Airworthiness Directives; Agusta S.p.A. Helicopters, 28727-28729 [2013-10903]
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
Docket No. FAA–2012–0221; Directorate
Identifier 2010–SW–082–AD.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2013–10–01 Spectrolab Nightsun XP
Searchlight: Amendment 39–17454;
(a) Applicability
This AD applies to Spectrolab Nightsun XP
Searchlight Assembly Systems with gimbal
assembly part number (P/N) 033295–1 or
033295–2, installed on, but not limited to,
Agusta S.p.A. Model AB139 and Model
AW139 helicopters, Sikorsky Aircraft
Corporation Model S–92A helicopters, and
Eurocopter Deutschland GmbH Model EC135
and Model MBB–BK 117 C–2 helicopters,
certificated in any category. The searchlight
assembly system P/Ns and revision level
using one of the two affected gimbal
assembly P/Ns are listed in Table 1 to
Paragraph (a) of this AD.
TABLE 1 TO PARAGRAPH (A)—AFFECTED SYSTEMS AND P/N
Affected
revisions
System P/N
Nomenclature
033338 ......................................
033338–3 ..................................
033338–4 ..................................
033704 ......................................
033704–1 ..................................
Nightsun XP Searchlight System ..................................................................................................
Nightsun XP Searchlight System ..................................................................................................
Nightsun XP Searchlight System ..................................................................................................
IFCO Nightsun XP Searchlight System .........................................................................................
IFCO Nightsun XP Searchlight System .........................................................................................
(b) Unsafe Condition
This AD defines the unsafe condition as
the Searchlight/Gimbal disconnecting from
the helicopter and remaining attached solely
by the internal cable harness, or separating
totally. This condition could result in
damage to the helicopter and injury to
persons on the ground.
in accordance with Nightsun XP Searchlight
System Kit and Procedure to Incorporate
EASA AD 2010–0183 Conformance, 034374
Revision NC, approved September 28, 2010,
steps 1 through 13.
(6) Accomplishing paragraph (e)(5) of this
AD is terminating action for the requirements
of this AD.
(c) Effective Date
This AD becomes effective June 20, 2013.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller,
Senior Aviation Safety Engineer, Safety
Management Group, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5110;
email matthew.fuller@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
erowe on DSK2VPTVN1PROD with RULES
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Before further flight, insert a copy of
Nightsun XP Searchlight Safety and Service
Bulletin No. SL 0810–01, Amendment No. 2,
dated September 24, 2010, into the Normal
Procedures section of the Rotorcraft Flight
Manual.
(2) Before the first flight of each day,
visually check the searchlight installation for
a gap between the top shroud rubber edging,
P/N 033381, and the side covers, P/N 033286,
with slight pressure applied to either side of
the searchlight. The edging must remain in
physical contact with the side covers when
slight pressure is applied to the searchlight.
(3) The actions required by paragraph (e)(2)
of this AD may be performed by the owner/
operator (pilot) holding at least a Private Pilot
Certificate, and must be entered into the
helicopter maintenance records in
accordance with 14 CFR 43.9(a)(1)–(4) and
91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439.
(4) If the edging does not remain in
physical contact with the side cover when
slight pressure is applied to the searchlight
in accordance with the requirements of
paragraph (e)(2) of this AD, before further
flight, with an affected Spectrolab Nightsun
XP Searchlight assembly system installed,
modify and re-identify the gimbal assembly
in accordance with paragraph (e)(5) of this
AD.
(5) Within 100 hours time-in-service,
modify and re-identify the gimbal assembly
VerDate Mar<15>2010
14:43 May 15, 2013
Jkt 229001
A
A
A
A
A
through
through
through
through
through
D.
D.
D.
C.
C.
this document is identified only in the
Change Record on page 2 of this service
information.
(3) For Spectrolab Nightsun XP Searchlight
service information identified in this AD,
contact Spectrolab, Inc. ATTN: Saul Vargas,
12500 Gladstone Ave., Sylmar, CA 91342,
telephone (818) 365–4611, fax (818) 361–
5102, or on the internet at https://
www.spectrolab.com.
(4) You may review a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(5) You may also review a copy of this
service information that is incorporated by
reference 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 April 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2010–0237R2, dated December 14, 2010.
[FR Doc. 2013–11383 Filed 5–15–13; 8:45 am]
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 3340, Exterior lighting.
DEPARTMENT OF TRANSPORTATION
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the following service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this information as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) Nightsun XP Searchlight Safety and
Service Bulletin No. SL 0810–01,
Amendment No. 2, dated September 24,
2010.
(ii) Nightsun XP Searchlight System Kit
and Procedure to Incorporate EASA AD
2010–0183 Conformance, 034374 Revision
NC, dated September 28, 2010. The date of
14 CFR Part 39
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BILLING CODE 4910–13–P
Federal Aviation Administration
[Docket No. FAA–2012–0695; Directorate
Identifier 2011–SW–031–AD; Amendment
39–17448; AD 2013–09–06]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
SUMMARY:
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
erowe on DSK2VPTVN1PROD with RULES
Agusta S.p.A. (Agusta) Model A119 and
AW119 MKII helicopters. The existing
AD currently requires inspecting the
pilot and copilot engine rotary variable
differential transformer (RVDT) control
box assemblies to determine if the
control gear locking pin is in its proper
position. Since we issued that AD,
Agusta has developed a terminating
action for this inspection. This AD
requires the same actions as the existing
AD as well as modifying the RVDT
control box assemblies. The actions of
this AD are intended to prevent failure
of an RVDT control box assembly, loss
of manual control of the engine throttle,
and subsequent loss of control of the
helicopter.
DATES: This AD is effective June 20,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of June 20, 2013.
ADDRESSES: For service information
identified in this AD, contact Agusta
Westland, Customer Support & Services,
Via Per Tornavento 15, 21019 Somma
Lombardo (VA) Italy, Attn: Giovanni
Cecchelli; telephone 39 0331711133; fax
39 0331 711180; or at https://
www.agustawestland.com/technicalbullettins. You may review the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
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, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 3, 2012, at 77 FR 39444, the
Federal Register published our notice of
VerDate Mar<15>2010
14:43 May 15, 2013
Jkt 229001
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
supersede AD 2010–15–51 (75 FR
50863, August 18, 2010). The NPRM
would apply to Agusta model A119 and
AW119 MKII helicopters and proposed
to require repetitively inspecting the
pilot and co-pilot control box
assemblies for the proper positioning of
the locking pins, and if the locking pin
is recessed or extended in excess of 2.0
millimeters from the face of the pin
bore, or missing, replacing the control
box assembly. Additionally, the NPRM
proposed to require modifying the pilot
and co-pilot control box assemblies to
terminate the repetitive inspection
requirements. The proposed
requirements were intended to prevent
failure of an RVDT control box
assembly, loss of manual control of the
engine throttle, and subsequent loss of
control of the helicopter.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2011–
0095–E, dated May 24, 2011, to
permanently correct the unsafe
condition addressed in AD 2010–15–51
(75 FR 50863, August 18, 2010) for the
Agusta A119 and AW MKII helicopters.
EASA advises that Agusta has
developed a modification to the pilot
and co-pilot control box assemblies that
will ‘‘remedy the problem and prevent
recurrence.’’ This EASA AD requires
repetitive inspections of the affected
pilot and co-pilot control box
assemblies until a terminating action
modification is made within 8 calendar
months of the effective date of the EASA
AD.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 39444, July 3, 2012).
FAA’s Determination
These helicopters have been approved
by the aviation authority of Italy and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with Italy, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
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Fmt 4700
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Related Service Information
We reviewed Agusta Alert Bollettino
Tecnico (ABT) No. 119–39 Revision A,
dated May 23, 2011 (ABT 119–39). The
ABT 119–39 describes procedures for
repetitively inspecting the pilot and copilot control box assemblies for correct
positioning of the engine RVDT control
gear locking pin and provides
instructions on how to modify the pilot
and co-pilot control box assemblies to
terminate the repetitive inspections.
EASA classified this ABT as mandatory
and issued EAD No. 2011–0095–E,
dated May 24, 2011, to ensure the
continued airworthiness of these
helicopters.
Costs of Compliance
We estimate that this AD will affect
49 helicopters of U.S. Registry. We
estimate that operators will incur the
following costs in order to comply with
this AD. At an average labor rate of $85
per work hour, inspecting the two RVDT
control box assemblies will require
about 1.5 hours, for a cost per helicopter
of about $128 and a cost to the U.S. fleet
of about $6,272 per inspection cycle.
Modification of the pilot and co-pilot
RVDT control box assemblies will
require about 8 hours, and required
parts will cost about $8, for a total cost
per helicopter of $688 and a cost to the
U.S. fleet of $33,712.
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
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
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
responsibilities among the various
levels of government.
specified compliance time unless it has
already been accomplished prior to that time.
For the reasons discussed above, I certify
that 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);
(3) Will not affect intrastate aviation in
Alaska to the extent that it justifies making
a regulatory distinction; and
(4) 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.
(f) Required Actions
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
removing airworthiness directive (AD)
2010–15–51, Amendment 39–16397 (75
FR 50863, August 18, 2010), and adding
the following new AD:
■
2013–09–06 Agusta S.p.A.: Amendment 39–
17448; Docket No. FAA–2012–0695;
Directorate Identifier 2011–SW–031–AD.
(a) Applicability
This AD applies to Agusta Model A119 and
AW119 MKII helicopters, with pilot control
box assembly (control box), part number
(P/N) 109–0010–81–103, and co-pilot control
box, P/N 109–0010–81–107, installed,
certificated in any category.
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(b) Unsafe Condition
This AD defines the unsafe condition as a
rotary variable differential transformer
(RVDT) locking pin, which could move out
of position and result in loss of manual
throttle control of the engine and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010–15–51,
Amendment 39–16397 (75 FR 50863, August
18, 2010).
(d) Effective Date
This AD becomes effective June 20, 2013.
(e) Compliance
You are responsible for performing each
action required by this AD within the
VerDate Mar<15>2010
14:43 May 15, 2013
Jkt 229001
(1) Within 5 hours time-in-service (TIS),
and thereafter at intervals not to exceed 50
hours TIS, remove the cover of the pilot and
co-pilot RVDT control box assemblies and
inspect the locking pins for proper position
by following the Compliance Instructions,
Parts I and II, paragraphs 2. through 4.1 for
the pilot control box assembly and
paragraphs 5. through 7.1 for the co-pilot
control box assembly, of Agusta Bollettino
Tecnico No. 119–39, Revision A, dated May
23, 2011.
(2) If during the inspection the locking pin
is recessed or extended in excess of 2.0
millimeters from the face of the pin bore, or
missing, before further flight, replace the
RVDT control box with an airworthy RVDT
control box that has been modified in
accordance with paragraph (f)(3) of this AD.
(3) Within 8 months,
(i) Modify the pilot RVDT control box
assembly, P/N 109–0010–81–103, by
reference to Figures 1 through 7 and in
accordance with the Compliance
Instructions, Part III, paragraphs 5.1 through
5.16 of Agusta Bollettino Tecnico No. 119–
39 Revision A, dated May 23, 2011; and
(ii) Modify the co-pilot RVDT control box
assembly, P/N 109–0010–81–107, by
reference to Figures 1 through 7 and in
accordance with the Compliance
Instructions, Part III, paragraphs 3.1 through
3.16 of Agusta Bollettino Tecnico No. 119–
39, Revision A, dated May 23, 2011.
(4) Modifying the pilot and copilot RVDT
control box assemblies in accordance with
paragraph (f)(3) of this AD constitutes
terminating action for the requirements of
this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5110; email robert.grant@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD 2011–
0095–E, dated May 24, 2011.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6700: Rotors Flight Control.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
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28729
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Agusta Bollettino Tecnico No. 119–39
Revision A, dated May 23, 2011.
(ii) Reserved.
(3) For Agusta service information
identified in this AD, contact Agusta
Westland, Customer Support & Services, Via
Per Tornavento 15, 21019 Somma Lombardo
(VA) Italy, ATTN: Giovanni Cecchelli;
telephone 39–0331–711133; fax 39 0331
711180; or at https://
www.agustawestland.com/technicalbullettins.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference 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/ibrlocations.html.
Issued in Fort Worth, Texas, on April 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–10903 Filed 5–15–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1109; Directorate
Identifier 2011–NM–172–AD; Amendment
39–17455; AD 2013–10–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain The Boeing Company Model
757–200 and –200PF series airplanes.
That AD currently requires modifying
the nacelle strut and wing structure, and
repairing any damage found during the
modification. This new AD specifies a
maximum compliance time limit that
overrides the optional threshold formula
results. This AD was prompted by
reports indicating that the actual
operational loads applied to the nacelle
are higher than the analytical loads that
SUMMARY:
E:\FR\FM\16MYR1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 95 (Thursday, May 16, 2013)]
[Rules and Regulations]
[Pages 28727-28729]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10903]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0695; Directorate Identifier 2011-SW-031-AD;
Amendment 39-17448; AD 2013-09-06]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for
[[Page 28728]]
Agusta S.p.A. (Agusta) Model A119 and AW119 MKII helicopters. The
existing AD currently requires inspecting the pilot and copilot engine
rotary variable differential transformer (RVDT) control box assemblies
to determine if the control gear locking pin is in its proper position.
Since we issued that AD, Agusta has developed a terminating action for
this inspection. This AD requires the same actions as the existing AD
as well as modifying the RVDT control box assemblies. The actions of
this AD are intended to prevent failure of an RVDT control box
assembly, loss of manual control of the engine throttle, and subsequent
loss of control of the helicopter.
DATES: This AD is effective June 20, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of June 20, 2013.
ADDRESSES: For service information identified in this AD, contact
Agusta Westland, Customer Support & Services, Via Per Tornavento 15,
21019 Somma Lombardo (VA) Italy, Attn: Giovanni Cecchelli; telephone 39
0331711133; fax 39 0331 711180; or at https://www.agustawestland.com/technical-bullettins. You may review the referenced service information
at the FAA, Office of the Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137.
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, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone: 800-647-5527) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 3, 2012, at 77 FR 39444, the Federal Register published our
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR
part 39 to supersede AD 2010-15-51 (75 FR 50863, August 18, 2010). The
NPRM would apply to Agusta model A119 and AW119 MKII helicopters and
proposed to require repetitively inspecting the pilot and co-pilot
control box assemblies for the proper positioning of the locking pins,
and if the locking pin is recessed or extended in excess of 2.0
millimeters from the face of the pin bore, or missing, replacing the
control box assembly. Additionally, the NPRM proposed to require
modifying the pilot and co-pilot control box assemblies to terminate
the repetitive inspection requirements. The proposed requirements were
intended to prevent failure of an RVDT control box assembly, loss of
manual control of the engine throttle, and subsequent loss of control
of the helicopter.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2011-0095-E, dated May 24, 2011, to permanently correct the unsafe
condition addressed in AD 2010-15-51 (75 FR 50863, August 18, 2010) for
the Agusta A119 and AW MKII helicopters. EASA advises that Agusta has
developed a modification to the pilot and co-pilot control box
assemblies that will ``remedy the problem and prevent recurrence.''
This EASA AD requires repetitive inspections of the affected pilot and
co-pilot control box assemblies until a terminating action modification
is made within 8 calendar months of the effective date of the EASA AD.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 39444,
July 3, 2012).
FAA's Determination
These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, EASA, its technical representative,
has notified us of the unsafe condition described in the EASA AD. We
are issuing this AD because we evaluated all information provided by
EASA and determined the unsafe condition exists and is likely to exist
or develop on other helicopters of these same type designs and that air
safety and the public interest require adopting the AD requirements as
proposed.
Related Service Information
We reviewed Agusta Alert Bollettino Tecnico (ABT) No. 119-39
Revision A, dated May 23, 2011 (ABT 119-39). The ABT 119-39 describes
procedures for repetitively inspecting the pilot and co-pilot control
box assemblies for correct positioning of the engine RVDT control gear
locking pin and provides instructions on how to modify the pilot and
co-pilot control box assemblies to terminate the repetitive
inspections. EASA classified this ABT as mandatory and issued EAD No.
2011-0095-E, dated May 24, 2011, to ensure the continued airworthiness
of these helicopters.
Costs of Compliance
We estimate that this AD will affect 49 helicopters of U.S.
Registry. We estimate that operators will incur the following costs in
order to comply with this AD. At an average labor rate of $85 per work
hour, inspecting the two RVDT control box assemblies will require about
1.5 hours, for a cost per helicopter of about $128 and a cost to the
U.S. fleet of about $6,272 per inspection cycle. Modification of the
pilot and co-pilot RVDT control box assemblies will require about 8
hours, and required parts will cost about $8, for a total cost per
helicopter of $688 and a cost to the U.S. fleet of $33,712.
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
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
[[Page 28729]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that 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);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) 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
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-15-51, Amendment 39-16397 (75 FR 50863, August 18, 2010), and
adding the following new AD:
2013-09-06 Agusta S.p.A.: Amendment 39-17448; Docket No. FAA-2012-
0695; Directorate Identifier 2011-SW-031-AD.
(a) Applicability
This AD applies to Agusta Model A119 and AW119 MKII helicopters,
with pilot control box assembly (control box), part number (P/N)
109-0010-81-103, and co-pilot control box, P/N 109-0010-81-107,
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a rotary variable
differential transformer (RVDT) locking pin, which could move out of
position and result in loss of manual throttle control of the engine
and subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010-15-51, Amendment 39-16397 (75 FR
50863, August 18, 2010).
(d) Effective Date
This AD becomes effective June 20, 2013.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Within 5 hours time-in-service (TIS), and thereafter at
intervals not to exceed 50 hours TIS, remove the cover of the pilot
and co-pilot RVDT control box assemblies and inspect the locking
pins for proper position by following the Compliance Instructions,
Parts I and II, paragraphs 2. through 4.1 for the pilot control box
assembly and paragraphs 5. through 7.1 for the co-pilot control box
assembly, of Agusta Bollettino Tecnico No. 119-39, Revision A, dated
May 23, 2011.
(2) If during the inspection the locking pin is recessed or
extended in excess of 2.0 millimeters from the face of the pin bore,
or missing, before further flight, replace the RVDT control box with
an airworthy RVDT control box that has been modified in accordance
with paragraph (f)(3) of this AD.
(3) Within 8 months,
(i) Modify the pilot RVDT control box assembly, P/N 109-0010-81-
103, by reference to Figures 1 through 7 and in accordance with the
Compliance Instructions, Part III, paragraphs 5.1 through 5.16 of
Agusta Bollettino Tecnico No. 119-39 Revision A, dated May 23, 2011;
and
(ii) Modify the co-pilot RVDT control box assembly, P/N 109-
0010-81-107, by reference to Figures 1 through 7 and in accordance
with the Compliance Instructions, Part III, paragraphs 3.1 through
3.16 of Agusta Bollettino Tecnico No. 119-39, Revision A, dated May
23, 2011.
(4) Modifying the pilot and copilot RVDT control box assemblies
in accordance with paragraph (f)(3) of this AD constitutes
terminating action for the requirements of this AD.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222-5110; email
robert.grant@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency AD 2011-0095-E, dated May 24, 2011.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6700: Rotors
Flight Control.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Agusta Bollettino Tecnico No. 119-39 Revision A, dated May
23, 2011.
(ii) Reserved.
(3) For Agusta service information identified in this AD,
contact Agusta Westland, Customer Support & Services, Via Per
Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni
Cecchelli; telephone 39-0331-711133; fax 39 0331 711180; or at
https://www.agustawestland.com/technical-bullettins.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference 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 April 26, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10903 Filed 5-15-13; 8:45 am]
BILLING CODE 4910-13-P
