Airworthiness Directives; BAe Systems (Operations) Limited Model ATP Airplanes, 53915-53917 [05-18059]
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Federal Register / Vol. 70, No. 176 / Tuesday, September 13, 2005 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20404; Directorate
Identifier 2005–NM–018–AD; Amendment
39–14268; AD 2005–19–03]
RIN 2120–AA64
Airworthiness Directives; BAe
Systems (Operations) Limited Model
ATP 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 BAe Systems
(Operations) Limited Model ATP
airplanes. That AD currently requires
revising the Airworthiness Limitations
Section (ALS) of the Instructions for
Continued Airworthiness to incorporate
life limits for certain items and
inspections to detect fatigue cracking in
certain structures. This new AD requires
a revision to the ALS of the Instructions
for Continued Airworthiness to
incorporate new inspections to detect
fatigue cracking of certain significant
structural items (SSIs) and to revise life
limits for certain equipment and various
components. This AD is prompted by a
determination that existing inspection
techniques are not adequate for certain
SSIs and by the revision of certain life
limits. We are issuing this AD to detect
and correct fatigue cracking of certain
structural elements, which could
adversely affect the structural integrity
of these airplanes.
DATES: Effective September 28, 2005.
We must receive comments on this
AD by November 14, 2005.
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.
• 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,
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15:30 Sep 12, 2005
Jkt 205001
DC, between 9:00 a.m. and 5:00 p.m.,
Monday through Friday, except Federal
holidays.
Contact British Aerospace Regional
Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia
20171, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 22, 2000, we issued AD
2000–26–10, amendment 39–12060 (66
FR 267, January 3, 2001). That AD is
applicable to all BAe Systems
(Operations) Limited Model ATP
airplanes. That AD requires revising the
Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness to incorporate life limits
for certain items and inspections to
detect fatigue cracking in certain
structures. That AD resulted from a
revision to the airworthiness limitations
of the British Aerospace ATP Aircraft
Maintenance Manual, which specifies
new inspections and compliance times
for inspection and replacement action.
The actions specified in that AD are
intended to detect and correct fatigue
cracking of certain structural elements,
which could adversely affect the
structural integrity of these airplanes.
Actions Since Existing AD Was Issued
Since we issued AD 2000–26–10, the
Civil Aviation Authority (CAA), which
is the airworthiness authority for the
United Kingdom, notified us that an
unsafe condition may exist on all BAe
Systems (Operations) Limited Model
ATP airplanes. The CAA advises that
existing inspection techniques given in
Section 05–10–17 of the British
Aerospace ATP Aircraft Maintenance
Manual (AMM) are not adequate for
certain structurally significant items
(SSIs) and that certain mandatory life
limitations given in Section 05–10–11 of
the AMM have been revised. (The
AMMs are described under ‘‘Relevant
Service Information’’ below.) Inadequate
inspection techniques or replacement
intervals could result in fatigue cracking
of certain structural elements, which
could adversely affect the structural
integrity of these airplanes.
Relevant Service Information
British Aerospace has issued revisions
to Section 05–10–11, ‘‘Mandatory Life
Limitations (Airframe)’’ and Section 05–
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
53915
10–17, ‘‘Structurally Significant Items
(SSI’S)’’ both dated July 15, 2004; of the
British Aerospace ATP AMM, which
refer to additional chapters of the AMM.
Those revised sections of the AMM
include mandatory life limitations for
the airframe and power plant/engine;
and structural inspections of the
fuselage, engine, horizontal stabilizer,
and wing bottom surface. The revised
section also describes new inspections
and compliance times for inspection
and replacement actions.
Accomplishment of those actions will
preclude the onset of fatigue cracking of
certain structural elements of the
airplane.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA mandated the
service information and issued British
airworthiness directive G–2004–0020,
dated August 25, 2004, to ensure the
continued airworthiness of these
airplanes in the United Kingdom.
FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in the United Kingdom 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 has
kept the FAA informed of the situation
described above. We have examined the
CAA’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
supersede AD 2000–26–10 and to
continue to require a revision to the
ALS of the Instructions for Continued
Airworthiness to incorporate
inspections to detect fatigue cracking of
certain SSIs. This new AD revises life
limits for certain equipment and various
components that are specified in the
previously referenced service
information.
Clarification of British Airworthiness
Directive
Operators should note that British
airworthiness directive G–2004–0020
specifies to do the tasks for chapters 27,
32, 52, 53, and 54 in Section 05–10–11
of the British Aerospace ATP AMM.
However, there are no tasks for chapter
52 listed in Section 05–10–11.
Therefore, this AD requires
incorporating the tasks for Chapters 27,
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53916
Federal Register / Vol. 70, No. 176 / Tuesday, September 13, 2005 / Rules and Regulations
32, 53, and 54 listed in Section 05–10–
11.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register.
Although 10 airplanes were on the U.S.
Register at the time of issuance of AD
2000–26–10, all airplanes affected by
this AD are currently operated by nonU.S. operators under foreign registry;
therefore, these airplanes 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 1
work hour per airplane, at an average
labor rate of $65 per work hour. Based
on these figures, the estimated cost of
the AD would be $65 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 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. Include
‘‘Docket No. FAA–2005–20404;
Directorate Identifier 2005–NM–018–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
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
VerDate Aug<18>2005
15:30 Sep 12, 2005
Jkt 205001
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
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.
Air transportation, Aircraft, Aviation
safety, Safety.
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
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Fmt 4700
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List of Subjects in 14 CFR Part 39
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 FAA amends § 39.13 by
removing amendment 39–12060 (66 FR
267, January 3, 2001) and by adding the
following new airworthiness directive
(AD):
I
2005–19–03 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14268. Docket No. FAA–2005–20404;
Directorate Identifier 2005–NM–018–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 28, 2005.
Affected ADs
(b) This AD supersedes AD 2000–26–10,
amendment 39–12060.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model ATP airplanes,
certificated in any category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance according
to paragraph (i) of this AD. The request
should include a description of changes to
the required inspections that will ensure the
continued damage tolerance of the affected
structure. The FAA has provided guidance
for this determination in Advisory Circular
(AC) 25–1529.
Unsafe Condition
(d) This AD was prompted by a
determination that existing inspection
techniques are not adequate for certain
structurally significant items and by the
revision of certain life limits. We are issuing
this AD to detect and correct fatigue cracking
of certain structural elements, which could
E:\FR\FM\13SER1.SGM
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Federal Register / Vol. 70, No. 176 / Tuesday, September 13, 2005 / Rules and Regulations
adversely affect the structural integrity of
these airplanes.
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 Requirements of AD 2000–
26–10
Airworthiness Limitations Revision
(f) Within 30 days after February 7, 2001
(the effective date of AD 2000–26–10), revise
the Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness according to a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA. One approved method is
by incorporating Section 05–00–00, dated
August 15, 1997, of the British Aerospace
ATP Aircraft Maintenance Manual (AMM),
dated October 15, 1999, into the ALS. This
section references other chapters of the
AMM. The applicable revision level of the
referenced chapters is that in effect on
February 7, 2001. Doing the revision
specified in paragraph (g) of this AD replaces
Chapters 27, 32, 53, and 54 listed in Section
05–10–11 and Chapters 52, 53, 54, 55, and 57
listed in Section 05–10–17 that are in effect
on February 7, 2001, with Chapters 27, 32,
53, and 54 listed in Section 05–10–11,
‘‘Mandatory Life Limitations (Airframe)’; and
Chapters 52, 53, 54, 55, and 57 listed in
Section 05–10–17, ‘‘Structurally Significant
Items (SSI’S)’’; both dated July 15, 2004; of
the British Aerospace ATP AMM.
New Requirements of This AD
New Airworthiness Limitations
(g) Within 30 days after the effective date
of this AD, revise the ALS of the Instructions
for Continued Airworthiness according to a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA. One approved
method is by incorporating the tasks for
Chapters 27, 32, 53, and 54 listed in Section
05–10–11, ‘‘Mandatory Life Limitations
(Airframe)’’; and the tasks for Chapters 52,
53, 54, 55, and 57 listed in Section 05–10–
17, ‘‘Structurally Significant Items (SSI’S)’’;
both dated July 15, 2004; of the British
Aerospace ATP AMM; into the ALS. These
chapters replace the corresponding chapters
in Section 05–00–00, dated August 15, 1997,
of the British Aerospace ATP AMM as
specified in paragraph (f) of this AD.
(h) Except as provided by paragraph (i) of
this AD: After the actions specified in
paragraphs (f) and (g) of this AD have been
accomplished, no alternative inspections or
inspection intervals may be approved for the
structural elements specified in the
documents listed in paragraphs (f) and (g) of
this AD.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, International Branch,
ANM–116, 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.
VerDate Aug<18>2005
15:30 Sep 12, 2005
Jkt 205001
Related Information
(j) British airworthiness directive G–2004–
0020, dated August 25, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(k) None.
Issued in Renton, Washington, on
September 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–18059 Filed 9–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2005–21448; Airspace
Docket No. 05–AAL–16]
Establishment of Class E Airspace;
Golovin, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action establishes Class
E airspace at Golovin, AK to provide
adequate controlled airspace to contain
aircraft executing two new Standard
Instrument Approach Procedures
(SIAPs) and one new departure
procedure. This rule results in new
Class E airspace upward from 700 feet
(ft.) and 1,200 ft. above the surface at
Golovin, AK.
EFFECTIVE DATE: This final rule is
effective September 13, 2005.
FOR FURTHER INFORMATION CONTACT: Gary
Rolf, AAL–538G, Federal Aviation
Administration, 222 West 7th Avenue,
Box 14, Anchorage, AK 99513–7587;
telephone number (907) 271–5898; fax:
(907) 271–2850; email:
gary.ctr.rolf@faa.gov. Internet address:
https://www.alaska.faa.gov/at.
SUPPLEMENTARY INFORMATION:
History
On Friday, June 24, 2005, the FAA
proposed to amend part 71 of the
Federal Aviation Regulations (14 CFR
part 71) to create new Class E airspace
upward from 700 ft. and 1,200 ft. above
the surface at Golovin, AK (70 FR
36544). The action was proposed in
order to create Class E airspace
sufficient in size to contain aircraft
while executing two new SIAPs and one
new departure procedure for the
Golovin Airport. The new approaches
are (1) Area Navigation (Global
Positioning System) (RNAV (GPS))
Runway (RWY) 02, original; and (2)
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Frm 00017
Fmt 4700
Sfmt 4700
53917
RNAV (GPS)–A, original. The new
departure procedure is the Nome ONE
Departure. New Class E controlled
airspace extending upward from 700 ft.
and 1,200 ft. above the surface in the
Golovin Airport area is established by
this action. Interested parties were
invited to participate in this rulemaking
proceeding by submitting written
comments on the proposal to the FAA.
No public comments have been
received; thus the rule is adopted as
proposed.
The area will be depicted on
aeronautical charts for pilot reference.
The coordinates for this airspace docket
are based on North American Datum 83.
The Class E airspace areas designated as
700/1200 ft. transition areas are
published in paragraph 6005 of FAA
Order 7400.9M, Airspace Designations
and Reporting Points, dated August 30,
2004, and effective September 16, 2004,
which is incorporated by reference in 14
CFR 71.1. The Class E airspace
designation listed in this document will
be published subsequently in the Order.
The Notice of Proposed Rulemaking
document included an airspace
exclusion to the Nome Class E airspace.
That exclusion was not neccessary and
it is not included in this action.
The Rule
This amendment to 14 CFR part 71
establishes Class E airspace at Golovin,
Alaska. This Class E airspace is
designated to accommodate aircraft
executing two new SIAPs and one new
departure procedure and will be
depicted on aeronautical charts for pilot
reference. The intended effect of this
rule is to provide adequate controlled
airspace for Instrument Flight Rule (IFR)
operations at Golovin Airport, Golovin,
Alaska.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(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)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. Since this a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this rule will not have
a significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
The FAA’s authority to issue rules
regarding aviation safety is found in
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]]>Agencies
[Federal Register Volume 70, Number 176 (Tuesday, September 13, 2005)]
[Rules and Regulations]
[Pages 53915-53917]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18059]
[[Page 53915]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20404; Directorate Identifier 2005-NM-018-AD;
Amendment 39-14268; AD 2005-19-03]
RIN 2120-AA64
Airworthiness Directives; BAe Systems (Operations) Limited Model
ATP 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 BAe Systems (Operations) Limited Model ATP
airplanes. That AD currently requires revising the Airworthiness
Limitations Section (ALS) of the Instructions for Continued
Airworthiness to incorporate life limits for certain items and
inspections to detect fatigue cracking in certain structures. This new
AD requires a revision to the ALS of the Instructions for Continued
Airworthiness to incorporate new inspections to detect fatigue cracking
of certain significant structural items (SSIs) and to revise life
limits for certain equipment and various components. This AD is
prompted by a determination that existing inspection techniques are not
adequate for certain SSIs and by the revision of certain life limits.
We are issuing this AD to detect and correct fatigue cracking of
certain structural elements, which could adversely affect the
structural integrity of these airplanes.
DATES: Effective September 28, 2005.
We must receive comments on this AD by November 14, 2005.
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.
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 British Aerospace Regional Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia 20171, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
On December 22, 2000, we issued AD 2000-26-10, amendment 39-12060
(66 FR 267, January 3, 2001). That AD is applicable to all BAe Systems
(Operations) Limited Model ATP airplanes. That AD requires revising the
Airworthiness Limitations section (ALS) of the Instructions for
Continued Airworthiness to incorporate life limits for certain items
and inspections to detect fatigue cracking in certain structures. That
AD resulted from a revision to the airworthiness limitations of the
British Aerospace ATP Aircraft Maintenance Manual, which specifies new
inspections and compliance times for inspection and replacement action.
The actions specified in that AD are intended to detect and correct
fatigue cracking of certain structural elements, which could adversely
affect the structural integrity of these airplanes.
Actions Since Existing AD Was Issued
Since we issued AD 2000-26-10, the Civil Aviation Authority (CAA),
which is the airworthiness authority for the United Kingdom, notified
us that an unsafe condition may exist on all BAe Systems (Operations)
Limited Model ATP airplanes. The CAA advises that existing inspection
techniques given in Section 05-10-17 of the British Aerospace ATP
Aircraft Maintenance Manual (AMM) are not adequate for certain
structurally significant items (SSIs) and that certain mandatory life
limitations given in Section 05-10-11 of the AMM have been revised.
(The AMMs are described under ``Relevant Service Information'' below.)
Inadequate inspection techniques or replacement intervals could result
in fatigue cracking of certain structural elements, which could
adversely affect the structural integrity of these airplanes.
Relevant Service Information
British Aerospace has issued revisions to Section 05-10-11,
``Mandatory Life Limitations (Airframe)'' and Section 05-10-17,
``Structurally Significant Items (SSI'S)'' both dated July 15, 2004; of
the British Aerospace ATP AMM, which refer to additional chapters of
the AMM. Those revised sections of the AMM include mandatory life
limitations for the airframe and power plant/engine; and structural
inspections of the fuselage, engine, horizontal stabilizer, and wing
bottom surface. The revised section also describes new inspections and
compliance times for inspection and replacement actions. Accomplishment
of those actions will preclude the onset of fatigue cracking of certain
structural elements of the airplane.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA mandated
the service information and issued British airworthiness directive G-
2004-0020, dated August 25, 2004, to ensure the continued airworthiness
of these airplanes in the United Kingdom.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in the United Kingdom 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 has kept the FAA
informed of the situation described above. We have examined the CAA'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 supersede AD 2000-26-10 and to
continue to require a revision to the ALS of the Instructions for
Continued Airworthiness to incorporate inspections to detect fatigue
cracking of certain SSIs. This new AD revises life limits for certain
equipment and various components that are specified in the previously
referenced service information.
Clarification of British Airworthiness Directive
Operators should note that British airworthiness directive G-2004-
0020 specifies to do the tasks for chapters 27, 32, 52, 53, and 54 in
Section 05-10-11 of the British Aerospace ATP AMM. However, there are
no tasks for chapter 52 listed in Section 05-10-11. Therefore, this AD
requires incorporating the tasks for Chapters 27,
[[Page 53916]]
32, 53, and 54 listed in Section 05-10-11.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. Although 10 airplanes were on the U.S. Register at the time
of issuance of AD 2000-26-10, all airplanes affected by this AD are
currently operated by non-U.S. operators under foreign registry;
therefore, these airplanes 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 1 work hour per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the AD would be $65 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 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. Include ``Docket No. FAA-
2005-20404; Directorate Identifier 2005-NM-018-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the AD. We
will consider all comments received by the closing date and may amend
the AD in light of those comments.
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. 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, 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 FAA amends Sec. 39.13 by removing amendment 39-12060 (66 FR
267, January 3, 2001) and by adding the following new airworthiness
directive (AD):
2005-19-03 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-14268. Docket No. FAA-
2005-20404; Directorate Identifier 2005-NM-018-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 28, 2005.
Affected ADs
(b) This AD supersedes AD 2000-26-10, amendment 39-12060.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model ATP airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (i) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529.
Unsafe Condition
(d) This AD was prompted by a determination that existing
inspection techniques are not adequate for certain structurally
significant items and by the revision of certain life limits. We are
issuing this AD to detect and correct fatigue cracking of certain
structural elements, which could
[[Page 53917]]
adversely affect the structural integrity of these airplanes.
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 Requirements of AD 2000-26-10
Airworthiness Limitations Revision
(f) Within 30 days after February 7, 2001 (the effective date of
AD 2000-26-10), revise the Airworthiness Limitations section (ALS)
of the Instructions for Continued Airworthiness according to a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA. One approved method is by
incorporating Section 05-00-00, dated August 15, 1997, of the
British Aerospace ATP Aircraft Maintenance Manual (AMM), dated
October 15, 1999, into the ALS. This section references other
chapters of the AMM. The applicable revision level of the referenced
chapters is that in effect on February 7, 2001. Doing the revision
specified in paragraph (g) of this AD replaces Chapters 27, 32, 53,
and 54 listed in Section 05-10-11 and Chapters 52, 53, 54, 55, and
57 listed in Section 05-10-17 that are in effect on February 7,
2001, with Chapters 27, 32, 53, and 54 listed in Section 05-10-11,
``Mandatory Life Limitations (Airframe)'; and Chapters 52, 53, 54,
55, and 57 listed in Section 05-10-17, ``Structurally Significant
Items (SSI'S)''; both dated July 15, 2004; of the British Aerospace
ATP AMM.
New Requirements of This AD
New Airworthiness Limitations
(g) Within 30 days after the effective date of this AD, revise
the ALS of the Instructions for Continued Airworthiness according to
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA. One approved method is by
incorporating the tasks for Chapters 27, 32, 53, and 54 listed in
Section 05-10-11, ``Mandatory Life Limitations (Airframe)''; and the
tasks for Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-
17, ``Structurally Significant Items (SSI'S)''; both dated July 15,
2004; of the British Aerospace ATP AMM; into the ALS. These chapters
replace the corresponding chapters in Section 05-00-00, dated August
15, 1997, of the British Aerospace ATP AMM as specified in paragraph
(f) of this AD.
(h) Except as provided by paragraph (i) of this AD: After the
actions specified in paragraphs (f) and (g) of this AD have been
accomplished, no alternative inspections or inspection intervals may
be approved for the structural elements specified in the documents
listed in paragraphs (f) and (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, International Branch, ANM-116, 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.
Related Information
(j) British airworthiness directive G-2004-0020, dated August
25, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(k) None.
Issued in Renton, Washington, on September 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18059 Filed 9-12-05; 8:45 am]
BILLING CODE 4910-13-P
