Airworthiness Directives; Vulcanair S.p.A. Model P68 Series Airplanes, 72314-72316 [E8-27916]
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE 5—INCORPORATION BY REFERENCE
Rolls-Royce Alert Service Bulletin No.
Page
Revision
RB.211–72–AE792, including Appendix A .........................................................
Total Pages: 31
All .............................................
4
Issued in Burlington, Massachusetts, on
November 12, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–27298 Filed 11–26–08; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1020 Directorate
Identifier 2008–CE–053–AD; Amendment
39–15751; AD 2008–24–11]
RIN 2120–AA64
Airworthiness Directives; Vulcanair
S.p.A. Model P68 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued 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:
dwashington3 on PROD1PC60 with RULES
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.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 2, 2009.
On January 2, 2009, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
14:57 Nov 26, 2008
Jkt 217001
August 2, 2007.
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
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:
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 required 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 AD.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 26, 2008 (73 FR
55786). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
BILLING CODE 4910–13–P
VerDate Aug<31>2005
Date
Costs of Compliance
Based on the service information, we
estimate that this AD will affect 72
products of U.S. registry. We also
estimate that it will take about 80 workhours per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Based on these figures, we estimate
the cost of this AD to the 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.
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.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
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 AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
dwashington3 on PROD1PC60 with RULES
■
2008–24–11 Vulcanair S.p.A.: Amendment
39–15751; Docket No. FAA–2008–1020;
Directorate Identifier 2008–CE–053–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 2, 2009.
Affected ADs
(b) None.
VerDate Aug<31>2005
14:57 Nov 26, 2008
Jkt 217001
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.
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.
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
January 2, 2009 (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 January 2, 2009
(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 January 2,
2009 (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 January 2, 2009 (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,
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72315
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.
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.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
(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.
DEPARTMENT OF TRANSPORTATION
The effective date of AD 2008–
20–05 remains October 27, 2008.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency AD No.: 2007–0027, dated
February 5, 2007, for related information.
repetitively inspecting the tailboom
attachment fittings, installing inspection
holes and attachment bolt washers,
modifying both access covers, and
replacing broken attachment bolts. This
document corrects the AD number that
is incorrectly listed as 2008–20–08 on
page 60104 of the AD.
RIN 2120–AA64
DATES:
Material Incorporated by Reference
(i) You must use Vulcanair S.p.A. Service
Bulletin No. 120 Rev. 1, dated June 7, 2006,
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Vulcanair S.p.A, Via G.
Pascoli, 7, Casoria (Naples), 80026 Italy;
telephone: +39 081 5918111; fax: +39 081
5918172; e-mail: info@vulcanair.com;
Internet: https://www.vulcanair.com.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on
November 19, 2008.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–27916 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
Eric
Schrieber, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification
Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712, telephone (562) 627–5348, fax
(562) 627–5210.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Discussion: On September 25, 2008,
we issued AD 2008–20–05 to amend 14
CFR part 39 to include an AD that
applies to MDHI Model 600N
helicopters. That AD requires modifying
the fuselage aft section, repetitively
inspecting the tailboom attachment
fittings, installing inspection holes and
attachment bolt washers, modifying
both access covers, and replacing
broken attachment bolts.
As published, AD 2008–20–05
contains an incorrect AD number (2008–
20–08) in the regulatory text on page
60104 of the AD. The correct AD
number is 2008–20–05.
No other part of the regulatory
information has been changed;
therefore, the AD is not republished in
the Federal Register.
Correction of Publication
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2008–0835; Directorate
Identifier 2008–SW–34–AD; Amendment 39–
15684; AD 2008–20–05]
Accordingly, the publication on
October 10, 2008 of Amendment 39–
15684, AD 2008–20–05, Docket No.
FAA–2008–0835, Directorate Identifier
2008–SW–34–AD (73 FR 60102), which
is the subject of FR Doc. E8–23540, is
corrected as follows:
RIN 2120–AA64
§ 39.13
Airworthiness Directives; MD
Helicopters, Inc. Model 600N
Helicopters
On page 60104, in the second column,
in the paragraph under § 39.13
[Amended], change ‘‘2008–20–08’’ to
read ‘‘2008–20–05’’.
Federal Aviation Administration
14 CFR Part 39
Federal Aviation
Administration, DOT.
ACTION: Final rule; correction.
dwashington3 on PROD1PC60 with RULES
AGENCY:
SUMMARY: This document corrects
airworthiness directive (AD) 2008–20–
05 which was published on October 10,
2008 (73 FR 60102) and applies to MD
Helicopters, Inc. (MDHI) Model 600N
helicopters. AD 2008–20–05 requires
modifying the fuselage aft section,
VerDate Aug<31>2005
14:57 Nov 26, 2008
Jkt 217001
[Corrected]
Issued in Fort Worth, Texas, on November
14, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–28108 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1238; Directorate
Identifier 2008–NM–181–AD; Amendment
39–15753; AD 2008–24–12]
Airworthiness Directives; Bombardier
Model BD–700–1A10 and BD–700–
1A11 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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:
During scheduled maintenance inspection,
a bolt which connects the PCU (power
control unit) to the elevator surface was
found fractured in the assembly. Further
inspection of the assembly revealed that the
bearing on the PCU rod end had seized,
which resulted in damage to the attachment
fitting bushing and fracture of the bolt.
Inspection of other in-service airplanes
revealed two more seized PCU attachment
joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of
the bolts in both PCUs on one side could
result in disconnection of the elevator control
surface which would lead to flutter and loss
of the aircraft.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
December 15, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 15, 2008.
We must receive comments on this
AD by December 29, 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.
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]]>Agencies
[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72314-72316]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-27916]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1020 Directorate Identifier 2008-CE-053-AD;
Amendment 39-15751; AD 2008-24-11]
RIN 2120-AA64
Airworthiness Directives; Vulcanair S.p.A. Model P68 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued 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.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 2, 2009.
On January 2, 2009, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 26, 2008
(73 FR 55786). That NPRM proposed 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This 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 required 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 AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect 72 products of U.S. registry. We also estimate that it will take
about 80 work-hours per product to comply with basic requirements of
this AD. The average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of this AD to the 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on
[[Page 72315]]
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 AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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2. The FAA amends Sec. 39.13 by adding the following new AD:
2008-24-11 Vulcanair S.p.A.: Amendment 39-15751; Docket No. FAA-
2008-1020; Directorate Identifier 2008-CE-053-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
2, 2009.
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.
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.
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
January 2, 2009 (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 January 2, 2009 (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 January 2, 2009
(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
January 2, 2009 (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.
[[Page 72316]]
(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, for related information.
Material Incorporated by Reference
(i) You must use Vulcanair S.p.A. Service Bulletin No. 120 Rev.
1, dated June 7, 2006, to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Vulcanair S.p.A, Via G. Pascoli, 7, Casoria (Naples), 80026 Italy;
telephone: +39 081 5918111; fax: +39 081 5918172; e-mail:
info@vulcanair.com; Internet: https://www.vulcanair.com.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on November 19, 2008.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-27916 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P
