S.
Register in the future.
ESTIMATED COSTS
Work
hours
Action
Tightening (required by AD 99–27–13) ...........................
Modification (new action) .................................................
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 that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2005–23214; Directorate Identifier
2001–NM–338–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
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Average labor
rate per hour
12
37
Parts cost
$65
65
None ...................................
$1,025 to 3,372 ..................
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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,
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Cost per airplane
$780, per inspection cycle
$3,430 to 5,777
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–11494 (65
FR 695, January 6, 2000) and by adding
the following new airworthiness
directive (AD):
I
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Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations
2005–25–06 Fokker Services B.V.:
Amendment 39–14399. Docket No.
FAA–2005–23214; Directorate Identifier
2001–NM–338–AD.
Effective Date
(a) This AD becomes effective December
27, 2005.
Affected ADs
(b) This AD supersedes AD 99–27–13.
Applicability
(c) This AD applies to all Fokker Model
F27 Mark 050 airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from a report of an inflight vibration caused by a loose leading
edge section of the elevator. We are issuing
this AD to prevent binding of the flight
controls caused by loose attachment screws,
which could result in reduced controllability
of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 99–
27–13
Repetitive Corrective Action
(f) Within 30 days after January 21, 2000
(the effective date of AD 99–27–13), use a
torque wrench to tighten the screws for the
attachment of the leading edges of the
elevators in accordance with Fokker Service
Bulletin SBF50–55–007, dated June 5, 1998;
or Revision 2, dated June 17, 2002. After the
effective date of this AD, only Revision 2 may
be used. Repeat the tightening thereafter at
intervals not to exceed 12 months until the
initial tightening required by paragraph (i) of
this AD is accomplished.
(g) Within 24 months after January 21,
2000, use a torque wrench to tighten the
screws for the attachment of the leading
edges of the rudder in accordance with
Fokker Service Bulletin SBF50–55–009,
Revision 1, dated July 23, 1999; or Revision
2, dated June 17, 2002. After the effective
date of this AD, only Revision 2 may be used.
Repeat the tightening thereafter at intervals
not to exceed 4,000 flight hours, or 24
months, whichever occurs first, until the
initial tightening required by paragraph (j) of
this AD is accomplished.
(h) Within 6 months after January 21, 2000,
use a torque wrench to tighten the screws for
the attachment of the leading edges of the
ailerons in accordance with Fokker Service
Bulletin SBF50–57–020, Revision 1, dated
July 23, 1999; or Revision 2, dated June 17,
2002. After the effective date of this AD, only
Revision 2 may be used. Repeat the
tightening thereafter at intervals not to
exceed 12 months until the initial tightening
required by paragraph (k) of this AD is
accomplished.
the action in paragraph (g) of this AD,
whichever occurs earlier: Use a torque
wrench to tighten the screws for the
attachment of the leading edge of the rudder
in accordance with Fokker Service Bulletin
SBF50–55–009, Revision 2, dated June 17,
2002. Repeat the tightening thereafter at
intervals not to exceed 12 months until the
modification required by paragraph (l) of this
AD is accomplished. Doing the actions in this
paragraph terminates the repetitive actions of
paragraph (g) of this AD.
(k) Within 6 months after the effective date
of this AD or 6 months after accomplishing
the action in paragraph (h) of this AD,
whichever occurs earlier: Use a torque
wrench to tighten the screws for the
attachment of the leading edges of the
ailerons in accordance with Fokker Service
Bulletin SBF50–57–020, Revision 2, dated
June 17, 2002. Repeat the tightening
thereafter at intervals not to exceed 6 months
until the modification required by paragraph
(l) of this AD is accomplished. Doing the
actions in this paragraph terminates the
repetitive actions of paragraph (h) of this AD.
New Requirements of This AD
Terminating Modification
New Repetitive Intervals
(i) Within 6 months after the effective date
of this AD or 12 months after accomplishing
the action in paragraph (f) of this AD,
whichever occurs earlier: Use a torque
wrench to tighten the screws for the
attachment of the leading edges of the
elevators in accordance with Fokker Service
Bulletin SBF50–55–007, Revision 2, dated
June 17, 2002. Repeat the tightening
thereafter at intervals not to exceed 6 months
until the modification required by paragraph
(l) of this AD is accomplished. Doing the
actions in this paragraph terminates the
repetitive actions of paragraph (f) of this AD.
(j) Within 12 months after the effective date
of this AD or 24 months after accomplishing
(l) At the earlier of the times in paragraph
(l)(1) and (l)(2) of this AD, modify the
elevator, rudder, and aileron leading edge
attachments by installing additional locking
devices in accordance with the
Accomplishment Instructions of the service
bulletins in Table 1 of this AD. Doing the
modifications terminates the applicable
repetitive actions in paragraphs (f), (g), (h),
(i), (j), and (k) of this AD, as specified in
Table 1.
(1) Within 24 months after the effective
date of this AD.
(2) Within 180 months since the date of
issuance of the original Airworthiness
Certificate or the date of issuance of the
original Export Certificate of Airworthiness.
TABLE 1.—FOKKER SERVICE BULLETINS FOR TERMINATING MODIFICATION
Terminates the actions
required in paragraph—
Fokker service bulletin
Location
SBF50–55–008, Revision 3, dated June 17, 2002 .....................................................
SBF50–55–010, Revision 2, dated June 17, 2002 .....................................................
SBF50–57–021, Revision 2, dated June 17, 2002 .....................................................
Elevator leading edge ...........
Rudder leading edge ............
Aileron leading edge .............
Note 1: Fokker Service Bulletin SBF50–55–
010, Revision 2, refers to Fokker Service
Bulletin SBF50–55–011, dated October 29,
2001, as an additional source of service
information for modifying the rudder
attachments. Fokker Service Bulletin SBF50–
57–021, Revision 2, refers to Fokker Service
Bulletin SBF50–57–025, dated October 29,
2001, as an additional source of service
information for modifying the aileron
attachments.
(f) and (i).
(g) and (j).
(h) and (k).
Alternative Methods of Compliance
(AMOCs)
Flight Standards Certificate Holding District
Office.
(m)(1) The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Related Information
(n) Dutch airworthiness directive 2000–
131/2, dated July 31, 2002, also addresses the
subject of this AD.
Material Incorporated by Reference
(o) You must use the service information
that is specified in Table 2 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
TABLE 2.—ALL MATERIAL INCORPORATED BY REFERENCE
Fokker service bulletin
Revision level
SBF50–55–007 ................................................................................................................................................
Original ...........
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Date
June 5, 1998.
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TABLE 2.—ALL MATERIAL INCORPORATED BY REFERENCE—Continued
Fokker service bulletin
SBF50–55–007
SBF50–55–008
SBF50–55–009
SBF50–55–009
SBF50–55–010
SBF50–57–020
SBF50–57–020
SBF50–57–021
Revision level
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
(1) The incorporation by reference of the
service bulletins in Table 3 of this AD is
approved by the Director of the Federal
2
3
1
2
2
1
2
2
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
Date
June 17, 2002.
June 17, 2002.
July 23, 1999.
June 17, 2002.
June 17, 2002.
July 23, 1999.
June 17, 2002.
June 17, 2002.
Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE
Fokker service bulletin
SBF50–55–007
SBF50–55–008
SBF50–55–009
SBF50–55–010
SBF50–57–020
SBF50–57–021
Revision level
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
(2) The incorporation by reference of the
service bulletins in Table 4 of this AD was
approved previously by the Director of the
Revision
Revision
Revision
Revision
Revision
Revision
2
3
2
2
2
2
......
......
......
......
......
......
Date
June
June
June
June
June
June
17,
17,
17,
17,
17,
17,
2002.
2002.
2002.
2002.
2002.
2002.
Federal Register as of January 21, 2000, (65
FR 695, January 6, 2000).
TABLE 4.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Fokker service bulletin
Revision level
SBF50–55–007 ................................................................................................................................................
SBF50–55–009 ................................................................................................................................................
SBF50–57–020 ................................................................................................................................................
Original ...........
Revision 1 ......
Revision 1 ......
(3) Contact Fokker Services B.V., P.O. Box
231, 2150 AE Nieuw-Vennep, the
Netherlands, for copies of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the 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
November 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–23779 Filed 12–9–05; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:45 Dec 09, 2005
Jkt 208001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20712; Directorate
Identifier 2005–CE–15–AD; Amendment 39–
14400; AD 2005–25–07]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company, Model 390, Premier
1 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Raytheon Aircraft Company (Raytheon),
Model 390, Premier 1 airplanes. For
certain airplanes, this AD requires you
(unless already done) to replace the
plastic cover over the air conditioning
motor module with a metallic cover and
modify the air conditioning compressor
motor module electromagnetic
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Date
June 5, 1998.
July 23, 1999.
July 23, 1999.
interference-radio frequency
interference (EMI–RFI) filter located
under the cover and reidentify the
module part number. For all airplanes,
the AD limits future installations of the
cover for the air conditioner and the air
conditioning compressor motor module.
This AD results from reports that the
plastic cover over the air conditioning
motor module was found melted or
burned and that the overheating of the
EMI–RFI filter assembly located under
the cover caused this damage. We are
issuing this AD to prevent the melting
or burning of the plastic cover. The
burning of the plastic cover could result
in a fire.
This AD becomes effective on
January 23, 2006.
As of January 23, 2006, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
DATES:
To get the service
information identified in this AD,
contact Raytheon Aircraft Company,
ADDRESSES:
E:\FR\FM\12DER1.SGM
12DER1
]]>Agencies
[Federal Register Volume 70, Number 237 (Monday, December 12, 2005)]
[Rules and Regulations]
[Pages 73347-73351]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23779]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23214; Directorate Identifier 2001-NM-338-AD;
Amendment 39-14399; AD 2005-25-06]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Fokker Model F27 Mark 050 series airplanes.
The existing AD currently requires using a torque wrench to
repetitively tighten the screws for the attachment of the leading edges
of the elevators, rudder, and ailerons. This new AD requires the same
actions as those of the existing AD, but with reductions in the
intervals for repetitive actions. This AD also requires modifying the
elevator, rudder, and aileron leading edge attachments with additional
locking devices. This AD results from a report of an in-flight
vibration caused by a loose leading edge section of the elevator. We
are issuing this AD to prevent binding of the flight controls caused by
loose attachment screws, which could result in reduced controllability
of the airplane.
DATES: This AD becomes effective December 27, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 27,
2005.
On January 21, 2000 (65 FR 695, January 6, 2000), the Director of
the Federal Register approved the incorporation by reference of certain
other publications listed in the regulations.
We must receive comments on this AD by February 10, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
[[Page 73348]]
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9:00
a.m. and 5:00 p.m., Monday through Friday, except Federal holidays.
Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep,
the Netherlands, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 28, 1999, we issued AD 99-27-13, amendment 39-11494 (65
FR 695, January 6, 2000), for all Fokker Model F27 Mark 050 series
airplanes. That AD requires using a torque wrench to repetitively
tighten the screws for the attachment of the leading edges of the
elevators, rudder, and ailerons. That AD resulted from an issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. We issued that AD to prevent loose attachment
screws on the leading edges of the elevators, rudder, and ailerons due
to vibration, which could result in interference with adjacent
structure and consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 99-27-13, the Civil Aviation Authority--The
Netherlands (CAA-NL), which is the airworthiness authority for the
Netherlands, notified us that an additional further unsafe condition
may exist on all Fokker Model F27 Mark 050 airplanes. The CAA-NL
advises that an operator reported in-flight vibration, which was caused
by one loose elevator leading edge section. The airplane was found to
have been inspected only seven months before the incident, which was
within the original 12-month inspection interval of the existing AD.
Further investigation by the manufacturer showed that the self-locking
properties of the attachment screws gradually decrease when tightened
repeatedly as required by the procedures in the existing AD. This
condition, if not corrected, could result in binding of the flight
controls caused by loose attachment screws, which could cause reduced
controllability of the airplane.
Relevant Service Information
Fokker Services B.V. has issued bulletins in the following table.
Fokker Service Bulletins
------------------------------------------------------------------------
Fokker Services Bulletin-- Describes procedures for--
------------------------------------------------------------------------
SBF50-55-007, Revision 2, Tightening the attachment screws of the
dated June 17, 2002. elevators' leading edges.
SBF50-55-008, Revision 3, Modifying the elevator attachments by
dated June 17, 2002. installing additional locking devices
for the elevators' leading edges.
SBF50-55-009, Revision 2, Tightening the attachment screws for the
dated June 17, 2002. rudder's leading edge.
SBF50-55-010, Revision 2, Modifying the rudder attachments by
dated June 17, 2002. installing additional locking devices
for the rudder's leading edge.
SBF50-57-020, Revision 2, Tightening the attachment screws for the
dated June 17, 2002. ailerons' leading edges.
SBF50-57-021, Revision 2, Modifying the aileron attachments by
dated June 17, 2002. installing additional locking devices
for the ailerons' leading edges.
------------------------------------------------------------------------
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 2000-131/2, dated July 31, 2002, to ensure the continued
airworthiness of these airplanes in the Netherlands.
Fokker Service Bulletin SBF50-55-010, Revision 2, refers to Fokker
Service Bulletin SBF50-55-011, dated October 29, 2001, as an additional
source of service information for modifying the rudder attachments.
Fokker Service Bulletin SBF50-57-021, Revision 2, refers to Fokker
Service Bulletin SBF50-57-025, dated October 29, 2001, as an additional
source of service information for modifying the aileron attachments.
FAA's Determination and Requirements of this AD
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 CAA-NL has kept the FAA informed
of the situation described above. We have examined the CAA-NL's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to prevent binding of the flight
controls caused by loose attachment screws, which could result in
reduced controllability of the airplane. This AD requires accomplishing
the actions specified in the service information described previously.
This AD supersedes AD 99-27-13. This AD continues to require the
same actions as the existing AD, but at reduced repetitive intervals.
This AD also requires a new modification for the elevators, rudder, and
aileron attachments, which terminates the repetitive inspection
requirements of this AD. This AD requires accomplishing the actions
specified in the service bulletins described previously.
Change To Existing AD
This AD will retain all requirements of AD 99-27-13. Since AD 99-
27-13 was issued, the AD format has been revised, and certain
paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers
[[Page 73349]]
have changed in this AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 99-27-13 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
------------------------------------------------------------------------
Explanation of Change to Applicability
We have revised the applicability of the proposed AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
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.
The following table provides the estimated costs to comply with
this AD for any affected airplane that might be imported and placed on
the U.S. Register in the future.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Work Average labor
Action hours rate per hour Parts cost Cost per airplane
--------------------------------------------------------------------------------------------------------------------------------------------------------
Tightening (required by AD 99-27-13).. 12 $65 None...................................... $780, per inspection cycle
Modification (new action)............. 37 65 $1,025 to 3,372........................... $3,430 to 5,777
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
23214; Directorate Identifier 2001-NM-338-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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
removing amendment 39-11494 (65 FR 695, January 6, 2000) and by adding
the following new airworthiness directive (AD):
[[Page 73350]]
2005-25-06 Fokker Services B.V.: Amendment 39-14399. Docket No. FAA-
2005-23214; Directorate Identifier 2001-NM-338-AD.
Effective Date
(a) This AD becomes effective December 27, 2005.
Affected ADs
(b) This AD supersedes AD 99-27-13.
Applicability
(c) This AD applies to all Fokker Model F27 Mark 050 airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from a report of an in-flight vibration
caused by a loose leading edge section of the elevator. We are
issuing this AD to prevent binding of the flight controls caused by
loose attachment screws, which could result in reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 99-27-13
Repetitive Corrective Action
(f) Within 30 days after January 21, 2000 (the effective date of
AD 99-27-13), use a torque wrench to tighten the screws for the
attachment of the leading edges of the elevators in accordance with
Fokker Service Bulletin SBF50-55-007, dated June 5, 1998; or
Revision 2, dated June 17, 2002. After the effective date of this
AD, only Revision 2 may be used. Repeat the tightening thereafter at
intervals not to exceed 12 months until the initial tightening
required by paragraph (i) of this AD is accomplished.
(g) Within 24 months after January 21, 2000, use a torque wrench
to tighten the screws for the attachment of the leading edges of the
rudder in accordance with Fokker Service Bulletin SBF50-55-009,
Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002.
After the effective date of this AD, only Revision 2 may be used.
Repeat the tightening thereafter at intervals not to exceed 4,000
flight hours, or 24 months, whichever occurs first, until the
initial tightening required by paragraph (j) of this AD is
accomplished.
(h) Within 6 months after January 21, 2000, use a torque wrench
to tighten the screws for the attachment of the leading edges of the
ailerons in accordance with Fokker Service Bulletin SBF50-57-020,
Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002.
After the effective date of this AD, only Revision 2 may be used.
Repeat the tightening thereafter at intervals not to exceed 12
months until the initial tightening required by paragraph (k) of
this AD is accomplished.
New Requirements of This AD
New Repetitive Intervals
(i) Within 6 months after the effective date of this AD or 12
months after accomplishing the action in paragraph (f) of this AD,
whichever occurs earlier: Use a torque wrench to tighten the screws
for the attachment of the leading edges of the elevators in
accordance with Fokker Service Bulletin SBF50-55-007, Revision 2,
dated June 17, 2002. Repeat the tightening thereafter at intervals
not to exceed 6 months until the modification required by paragraph
(l) of this AD is accomplished. Doing the actions in this paragraph
terminates the repetitive actions of paragraph (f) of this AD.
(j) Within 12 months after the effective date of this AD or 24
months after accomplishing the action in paragraph (g) of this AD,
whichever occurs earlier: Use a torque wrench to tighten the screws
for the attachment of the leading edge of the rudder in accordance
with Fokker Service Bulletin SBF50-55-009, Revision 2, dated June
17, 2002. Repeat the tightening thereafter at intervals not to
exceed 12 months until the modification required by paragraph (l) of
this AD is accomplished. Doing the actions in this paragraph
terminates the repetitive actions of paragraph (g) of this AD.
(k) Within 6 months after the effective date of this AD or 6
months after accomplishing the action in paragraph (h) of this AD,
whichever occurs earlier: Use a torque wrench to tighten the screws
for the attachment of the leading edges of the ailerons in
accordance with Fokker Service Bulletin SBF50-57-020, Revision 2,
dated June 17, 2002. Repeat the tightening thereafter at intervals
not to exceed 6 months until the modification required by paragraph
(l) of this AD is accomplished. Doing the actions in this paragraph
terminates the repetitive actions of paragraph (h) of this AD.
Terminating Modification
(l) At the earlier of the times in paragraph (l)(1) and (l)(2)
of this AD, modify the elevator, rudder, and aileron leading edge
attachments by installing additional locking devices in accordance
with the Accomplishment Instructions of the service bulletins in
Table 1 of this AD. Doing the modifications terminates the
applicable repetitive actions in paragraphs (f), (g), (h), (i), (j),
and (k) of this AD, as specified in Table 1.
(1) Within 24 months after the effective date of this AD.
(2) Within 180 months since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness.
Table 1.--Fokker Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
Terminates the actions required in
Fokker service bulletin Location paragraph--
----------------------------------------------------------------------------------------------------------------
SBF50-55-008, Revision 3, dated Elevator leading edge................. (f) and (i).
June 17, 2002.
SBF50-55-010, Revision 2, dated Rudder leading edge................... (g) and (j).
June 17, 2002.
SBF50-57-021, Revision 2, dated Aileron leading edge.................. (h) and (k).
June 17, 2002.
----------------------------------------------------------------------------------------------------------------
Note 1: Fokker Service Bulletin SBF50-55-010, Revision 2, refers
to Fokker Service Bulletin SBF50-55-011, dated October 29, 2001, as
an additional source of service information for modifying the rudder
attachments. Fokker Service Bulletin SBF50-57-021, Revision 2,
refers to Fokker Service Bulletin SBF50-57-025, dated October 29,
2001, as an additional source of service information for modifying
the aileron attachments.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, ANM-116, International Branch, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(n) Dutch airworthiness directive 2000-131/2, dated July 31,
2002, also addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information that is specified in
Table 2 of this AD to perform the actions that are required by this
AD, unless the AD specifies otherwise.
Table 2.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Fokker service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007............................. Original....................... June 5, 1998.
[[Page 73351]]
SBF50-55-007............................. 2.............................. June 17, 2002.
SBF50-55-008............................. 3.............................. June 17, 2002.
SBF50-55-009............................. 1.............................. July 23, 1999.
SBF50-55-009............................. 2.............................. June 17, 2002.
SBF50-55-010............................. 2.............................. June 17, 2002.
SBF50-57-020............................. 1.............................. July 23, 1999.
SBF50-57-020............................. 2.............................. June 17, 2002.
SBF50-57-021............................. 2.............................. June 17, 2002.
----------------------------------------------------------------------------------------------------------------
(1) The incorporation by reference of the service bulletins in
Table 3 of this AD is approved by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Fokker service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007............................. Revision 2..................... June 17, 2002.
SBF50-55-008............................. Revision 3..................... June 17, 2002.
SBF50-55-009............................. Revision 2..................... June 17, 2002.
SBF50-55-010............................. Revision 2..................... June 17, 2002.
SBF50-57-020............................. Revision 2..................... June 17, 2002.
SBF50-57-021............................. Revision 2..................... June 17, 2002.
----------------------------------------------------------------------------------------------------------------
(2) The incorporation by reference of the service bulletins in
Table 4 of this AD was approved previously by the Director of the
Federal Register as of January 21, 2000, (65 FR 695, January 6,
2000).
Table 4.--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Fokker service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
SBF50-55-007............................. Original....................... June 5, 1998.
SBF50-55-009............................. Revision 1..................... July 23, 1999.
SBF50-57-020............................. Revision 1..................... July 23, 1999.
----------------------------------------------------------------------------------------------------------------
(3) Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands, for copies of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the 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 November 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23779 Filed 12-9-05; 8:45 am]
BILLING CODE 4910-13-P
