Airworthiness Directives; Agusta S.p.A. Model AB 139 and AW 139 Helicopters, 39572-39574 [E8-14720]
Download as PDF
<![CDATA[
39572
Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations
horizontal stabilizer, part number (P/N) 206–
023–119–167, and Model 407 helicopters
with horizontal stabilizer, P/N 407–023–801–
109, installed, certificated in any category.
mstockstill on PROD1PC66 with RULES
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states:
‘‘Horizontal stabilizers part numbers 206–
023–119–167 and 407–023–801–109 may
have manufacturing flaws on the inside
surface of the upper and/or lower skin at the
tailboom attachment inserts. These flaws may
result in cracking of the skin and failure of
the horizontal stabilizer.’’
The manufacturer’s service information
states that in addition to cracks, the
horizontal stabilizer may have deformation or
debonding around and between the inserts.
This AD requires actions that are intended to
address all these unsafe conditions.
Actions and Compliance
(e) Within the next 100 hours time-inservice (TIS) or 30 days, whichever occurs
first, unless done previously.
(1) Determine whether you have an
affected serial numbered horizontal stabilizer
installed by removing the elevators from the
horizontal stabilizer. Access the horizontal
stabilizer identification tag containing the
horizontal stabilizer serial number as shown
in Figure 1 and remove the elevators by
following the Accomplishment Instructions,
Part I, of Bell Helicopter Textron Canada
(BHTC) Alert Service Bulletin (ASB) No.
206L–06–141, dated September 12, 2006,
applicable to the Model 206L series
helicopter (206L ASB) or BHTC ASB No.
407–06–72, dated September 12, 2006,
applicable to the Model 407 helicopters (407
ASB).
(2) If the serial number on the
identification tag is a serial number listed in
Table 1 of the 206L ASB or 407 ASB, inspect
the horizontal stabilizer as follows:
(i) Using a 10× or higher magnifying glass,
inspect the horizontal stabilizer for a crack or
deformation around the areas of the inserts.
Also, using a tap test method, inspect for
debonding between the inserts by following
the Accomplishment Instructions, Part II, of
either the 206L ASB or 407 ASB, as
applicable.
(ii) If you find a crack, deformation, or
debonding, replace the horizontal stabilizer
with an airworthy horizontal stabilizer that
does not have a serial number listed in Table
1 of the 206L ASB or 407 ASB. Replace the
horizontal stabilizer by following the
Accomplishment Instructions, Part III, of
either the 206L ASB or the 407 ASB, as
applicable.
(iii) If you do not find a crack, deformation,
or debonding, thereafter, at intervals not to
exceed 600 hours TIS or during each annual
inspection, whichever occurs first, repeat the
inspection required by paragraph (e)(2)(i) of
this AD.
(f) Replacing any horizontal stabilizer
containing a serial number listed in Table 1
of 206L ASB or 407 ASB with a horizontal
stabilizer that does not contain such a serial
number by following the Accomplishment
Instructions, Part III, of either the 206L ASB
or 407 ASB, as applicable, constitutes
VerDate Aug<31>2005
16:54 Jul 09, 2008
Jkt 214001
terminating actions for the requirements of
this AD.
Differences Between This AD and the MCAI
AD
(g) The MCAI requires compliance ‘‘within
the next 100 hours air time but no later than
9 May 2007.’’ This AD requires compliance
within the next 100 hours TIS or 30 days,
whichever occurs first, unless done
previously. Also, the MCAI requires
replacing the horizontal stabilizer by
September 30, 2008, and we have not
mandated a compliance time for replacing
the horizontal stabilizer.
Other Information
(h) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, 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 Sharon Miles, Aviation
Safety Engineer, FAA, Rotorcraft Directorate,
Regulations and Guidance Group, Fort
Worth, Texas 76193–0111, telephone (817)
222–5122, fax (817) 222–5961.
Related Information
(i) MCAI Transport Canada AD No. CF–
2007–03, dated March 27, 2007, contains
related information.
Air Transport Association of America (ATA)
Tracking Code
(j) ATA Code 5510: Horizontal Stabilizer
Structure.
Material Incorporated by Reference
(k) You must use the specified portions of
Bell Helicopter Textron Canada Alert Service
Bulletin No. 206L–06–141 or No. 407–06–72,
both dated September 12, 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 Bell Helicopter Textron
Canada, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4, telephone (450) 437–2862 or
(800) 363–8023, fax (450) 433–0272.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Fort Worth,
Texas 76193; 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 Fort Worth, Texas on June 19,
2008.
Judy I. Carl,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–14719 Filed 7–9–08; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0256; Directorate
Identifier 2007–SW–01–AD; Amendment 39–
15597; AD 2008–14–02]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model AB 139 and AW 139
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for Agusta
S.p.A. Model AB 139 and AW 139
helicopters. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by the
European Aviation Safety Agency
(EASA), the Technical Agent for Italy,
with which we have a bilateral
agreement, which indicates that the
Agusta AB 139’s and AW 139’s Fuselage
Frame 5700 middle section is prone to
fatigue damage. The actions are
intended to detect cracks in the fuselage
frame structure and to prevent structural
failure in this area.
DATES: This AD becomes effective on
August 14, 2008.
The incorporation by reference of
certain publications is approved by the
Director of the Federal Register as of
August 14, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
regulations.gov or in person at the
Docket Operations office, U.S.
Department of Transportation, M–30,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC between 9 a.m. and 5
p.m. Monday through Friday, except
Federal holidays.
You may get the service information
identified in this AD from Agusta,
21017 Cascina Costa di Samarate (VA)
Italy, Via Giovanni Agusta 520,
telephone 39 (0331) 229111, fax 39
(0331) 229605–222595.
Examining the AD Docket: The AD
docket contains the NPRM, the
economic evaluation, any comments
received, and other information. The
street address and operating hours for
the Docket Operations office (telephone
(800) 647–5227) are in the ADDRESSES
section of this AD. Comments will be
available in the AD docket shortly after
they are received.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
E:\FR\FM\10JYR1.SGM
10JYR1
Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
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 Agusta S.p.A. Model AB 139
and AW 139 helicopters. That NPRM
was published in the Federal Register
on March 7, 2008 (73 FR 12299). That
NPRM proposed to require repetitive
inspections of the fuselage frame
structure for a crack, and if a crack is
found, repairing the crack before further
flight in accordance with an FAAapproved procedure. You may obtain
further information by examining the
MCAI and any related service
information in the AD docket.
Comments
By publishing the NPRM, we gave the
public an opportunity to participate in
developing this AD. However, we
received no comment on the NPRM or
on our determination of the cost to the
public. Therefore, based on our review
and evaluation of the available data, we
have determined that air safety and the
public interest require adopting the AD
as proposed except for some formatting
changes. These changes will neither
increase the economic burden on any
operator nor increase the scope of this
AD.
Relevant Service Information
Agusta S.p.A. has issued Bollettino
Tecnico No. 139–018, Revision B, dated
October 18, 2006. The actions described
in the MCAI are intended to correct the
same unsafe condition as that identified
in the service information.
mstockstill on PROD1PC66 with RULES
Differences Between This AD and the
MCAI AD
This AD differs from the MCAI in that
the MCAI states ‘‘When damage or
cracks are found, before next flight,
contact the TC Holder for further
instructions.’’ This AD requires
repairing the crack before further flight
in accordance with an FAA-approved
procedure if a crack is found. Also, this
AD requires that the inspection be
performed based on ‘‘hours time-inservice’’ rather than ‘‘flight hours,’’ as
stated in the MCAI.
Costs of Compliance
We estimate that this AD will affect
about 17 helicopters of U.S. registry. We
also estimate that it will take about 1
work-hour per helicopter to comply
with the initial and each subsequent
VerDate Aug<31>2005
16:54 Jul 09, 2008
Jkt 214001
recurring inspection required by this
AD. The average labor rate is $80 per
work-hour. Assuming that 3 recurring
inspections will be performed on each
of the affected helicopters every year
after the initial inspection, and that 2 of
the affected helicopters will require
repairs to the fuselage middle frame
section at $10,000 per repair during the
service life of these helicopters, we
estimate the cost of this AD as follows:
• Initial Inspection Costs: 1 × 80 × 17
= $1360.
• Subsequent Recurring Inspection
Costs over the next 20 years: 1 × 3 × 20
× 80 × 17 = $81,600.
• Repair Costs: 2 × 10,000 = $20,000.
Based on these figures, we estimate
the cost of this AD on U.S. operators to
be $102,960, or $6,056 per helicopter.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
helicopters 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
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.
Therefore, I certify this 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.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
39573
§ 39.13
[Amended]
2. The FAA amends 39.13 by adding
the following new AD:
I
2008–14–02 Agusta S.p.A.: Amendment 39–
15597. Docket No. FAA–2008–0256;
Directorate Identifier 2007–SW–01–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on August 14, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Agusta S.p.A. Model
AB 139 and AW 139 helicopters, certificated
in any category.
Reason
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by the European Aviation Safety
Agency (EASA), the Technical Agent for
Italy, with which we have a bilateral
agreement, which indicates that the Agusta
AB/AW 139’s Fuselage Frame 5700 middle
section is prone to fatigue damage. These
fatigue cracks constitute an unsafe condition.
The actions are intended to detect cracks in
the fuselage frame structure and to prevent
structural failure in this area.
Actions and Compliance
(e) Required as indicated, unless already
done.
(1) Within the next 10 hours time-inservice (TIS), or upon accumulating 100
hours TIS since new, whichever occurs later,
inspect the fuselage frame 5700 middle
section in accordance with the Compliance
Instructions, pargraphs 1. through 4., of
Agusta Bollettino Tecnico No. 139–018,
Revision B, dated October 18, 2006;
(2) Thereafter, at intervals not exceeding
100 hours TIS, repeat the inspection as
required by paragraph (e)(1) of this AD.
(3) If a crack is found, before further flight,
repair the crack in accordance with an FAAapproved procedure.
E:\FR\FM\10JYR1.SGM
10JYR1
39574
Federal Register / Vol. 73, No. 133 / Thursday, July 10, 2008 / Rules and Regulations
Differences Between This AD and the MCAI
AD
DEPARTMENT OF TRANSPORTATION
(f) This AD differs from the MCAI as
follows:
(1) The MCAI states ‘‘When damage or
cracks are found, before next flight, contact
the TC Holder for further instructions.’’ If a
crack is found, this AD requires repairing the
crack before further flight in accordance with
an FAA-approved procedure.
(2) This AD requires that the inspection be
performed based on ‘‘hours time-in-service’’
not ‘‘flight hours.’’
Federal Aviation Administration
Other Information
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, FAA, FAA, ATTN: Sharon Miles,
Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Regulations and Guidance
Group, Fort Worth, Texas 76193–0111,
telephone (817) 222–5122, fax (817) 222–
5961, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
Related Information
(h) European Aviation Safety Agency
(EASA) Airworthiness Directive No. 2006–
0357, dated November 29, 2006, contains
related information.
Air Transport Association of America (ATA)
Tracking Code
(i) ATA Code 5700: Fuselage frame middle
section.
Material Incorporated by Reference
mstockstill on PROD1PC66 with RULES
(j) You must use the specified portions of
Agusta Bollettino Tecnico No. 139–018,
Revision B, dated October 18, 2006, to do the
actions required.
(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 Agusta, 21017 Cascina Costa
di Samarate (VA) Italy, Via Giovanni Agusta
520, telephone 39 (0331) 229111, fax 39
(0331) 229605–222595.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Fort Worth,
Texas 76193; 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 Fort Worth, Texas on June 19,
2008.
Judy Carl,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–14720 Filed 7–9–08; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
16:54 Jul 09, 2008
Jkt 214001
14 CFR Part 39
[Docket No. FAA–2007–0218; Directorate
Identifier 92–ANE–56–AD; Amendment 39–
15602; AD 2008–14–07]
RIN 2120–AA64
Airworthiness Directives; Lycoming
Engines, Fuel Injected Reciprocating
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
certain fuel injected reciprocating
engines manufactured by Lycoming
Engines. That AD currently requires
inspection, and replacement if
necessary, of externally mounted fuel
injector fuel lines. This AD requires the
same actions but adds additional engine
models and clarifies certain compliance
time wording. This AD also exempts
engines that have a Maintenance and
Overhaul Manual with an Airworthiness
Limitations Section that requires
inspection and replacement, if
necessary, of externally mounted fuel
injector lines. This AD results from
Lycoming Engines revising their
Mandatory Service Bulletin to add new
engine models requiring inspection, and
from the need to clarify a repetitive
inspection compliance time. We are
issuing this AD to prevent failure of the
fuel injector fuel lines that would allow
fuel to spray into the engine
compartment, resulting in an engine
fire.
DATES: This AD becomes effective
August 14, 2008. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of August 14, 2008.
ADDRESSES: You can get the service
information identified in this AD from
Lycoming Engines, 652 Oliver Street,
Williamsport, PA 17701, or go to
https://www.lycoming.textron.com.
The Docket Operations office is
located at Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
FOR FURTHER INFORMATION CONTACT:
Norm Perenson, Aerospace Engineer,
New York Aircraft Certification Office,
FAA, Engine & Propeller Directorate,
1600 Stewart Avenue, Suite 410,
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Westbury, NY 11590; e-mail:
Norman.perenson@faa.gov; telephone
(516) 228–7337; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
superseding AD 2002–26–01,
Amendment 39–12986 (67 FR 78965,
December 27, 2002), with a proposed
AD. The proposed AD applies to certain
fuel injected reciprocating engines
manufactured by Lycoming Engines. We
published the proposed AD in the
Federal Register on January 2, 2008 (73
FR 87). That action proposed to:
• Require the same actions as AD
2002–26–01; and
• Add additional engine models,
clarify certain compliance time
wording; and
• Exempt engines that have a
Maintenance and Overhaul Manual with
an Airworthiness Limitations Section
that requires inspection and
replacement, if necessary, of externally
mounted fuel injector lines.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
One commenter, a private citizen,
states that in the proposed AD, we wish
to exempt engines that have a
maintenance manual that deals with
this subject. He asks how the mechanic
is to know if an engine has a
maintenance manual, if the mechanic
does not have access to that manual,
unless we list the specific engines that
are not applicable to the proposed AD.
He states that we should either make the
AD applicable to fuel injected Lycoming
Engines and then list the applicable and
nonapplicable engines, or do not change
the AD.
We do not agree. If the engine has an
‘‘I’’ in the prefix of the engine model
and the engine has external fuel lines,
the fuel lines require inspection. For
engines that have a Maintenance
Manual, the required inspection will be
described in the Airworthiness
E:\FR\FM\10JYR1.SGM
10JYR1
]]>Agencies
[Federal Register Volume 73, Number 133 (Thursday, July 10, 2008)]
[Rules and Regulations]
[Pages 39572-39574]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14720]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0256; Directorate Identifier 2007-SW-01-AD;
Amendment 39-15597; AD 2008-14-02]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model AB 139 and AW 139
Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta
S.p.A. Model AB 139 and AW 139 helicopters. This AD results from
mandatory continuing airworthiness information (MCAI) issued by the
European Aviation Safety Agency (EASA), the Technical Agent for Italy,
with which we have a bilateral agreement, which indicates that the
Agusta AB 139's and AW 139's Fuselage Frame 5700 middle section is
prone to fatigue damage. The actions are intended to detect cracks in
the fuselage frame structure and to prevent structural failure in this
area.
DATES: This AD becomes effective on August 14, 2008.
The incorporation by reference of certain publications is approved
by the Director of the Federal Register as of August 14, 2008.
ADDRESSES: You may examine the AD docket on the Internet at https://
regulations.gov or in person at the Docket Operations office, U.S.
Department of Transportation, M-30, West Building Ground Floor, Room
W12-140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and
5 p.m. Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from
Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta
520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
Examining the AD Docket: The AD docket contains the NPRM, the
economic evaluation, any comments received, and other information. The
street address and operating hours for the Docket Operations office
(telephone (800) 647-5227) are in the ADDRESSES section of this AD.
Comments will be available in the AD docket shortly after they are
received.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer,
[[Page 39573]]
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.
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 Agusta S.p.A. Model AB 139
and AW 139 helicopters. That NPRM was published in the Federal Register
on March 7, 2008 (73 FR 12299). That NPRM proposed to require
repetitive inspections of the fuselage frame structure for a crack, and
if a crack is found, repairing the crack before further flight in
accordance with an FAA-approved procedure. You may obtain further
information by examining the MCAI and any related service information
in the AD docket.
Comments
By publishing the NPRM, we gave the public an opportunity to
participate in developing this AD. However, we received no comment on
the NPRM or on our determination of the cost to the public. Therefore,
based on our review and evaluation of the available data, we have
determined that air safety and the public interest require adopting the
AD as proposed except for some formatting changes. These changes will
neither increase the economic burden on any operator nor increase the
scope of this AD.
Relevant Service Information
Agusta S.p.A. has issued Bollettino Tecnico No. 139-018, Revision
B, dated October 18, 2006. The actions described in the MCAI are
intended to correct the same unsafe condition as that identified in the
service information.
Differences Between This AD and the MCAI AD
This AD differs from the MCAI in that the MCAI states ``When damage
or cracks are found, before next flight, contact the TC Holder for
further instructions.'' This AD requires repairing the crack before
further flight in accordance with an FAA-approved procedure if a crack
is found. Also, this AD requires that the inspection be performed based
on ``hours time-in-service'' rather than ``flight hours,'' as stated in
the MCAI.
Costs of Compliance
We estimate that this AD will affect about 17 helicopters of U.S.
registry. We also estimate that it will take about 1 work-hour per
helicopter to comply with the initial and each subsequent recurring
inspection required by this AD. The average labor rate is $80 per work-
hour. Assuming that 3 recurring inspections will be performed on each
of the affected helicopters every year after the initial inspection,
and that 2 of the affected helicopters will require repairs to the
fuselage middle frame section at $10,000 per repair during the service
life of these helicopters, we estimate the cost of this AD as follows:
Initial Inspection Costs: 1 x 80 x 17 = $1360.
Subsequent Recurring Inspection Costs over the next 20
years: 1 x 3 x 20 x 80 x 17 = $81,600.
Repair Costs: 2 x 10,000 = $20,000.
Based on these figures, we estimate the cost of this AD on U.S.
operators to be $102,960, or $6,056 per helicopter.
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 helicopters 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 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.
Therefore, I certify this 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 an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends 39.13 by adding the following new AD:
2008-14-02 Agusta S.p.A.: Amendment 39-15597. Docket No. FAA-2008-
0256; Directorate Identifier 2007-SW-01-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective on
August 14, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Agusta S.p.A. Model AB 139 and AW 139
helicopters, certificated in any category.
Reason
(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the European Aviation Safety Agency
(EASA), the Technical Agent for Italy, with which we have a
bilateral agreement, which indicates that the Agusta AB/AW 139's
Fuselage Frame 5700 middle section is prone to fatigue damage. These
fatigue cracks constitute an unsafe condition. The actions are
intended to detect cracks in the fuselage frame structure and to
prevent structural failure in this area.
Actions and Compliance
(e) Required as indicated, unless already done.
(1) Within the next 10 hours time-in-service (TIS), or upon
accumulating 100 hours TIS since new, whichever occurs later,
inspect the fuselage frame 5700 middle section in accordance with
the Compliance Instructions, pargraphs 1. through 4., of Agusta
Bollettino Tecnico No. 139-018, Revision B, dated October 18, 2006;
(2) Thereafter, at intervals not exceeding 100 hours TIS, repeat
the inspection as required by paragraph (e)(1) of this AD.
(3) If a crack is found, before further flight, repair the crack
in accordance with an FAA-approved procedure.
[[Page 39574]]
Differences Between This AD and the MCAI AD
(f) This AD differs from the MCAI as follows:
(1) The MCAI states ``When damage or cracks are found, before
next flight, contact the TC Holder for further instructions.'' If a
crack is found, this AD requires repairing the crack before further
flight in accordance with an FAA-approved procedure.
(2) This AD requires that the inspection be performed based on
``hours time-in-service'' not ``flight hours.''
Other Information
(g) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, FAA, FAA, ATTN: Sharon Miles, Aviation
Safety Engineer, FAA, Rotorcraft Directorate, Regulations and
Guidance Group, Fort Worth, Texas 76193-0111, telephone (817) 222-
5122, fax (817) 222-5961, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Related Information
(h) European Aviation Safety Agency (EASA) Airworthiness
Directive No. 2006-0357, dated November 29, 2006, contains related
information.
Air Transport Association of America (ATA) Tracking Code
(i) ATA Code 5700: Fuselage frame middle section.
Material Incorporated by Reference
(j) You must use the specified portions of Agusta Bollettino
Tecnico No. 139-018, Revision B, dated October 18, 2006, to do the
actions required.
(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
Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
(3) You may review copies at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas
76193; 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 Fort Worth, Texas on June 19, 2008.
Judy Carl,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-14720 Filed 7-9-08; 8:45 am]
BILLING CODE 4910-13-P
