Airworthiness Directives; Alpha Aviation Design Limited (Type Certificate No. A48EU Previously Held by APEX Aircraft and Avions Pierre ROBIN) Model R2160 Airplanes, 57896-57898 [E7-20047]
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57896
Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
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 proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
There are about 134 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
104 airplanes of U.S. registry. The
proposed actions would take about 4
work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts would cost about $9 per
airplane. Based on these figures, the
estimated cost of the proposed AD for
U.S. operators is $34,216, or $329 per
airplane.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
1. The authority citation for part 39
continues to read as follows:
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.
mstockstill on PROD1PC66 with PROPOSALS
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 proposed regulation:
VerDate Aug<31>2005
14:15 Oct 10, 2007
Jkt 214001
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA–2007–
29330; Directorate Identifier 2007–NM–
199–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 26, 2007.
Applicability
(c) This AD applies to McDonnell Douglas
Model 717–200 airplanes, certificated in any
category, as identified in Boeing Service
Bulletin 717–28–0012, Revision 1, dated June
7, 2006.
Unsafe Condition
(d) This AD results from a fuel system
review conducted by the manufacturer. We
are issuing this AD to prevent improper
bonding of the fill valves and defuel shutoff
valve for the main fuel tanks and center wing
tank, which, in combination with a lightning
strike, could result in a fuel tank explosion
and consequent loss 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.
Frm 00008
Credit for Actions Done Using the Previous
Service Information
(g) Actions accomplished before the
effective date of this AD in accordance with
Boeing Service Bulletin 717–28–0012, dated
April 16, 2004, are considered acceptable for
compliance with the corresponding actions
specified in paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on October
1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–20051 Filed 10–10–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Affected ADs
(b) None.
PO 00000
Electrical Bonding
(f) Within 60 months after the effective
date of this AD, accomplish the electrical
bonding of the fill valves for the right and left
main fuel tanks, the fill valve and pipe
assembly for the center wing fuel tank, and
the defuel shutoff valve, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 717–28–0012, Revision 1,
dated June 7, 2006.
Fmt 4702
Sfmt 4702
[Docket No. FAA–2006–26490; Directorate
Identifier 2006–CE–75-AD]
RIN 2120–AA64
Airworthiness Directives; Alpha
Aviation Design Limited (Type
Certificate No. A48EU Previously Held
by APEX Aircraft and Avions Pierre
ROBIN) Model R2160 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
E:\FR\FM\11OCP1.SGM
11OCP1
Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
To prevent failure of the wing structure
and assembly components due to undetected
fatigue and corrosion * * *
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 13,
2007.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Karl
Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4146; fax: (816)
329–4090.
SUPPLEMENTARY INFORMATION:
mstockstill on PROD1PC66 with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–26490; Directorate Identifier
2006–CE–75–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
VerDate Aug<31>2005
14:15 Oct 10, 2007
Jkt 214001
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The Civil Aviation Authority (CAA),
which is the airworthiness authority for
New Zealand, has issued AD DCA/
R2000/28, dated September 28, 2006
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
To prevent failure of the wing structure
and assembly components due to undetected
fatigue and corrosion * * *
The MCAI requires that you inspect the
wing structure and fuselage attachment
and repair any defects that you find.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Avions Pierre Robin (recent type
certificate responsibility was with APEX
Aircraft and current responsibility with
Alpha Aviation Design Limited) has
issued Service Bulletin No. 123,
revision 2, dated November 14, 1995;
and Mandatory Service Bulletin No.
123, revision 3, issued December 23,
1999.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of the Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
57897
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
described in a separate paragraph of the
proposed AD. These requirements, if
ultimately adopted, will take
precedence over the actions copied from
the MCAI.
Costs of Compliance
We estimate that this proposed AD
will affect 10 products of U.S. registry.
We also estimate that it will take about
15 work-hours per product to comply
with basic requirements of this
proposed AD. The average labor rate is
$80 per work-hour. Required parts will
cost about $1,326 per product.
Based on these figures, we estimate
the cost of this proposed AD to the U.S.
operators to be $25,260 or $2,526 per
product.
We have no way to determine what
aircraft will need replacement parts that
may be required based on the results of
any inspection.
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 determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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
E:\FR\FM\11OCP1.SGM
11OCP1
57898
Federal Register / Vol. 72, No. 196 / Thursday, October 11, 2007 / Proposed Rules
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed 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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Alpha Aviation Design Limited (Type
Certificate No. A48EU previously held
by Apex Aircraft and Avions Pierre
Robin): Docket No. FAA–2006–26490;
Directorate Identifier 2006–CE–75–AD.
Comments Due Date
(a) We must receive comments by
November 13, 2007.
Affected ADs
(b) None.
mstockstill on PROD1PC66 with PROPOSALS
Applicability
(c) This AD applies to Model R2160
airplanes, serial numbers 001 through 378,
certificated in any category.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states:
To prevent failure of the wing structure
and assembly components due to undetected
fatigue and corrosion * * *
The MCAI requires that you inspect the wing
structure and fuselage attachment and repair
any defects that you find.
Actions and Compliance
(e) Unless already done, do the following
actions:
(1) For airplanes with less than 4,000 hours
time-in-service (TIS): When the airplane
VerDate Aug<31>2005
14:15 Oct 10, 2007
Jkt 214001
reaches a total of 3,500 hours TIS or within
the next 100 hours TIS after the effective date
of this AD, whichever occurs later, and
thereafter at intervals not to exceed 750 hours
TIS, disassemble the wings from the fuselage
and inspect the wing structure and assembly
components following instruction No. 1 in
Robin Aviation Service Bulletin No. 123,
revision 3, dated December 23, 1999. If any
defects are found, before further flight, repair
following Robin Aviation Service Bulletin
No. 123, revision 3, dated December 23,
1999; and Avions Pierre Robin Service
Bulletin No. 123, revision 2, issued
November 14, 1995.
(2) For airplanes with 4,000 hours TIS or
more that do not have the special instruction
in paragraph E of Avions Pierre Robin
Service Bulletin No. 123, revision 2, dated
November 14, 1995, incorporated: Within the
next 100 hours TIS after the effective date of
this AD and thereafter at intervals not to
exceed 750 hours TIS, disassemble the wings
from the fuselage and inspect the wing
structure and assembly components
following instruction No. 1 in Robin Aviation
Service Bulletin No. 123, revision 3, dated
December 23, 1999. If any defects are found,
before further flight, repair following Robin
Aviation Service Bulletin No. 123, revision 3,
dated December 23, 1999; and Avions Pierre
Robin Service Bulletin No. 123, revision 2,
issued November 14, 1995.
(3) For airplanes with 4,000 hours TIS or
more that have the special instruction in
paragraph E of Avions Pierre Robin Service
Bulletin No. 123, revision 2, dated November
14, 1995, incorporated: Within the next 750
hours TIS after the effective date of this AD
and thereafter at intervals not to exceed 750
hours TIS, disassemble the wings from the
fuselage and inspect the wing structure and
assembly components following instruction
No. 1 in Robin Aviation Service Bulletin No.
123, revision 3, dated December 23, 1999. If
any defects are found, before further flight,
repair following Robin Aviation Service
Bulletin No. 123, revision 3, dated December
23, 1999; and Avions Pierre Robin Service
Bulletin No. 123, revision 2, issued
November 14, 1995.
(4) For all airplanes: When the airplane
reaches a total of 3,500 hours TIS after
installation of the wing-to-fuselage bolts or
within the next 100 hours TIS after the
effective date of this AD, whichever occurs
later, do a non-destructive inspection of the
wing-to-fuselage retaining bolts and replace
any bolts that do not pass this inspection
following instruction No. 2 in Robin Aviation
Service Bulletin No. 123, revision 3, dated
December 23, 1999.
(5) For all airplanes: Within the next 50
hours TIS after re-assembling the wing and
thereafter at intervals not to exceed 100 hours
TIS, inspect the wing-to-fuselage retaining
bolts for correct torque settings following
instruction No. 3 in Robin Aviation Service
Bulletin No. 123, revision 3, dated December
23, 1999. The required torque value is 22 ftlb with nut part number 95.24.39.010.
Tighten to 16 ft-lb (pre-loading) and then
torque from 16 to 22 ft-lb.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
Differences.
Other FAA AD Provisions
(f) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4146; fax: (816)
329–4090. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(g) Refer to MCAI Civil Aviation Authority
AD DCA/R2000/28, dated September 28,
2006; Avions Pierre Robin Service Bulletin
No. 123, revision 2, issued November 14,
1995; and Robin Aviation Mandatory Service
Bulletin No. 123, revision 3, issued December
23, 1999, for related information.
Issued in Kansas City, Missouri, on
October 4, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–20047 Filed 10–10–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–29231; Airspace
Docket No. 07–AGL–8]
Proposed Establishment of Class E5
Airspace; Hinckley, MN
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking.
AGENCY:
E:\FR\FM\11OCP1.SGM
11OCP1
]]>Agencies
[Federal Register Volume 72, Number 196 (Thursday, October 11, 2007)]
[Proposed Rules]
[Pages 57896-57898]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-20047]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-75-AD]
RIN 2120-AA64
Airworthiness Directives; Alpha Aviation Design Limited (Type
Certificate No. A48EU Previously Held by APEX Aircraft and Avions
Pierre ROBIN) Model R2160 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of
[[Page 57897]]
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by November 13,
2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2006-
26490; Directorate Identifier 2006-CE-75-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for New Zealand, has issued AD DCA/R2000/28, dated September
28, 2006 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
The MCAI requires that you inspect the wing structure and fuselage
attachment and repair any defects that you find.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Avions Pierre Robin (recent type certificate responsibility was
with APEX Aircraft and current responsibility with Alpha Aviation
Design Limited) has issued Service Bulletin No. 123, revision 2, dated
November 14, 1995; and Mandatory Service Bulletin No. 123, revision 3,
issued December 23, 1999.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed AD and the MCAI or Service
Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the proposed AD. These
requirements, if ultimately adopted, will take precedence over the
actions copied from the MCAI.
Costs of Compliance
We estimate that this proposed AD will affect 10 products of U.S.
registry. We also estimate that it will take about 15 work-hours per
product to comply with basic requirements of this proposed AD. The
average labor rate is $80 per work-hour. Required parts will cost about
$1,326 per product.
Based on these figures, we estimate the cost of this proposed AD to
the U.S. operators to be $25,260 or $2,526 per product.
We have no way to determine what aircraft will need replacement
parts that may be required based on the results of any inspection.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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
[[Page 57898]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Alpha Aviation Design Limited (Type Certificate No. A48EU previously
held by Apex Aircraft and Avions Pierre Robin): Docket No. FAA-2006-
26490; Directorate Identifier 2006-CE-75-AD.
Comments Due Date
(a) We must receive comments by November 13, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model R2160 airplanes, serial numbers 001
through 378, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
The MCAI requires that you inspect the wing structure and fuselage
attachment and repair any defects that you find.
Actions and Compliance
(e) Unless already done, do the following actions:
(1) For airplanes with less than 4,000 hours time-in-service
(TIS): When the airplane reaches a total of 3,500 hours TIS or
within the next 100 hours TIS after the effective date of this AD,
whichever occurs later, and thereafter at intervals not to exceed
750 hours TIS, disassemble the wings from the fuselage and inspect
the wing structure and assembly components following instruction No.
1 in Robin Aviation Service Bulletin No. 123, revision 3, dated
December 23, 1999. If any defects are found, before further flight,
repair following Robin Aviation Service Bulletin No. 123, revision
3, dated December 23, 1999; and Avions Pierre Robin Service Bulletin
No. 123, revision 2, issued November 14, 1995.
(2) For airplanes with 4,000 hours TIS or more that do not have
the special instruction in paragraph E of Avions Pierre Robin
Service Bulletin No. 123, revision 2, dated November 14, 1995,
incorporated: Within the next 100 hours TIS after the effective date
of this AD and thereafter at intervals not to exceed 750 hours TIS,
disassemble the wings from the fuselage and inspect the wing
structure and assembly components following instruction No. 1 in
Robin Aviation Service Bulletin No. 123, revision 3, dated December
23, 1999. If any defects are found, before further flight, repair
following Robin Aviation Service Bulletin No. 123, revision 3, dated
December 23, 1999; and Avions Pierre Robin Service Bulletin No. 123,
revision 2, issued November 14, 1995.
(3) For airplanes with 4,000 hours TIS or more that have the
special instruction in paragraph E of Avions Pierre Robin Service
Bulletin No. 123, revision 2, dated November 14, 1995, incorporated:
Within the next 750 hours TIS after the effective date of this AD
and thereafter at intervals not to exceed 750 hours TIS, disassemble
the wings from the fuselage and inspect the wing structure and
assembly components following instruction No. 1 in Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999. If
any defects are found, before further flight, repair following Robin
Aviation Service Bulletin No. 123, revision 3, dated December 23,
1999; and Avions Pierre Robin Service Bulletin No. 123, revision 2,
issued November 14, 1995.
(4) For all airplanes: When the airplane reaches a total of
3,500 hours TIS after installation of the wing-to-fuselage bolts or
within the next 100 hours TIS after the effective date of this AD,
whichever occurs later, do a non-destructive inspection of the wing-
to-fuselage retaining bolts and replace any bolts that do not pass
this inspection following instruction No. 2 in Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999.
(5) For all airplanes: Within the next 50 hours TIS after re-
assembling the wing and thereafter at intervals not to exceed 100
hours TIS, inspect the wing-to-fuselage retaining bolts for correct
torque settings following instruction No. 3 in Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999. The
required torque value is 22 ft-lb with nut part number 95.24.39.010.
Tighten to 16 ft-lb (pre-loading) and then torque from 16 to 22 ft-
lb.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No Differences.
Other FAA AD Provisions
(f) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(g) Refer to MCAI Civil Aviation Authority AD DCA/R2000/28,
dated September 28, 2006; Avions Pierre Robin Service Bulletin No.
123, revision 2, issued November 14, 1995; and Robin Aviation
Mandatory Service Bulletin No. 123, revision 3, issued December 23,
1999, for related information.
Issued in Kansas City, Missouri, on October 4, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-20047 Filed 10-10-07; 8:45 am]
BILLING CODE 4910-13-P
