Airworthiness Directives; Vulcanair S.p.A. Model P68 Series Airplanes, 55786-55788 [E8-22338]
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Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules
paragraph (o) or (p) of this AD terminates the
requirements of this paragraph.
New Requirements of This AD
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Revise Airworthiness Limitations Section
(ALS) To Incorporate Limitations and
Maintenance Tasks for Aging Systems
Maintenance
(o) Within 3 months after the effective date
of this AD, revise the ALS of the Instructions
for Continued Airworthiness (ICA) to
incorporate Airbus A310 ALS Part 4—Aging
Systems Maintenance, Revision 01, dated
December 21, 2006; or Airbus A300–600 ALS
Part 4—Aging Systems Maintenance,
Revision 01, dated December 21, 2006; as
applicable. For all tasks identified in Airbus
A310 ALS Part 4—Aging Systems
Maintenance, Revision 01; and Airbus A300–
600 ALS Part 4—Aging Systems
Maintenance, Revision 01; do the tasks at the
later of the times specified in paragraphs
(o)(1) and (o)(2) of this AD, except as
provided by paragraph (p) of this AD. The
repetitive inspections must be accomplished
thereafter at the interval specified in Airbus
A310 ALS Part 4—Aging Systems
Maintenance, Revision 01; and Airbus A300–
600 ALS Part 4—Aging Systems
Maintenance, Revision 01. Doing an
inspection required by this paragraph
terminates the corresponding inspection
required by paragraph (f), (g), (l), (m), or (n)
of this AD.
(1) At the initial compliance times
(thresholds) specified in the applicable ALS
Part 4—Aging Systems Maintenance, with
the compliance times starting from the later
of the times specified in paragraphs (o)(1)(i)
and (o)(1)(ii) of this AD.
(i) Since first flight of the airplane.
(ii) Since the applicable part was new or
refurbished if the part’s life (in flight hours,
flight cycles, landings, or calendar time, as
applicable) can be conclusively determined.
(2) Within 3 months after doing the
revision of the ALS of the ICA required by
paragraph (o) of this AD.
Note 7: Refer to Airbus OIT SE 999.0074/
05/BB, dated August 3, 2005, for additional
information on the THSA life limits.
Note 8: Refer to Airbus OIT SE 999.0008/
07/LB, dated January 16, 2007; and Airbus
Service Information Letter (SIL) 05–008,
Revision 1, dated February 21, 2007; for
additional information on the THSA life
limits and calculation method for unknown
history of parts.
(p) For airplanes on which any life
limitation/maintenance task has been
complied with in accordance with the
requirements of paragraph (f), (g), (l), (m), or
(n) of this AD (e.g., AD 2006–10–11 or AD
2006–15–10), the last accomplishment of
each limitation/task must be retained as a
starting point for the accomplishment of each
corresponding limitation/task interval now
introduced in Airbus A310 ALS Part 4—
Aging Systems Maintenance, Revision 01,
dated December 21, 2006; and A300–600
ALS Part 4—Aging Systems Maintenance,
Revision 01, dated December 21, 2006; as
applicable. Doing an inspection required by
this paragraph terminates the corresponding
inspection required by paragraph (f), (g), (l),
(m), or (n) of this AD.
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(q) Except as provided by paragraph (r) of
this AD: After accomplishing the actions
specified in paragraphs (o) and (p) of this AD,
no alternative inspection, inspection
intervals, or limitations may be used.
Alternative Methods of Compliance (AMOCs)
(r)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Tom Stafford, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1622; fax (425)
227–1149. 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) AMOCs approved previously in
accordance with AD 2006–10–11 are not
approved as AMOCs with this AD.
(3) AMOCs approved previously in
accordance with AD 2006–15–10 are not
approved as AMOCs with this AD.
Related Information
(s) EASA airworthiness directive 2007–
0092, dated April 10, 2007, also addresses
the subject of this AD.
Issued in Renton, Washington, on
September 18, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–22632 Filed 9–25–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1020; Directorate
Identifier 2008–CE–053–AD]
RIN 2120–AA64
Airworthiness Directives; Vulcanair
S.p.A. Model P68 Series 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)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
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The Safe Fatigue Limits (SFL) of the Wing
Structure in the P68 Series aircraft have been
redefined from the current 8,500 Flight Hours
to a new value to be calculated up to a
maximum of 17,500 Flight Hours. This has
been developed by Vulcanair under Change
No. MOD.P68/79 Rev. 1 and approved by
EASA with No. EASA.A.C.02482 on 07 June
2006.
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 October 27, 2008.
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:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; 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–2008–1020; Directorate Identifier
2008–CE–053–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
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Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules
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 European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No.: 2007–
0027, dated February 5, 2007 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
The Safe Fatigue Limits (SFL) of the Wing
Structure in the P68 Series aircraft have been
redefined from the current 8,500 Flight Hours
to a new value to be calculated up to a
maximum of 17,500 Flight Hours. This has
been developed by Vulcanair under Change
No. MOD.P68/79 Rev. 1 and approved by
EASA with No. EASA.A.C.02482 on 07 June
2006.
The new Safe Fatigue Limits depend on:
(a) Status of the modification
(reinforcement) of the wing structure itself
(Partenavia Service Bulletin No. 65 refers);
and
(b) Aircraft Flight Hours accumulated
before the modification (reinforcement) was
implemented.
You may obtain further information by
examining the MCAI in the AD docket.
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Relevant Service Information
Vulcanair S.p.A. has issued Service
Bulletin No. 120 Rev. 1, dated June 7,
2006. 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
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55787
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
highlighted in a NOTE within the
proposed AD.
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.
Costs of Compliance
We estimate that this proposed AD
will affect 72 products of U.S. registry.
We also estimate that it would take
about 80 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $460,800, or $6,400 per
product.
We have no way of determining the
number of products that may need any
necessary follow-on actions.
List of Subjects in 14 CFR Part 39
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 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 this proposed regulation:
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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:
Vulcanair S.p.A. (Type Certificate No.
A31EU formally held by Partenavia
Costruzioni Aeronautiche S.p.A.): Docket
No. FAA–2008–1020; Directorate Identifier
2008–CE–053–AD.
Comments Due Date
(a) We must receive comments by October
27, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models P 68, P 68B,
P 68C, P 68C–TC, P 68 ‘‘OBSERVER,’’
AP68TP300 ‘‘SPARTACUS,’’ P68TC
‘‘OBSERVER,’’ AP68TP 600 ‘‘VIATOR,’’ and
P68 ‘‘OBSERVER 2’’ airplanes; all serial
numbers, certificated in any category.
Subject
(d) Air Transport Association of America
(ATA) Code 51: Standard Practices/
Structures.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
The Safe Fatigue Limits (SFL) of the Wing
Structure in the P68 Series aircraft have been
redefined from the current 8,500 Flight Hours
to a new value to be calculated up to a
maximum of 17,500 Flight Hours. This has
been developed by Vulcanair under Change
No. MOD.P68/79 Rev. 1 and approved by
EASA with No. EASA.A.C.02482 on 07 June
2006.
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Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules
mstockstill on PROD1PC66 with PROPOSALS
The new Safe Fatigue Limits depend on:
(1) Status of the modification
(reinforcement) of the wing structure itself
(Partenavia Service Bulletin No. 65 refers);
and
(2) Aircraft Flight Hours accumulated
before the modification (reinforcement) was
implemented.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) For serial numbers 01 through 356,
determine the safe fatigue limit of the wing
structure following Vulcanair S.p.A. Service
Bulletin No. 120 Rev. 1, dated June 7, 2006,
within 8,500 hours time-in-service (TIS)
since new or within 500 hours TIS after the
effective date of this AD, whichever occurs
later.
(2) For serial numbers 01 through 356,
inspect the wing structure and the wing to
fuselage attachments following Vulcanair
S.p.A. Service Bulletin No. 120 Rev. 1, dated
June 7, 2006, within the safe fatigue limit
determined in paragraph (f)(1) of this AD or
within 500 hours TIS after the effective date
of this AD, whichever occurs later.
Repetitively thereafter inspect at intervals not
to exceed every 500 hours TIS.
(3) For serial numbers 357 and above,
inspect the wing structure and the wing to
fuselage attachments following Vulcanair
S.p.A. Service Bulletin No. 120 Rev. 1, dated
June 7, 2006, within 17,500 hours TIS since
new or within 500 hours TIS after the
effective date of this AD, whichever occurs
later. Repetitively thereafter inspect at
intervals not to exceed every 500 hours TIS.
(4) For all serial numbers, inspect the
stabilator following Vulcanair S.p.A. Service
Bulletin No. 120 Rev. 1, dated June 7, 2006,
within 8,500 hours TIS since new or within
500 hours TIS after the effective date of this
AD, whichever occurs later. Repetitively
thereafter inspect at intervals not to exceed
every 500 hours TIS.
(5) If as a result of any inspection required
by paragraphs (f)(2), (f)(3), or (f)(4) of this AD
you find any discrepancies (for example,
cracked or broken parts), do one of the
following actions before further flight:
(i) Repair the airplane following FAAapproved repair instructions obtained from
Vulcanair S.p.A.; or
(ii) Repair the airplane following a repair
method approved by the FAA for this AD.
Contact the FAA at the address in paragraph
(g)(1) of this AD for an FAA-approved
method.
Note 1: For certain Model P 68 airplanes,
AD 85–08–04 requires repetitive inspections
of the front and rear wing spars for cracks
with modification if cracks are found. The
modification terminates the repetitive
inspections required in AD 85–08–04 and
may be done regardless if cracks are found.
The actions of AD 85–08–08 are independent
of this AD action and remain in effect.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows:
(1) The MCAI is extending the safe fatigue
limits of the wing structure and the wing to
fuselage attachments of certain airplanes.
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Airplanes registered in the United States did
not have safe fatigue limits established for
the wing structure and the wing to fuselage
attachments. This AD is establishing safe
fatigue limits for the wing structure and the
wing to fuselage attachments. This AD is also
establishing safe fatigue limits for the
stabilator.
(2) The MCAI requires implementation of
safe fatigue limits into the airplane
maintenance program (maintenance
program). An airplane registered in the
United States and operated under 14 CFR
part 91 is required to have a maintenance
program, but not necessarily following the
airplane maintenance manual. This AD
requires you to do specific actions of
Vulcanair S.p.A. Service Bulletin No. 120
Rev. 1, dated June 7, 2006, rather than
incorporating those actions into the
maintenance program.
Other FAA AD Provisions
(g) 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: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4145; 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
(h) Refer to MCAI European Aviation
Safety Agency AD No.: 2007–0027, dated
February 5, 2007; and Vulcanair S.p.A.
Service Bulletin No. 120 Rev. 1, dated June
7, 2006, for related information.
Issued in Kansas City, Missouri, on
September 17, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–22338 Filed 9–25–08; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 93
[Docket No. FAA–2007–26470; and Notice
No. 08–10]
RIN 2120–AJ29
Proposed Establishment of Special Air
Traffic Rule, in the Vicinity of Luke
AFB, AZ
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This rule would establish a
Special Air Traffic Rule (SATR) in the
vicinity of Luke Air Force Base (Luke)
which would require general aviation
(GA) traffic operating under visual flight
rules (VFR) to establish communication
with the Luke Radar Approach Control
(RAPCON) while operating in the area
around Luke. This action is necessary to
address reported near midair collisions
in the area around Luke and would help
reduce the potential for midair
collisions in the vicinity of Luke.
DATES: Comments must be received on
or before November 25, 2008.
ADDRESSES: You may send comments
identified by Docket Number FAA–
2007–26470 using any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the online instructions for sending your
comments electronically.
• Mail: Send comments to Docket
Operations, M–30; U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., Room W12–140, West
Building Ground Floor, Washington, DC
20590–0001.
• Hand Delivery or Courier: Bring
comments to Docket Operations in
Room W12–140 of the West Building
Ground Floor at 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• Fax: Fax comments to Docket
Operations at 202–493–2251.
For more information on the
rulemaking process, see the
SUPPLEMENTARY INFORMATION section of
this document.
Privacy: We will post all comments
we receive, without change, to https://
www.regulations.gov, including any
personal information you provide.
Using the search function of our docket
Web site, anyone can find and read the
electronic form of all comments
received into any of our dockets,
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]]>Agencies
[Federal Register Volume 73, Number 188 (Friday, September 26, 2008)]
[Proposed Rules]
[Pages 55786-55788]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-22338]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1020; Directorate Identifier 2008-CE-053-AD]
RIN 2120-AA64
Airworthiness Directives; Vulcanair S.p.A. Model P68 Series
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) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
The Safe Fatigue Limits (SFL) of the Wing Structure in the P68
Series aircraft have been redefined from the current 8,500 Flight
Hours to a new value to be calculated up to a maximum of 17,500
Flight Hours. This has been developed by Vulcanair under Change No.
MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07
June 2006.
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 October 27,
2008.
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: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4145; 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-2008-1020;
Directorate Identifier 2008-CE-053-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
[[Page 55787]]
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 European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No.: 2007-0027, dated February 5, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
The Safe Fatigue Limits (SFL) of the Wing Structure in the P68
Series aircraft have been redefined from the current 8,500 Flight
Hours to a new value to be calculated up to a maximum of 17,500
Flight Hours. This has been developed by Vulcanair under Change No.
MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07
June 2006.
The new Safe Fatigue Limits depend on:
(a) Status of the modification (reinforcement) of the wing
structure itself (Partenavia Service Bulletin No. 65 refers); and
(b) Aircraft Flight Hours accumulated before the modification
(reinforcement) was implemented.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Vulcanair S.p.A. has issued Service Bulletin No. 120 Rev. 1, dated
June 7, 2006. 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
highlighted in a NOTE within the proposed AD.
Costs of Compliance
We estimate that this proposed AD will affect 72 products of U.S.
registry. We also estimate that it would take about 80 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $460,800, or $6,400 per product.
We have no way of determining the number of products that may need
any necessary follow-on actions.
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 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:
Vulcanair S.p.A. (Type Certificate No. A31EU formally held by
Partenavia Costruzioni Aeronautiche S.p.A.): Docket No. FAA-2008-
1020; Directorate Identifier 2008-CE-053-AD.
Comments Due Date
(a) We must receive comments by October 27, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Models P 68, P 68B, P 68C, P 68C-TC, P 68
``OBSERVER,'' AP68TP300 ``SPARTACUS,'' P68TC ``OBSERVER,'' AP68TP
600 ``VIATOR,'' and P68 ``OBSERVER 2'' airplanes; all serial
numbers, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 51: Standard
Practices/Structures.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
The Safe Fatigue Limits (SFL) of the Wing Structure in the P68
Series aircraft have been redefined from the current 8,500 Flight
Hours to a new value to be calculated up to a maximum of 17,500
Flight Hours. This has been developed by Vulcanair under Change No.
MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07
June 2006.
[[Page 55788]]
The new Safe Fatigue Limits depend on:
(1) Status of the modification (reinforcement) of the wing
structure itself (Partenavia Service Bulletin No. 65 refers); and
(2) Aircraft Flight Hours accumulated before the modification
(reinforcement) was implemented.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For serial numbers 01 through 356, determine the safe
fatigue limit of the wing structure following Vulcanair S.p.A.
Service Bulletin No. 120 Rev. 1, dated June 7, 2006, within 8,500
hours time-in-service (TIS) since new or within 500 hours TIS after
the effective date of this AD, whichever occurs later.
(2) For serial numbers 01 through 356, inspect the wing
structure and the wing to fuselage attachments following Vulcanair
S.p.A. Service Bulletin No. 120 Rev. 1, dated June 7, 2006, within
the safe fatigue limit determined in paragraph (f)(1) of this AD or
within 500 hours TIS after the effective date of this AD, whichever
occurs later. Repetitively thereafter inspect at intervals not to
exceed every 500 hours TIS.
(3) For serial numbers 357 and above, inspect the wing structure
and the wing to fuselage attachments following Vulcanair S.p.A.
Service Bulletin No. 120 Rev. 1, dated June 7, 2006, within 17,500
hours TIS since new or within 500 hours TIS after the effective date
of this AD, whichever occurs later. Repetitively thereafter inspect
at intervals not to exceed every 500 hours TIS.
(4) For all serial numbers, inspect the stabilator following
Vulcanair S.p.A. Service Bulletin No. 120 Rev. 1, dated June 7,
2006, within 8,500 hours TIS since new or within 500 hours TIS after
the effective date of this AD, whichever occurs later. Repetitively
thereafter inspect at intervals not to exceed every 500 hours TIS.
(5) If as a result of any inspection required by paragraphs
(f)(2), (f)(3), or (f)(4) of this AD you find any discrepancies (for
example, cracked or broken parts), do one of the following actions
before further flight:
(i) Repair the airplane following FAA-approved repair
instructions obtained from Vulcanair S.p.A.; or
(ii) Repair the airplane following a repair method approved by
the FAA for this AD. Contact the FAA at the address in paragraph
(g)(1) of this AD for an FAA-approved method.
Note 1: For certain Model P 68 airplanes, AD 85-08-04 requires
repetitive inspections of the front and rear wing spars for cracks
with modification if cracks are found. The modification terminates
the repetitive inspections required in AD 85-08-04 and may be done
regardless if cracks are found. The actions of AD 85-08-08 are
independent of this AD action and remain in effect.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
(1) The MCAI is extending the safe fatigue limits of the wing
structure and the wing to fuselage attachments of certain airplanes.
Airplanes registered in the United States did not have safe fatigue
limits established for the wing structure and the wing to fuselage
attachments. This AD is establishing safe fatigue limits for the
wing structure and the wing to fuselage attachments. This AD is also
establishing safe fatigue limits for the stabilator.
(2) The MCAI requires implementation of safe fatigue limits into
the airplane maintenance program (maintenance program). An airplane
registered in the United States and operated under 14 CFR part 91 is
required to have a maintenance program, but not necessarily
following the airplane maintenance manual. This AD requires you to
do specific actions of Vulcanair S.p.A. Service Bulletin No. 120
Rev. 1, dated June 7, 2006, rather than incorporating those actions
into the maintenance program.
Other FAA AD Provisions
(g) 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: Sarjapur Nagarajan, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4145; 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
(h) Refer to MCAI European Aviation Safety Agency AD No.: 2007-
0027, dated February 5, 2007; and Vulcanair S.p.A. Service Bulletin
No. 120 Rev. 1, dated June 7, 2006, for related information.
Issued in Kansas City, Missouri, on September 17, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-22338 Filed 9-25-08; 8:45 am]
BILLING CODE 4910-13-P
