Airworthiness Directives; Agusta S.p.A. Model A119 and AW119 MKII Helicopters, 50863-50865 [2010-19816]
Download as PDF
Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on July 27,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–19696 Filed 8–17–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0806; Directorate
Identifier 2010–SW–071–AD; Amendment
39–16397; AD 2010–15–51]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A119 and AW119 MKII
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
AGENCY:
This document publishes in
the Federal Register an amendment
adopting Airworthiness Directive (AD)
2010–15–51, which was sent previously
to all known U.S. owners and operators
of Agusta S.p.A. (Agusta) Model A119
and AW119 MKII helicopters by
individual letters. This AD requires,
within 5 hours time-in-service (TIS),
and thereafter at intervals not to exceed
50 hours TIS, removing the cover of
each pilot and co-pilot control box
assembly (control box) and inspecting
each rotary variable differential
transformer (RVDT) control gear locking
pin (locking pin) for proper position. If
a locking pin is recessed, extended, or
missing, this AD requires replacing the
control box before further flight. This
amendment is prompted by a report that
an RVDT locking pin that was installed
on a Model AW119 MKII helicopter
moved from its proper position,
resulting in loss of connectivity of the
pilot and co-pilot throttle controls. The
actions specified by this AD are
intended to prevent the RVDT locking
pin from moving from its proper
position, which could lead to loss of
manual engine throttle control, and
subsequent loss of control of the
helicopter.
DATES: Effective September 2, 2010, to
all persons except those persons to
erowe on DSK5CLS3C1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
15:12 Aug 17, 2010
Jkt 220001
whom it was made immediately
effective by Emergency AD 2010–15–51,
issued on July 16, 2010, which
contained the requirements of this
amendment.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of September
2, 2010.
Comments for inclusion in the Rules
Docket must be received on or before
October 18, 2010.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may get the service information
identified in this AD from Agusta, Via
Giovanni Agusta, 520 21017 Cascina
Costa di Samarate (VA), Italy, telephone
39 0331–229111, fax 39 0331–229605/
222595, or at https://
customersupport.agusta.com/
technical_advice.php.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information 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 Docket
Operations office (telephone (800) 647–
5527) is located in Room W12–140 on
the ground floor of the West Building at
the street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Rao
Edupuganti, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Policy Group, 2601 Meacham Blvd.,
Fort Worth, Texas 76137, telephone
(817) 222–4389, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: On July
16, 2010, we issued Emergency AD
2010–15–51 for the specified model
helicopters, which requires, within 5
hours TIS, and thereafter at intervals not
to exceed 50 hours TIS, removing the
cover of the pilot and co-pilot control
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
50863
boxes and inspecting each RVDT
locking pin for proper position. If a
locking pin is recessed, extended, or
missing, the AD requires replacing the
control box before further flight. That
action was prompted by a report that an
RVDT locking pin that was installed on
a Model AW119 MKII helicopter moved
from its proper position, resulting in
loss of connectivity of the pilot and copilot throttle controls. Investigation
revealed that the pilot’s locking pin had
moved from its proper position, which
resulted in the loss of the co-pilot
throttle control. This condition, if not
detected and corrected, could result in
loss of manual engine throttle control,
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
Community, notified us that an unsafe
condition may exist on Agusta Model
A119 and AW119 MKII helicopters.
EASA advises of a nonconformity of
certain control boxes, unseating of a
locking pin, and loss of the pilot and copilot engine throttle synchronicity.
EASA states this condition, if not
detected and corrected, could lead to
the loss of manual engine throttle
control and consequent loss of control
of the helicopter.
Agusta has issued Alert Bollettino
Tecnico No. 119–39, dated July 2, 2010
(ABT). The ABT describes procedures
for inspecting the pilot and co-pilot
control box for correct positioning of the
locking pin. The ABT states that the
investigation is still in progress to find
a solution to the malfunction. The
instructions in the ABT are prescribed
as precautionary pending future
corrective action. EASA classified this
ABT as mandatory and issued
Emergency AD 2010–0142–E, dated July
5, 2010, to ensure the continued
airworthiness of these helicopters. This
AD differs from EASA Emergency AD
No. 2010–0142–E in that we use the
term ‘‘hours time-in-service’’ rather than
‘‘flight hours.’’ Also, we clarify the
inspection requirements and do not use
the calendar date of August 31, 2010 as
a required compliance time.
These helicopter models are
manufactured in Italy and are type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, EASA has kept the
FAA informed of the situation
described. We have examined the
findings of EASA, reviewed all available
information, and determined that AD
action is necessary for products of these
E:\FR\FM\18AUR1.SGM
18AUR1
erowe on DSK5CLS3C1PROD with RULES
50864
Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
type designs that are certificated for
operation in the United States.
Since the unsafe condition described
is likely to exist or develop on other
Agusta Model A119 and AW119 MKII
helicopters of the same type design, we
issued Emergency AD 2010–15–51 to
detect a missing or improperly fitted
RVDT locking pin, which could lead to
loss of manual engine throttle control,
and subsequent loss of control of the
helicopter. The AD requires, within 5
hours TIS, and thereafter at intervals not
to exceed 50 hours TIS, removing the
cover of the pilot and co-pilot control
boxes and inspecting the locking pins
for proper position. If 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,
replacing the control box with an
airworthy control box that has been
inspected in accordance with paragraph
(a) of the AD is required. Replacing the
control box does not constitute
terminating action for the inspection
requirements of the AD. The actions
must be accomplished in accordance
with specified portions of the ABT
described previously.
The short compliance time involved
is required because the previously
described critical unsafe condition can
adversely affect the controllability of the
helicopter. The actions previously
described are required within short
compliance times: 5 hours TIS and then
at intervals not to exceed 50 hours TIS
for the initial and repetitive inspections
and before further flight for any required
control box replacement; therefore, this
AD must be issued immediately.
Since it was found that immediate
corrective action was required, notice
and opportunity for prior public
comment thereon were impracticable
and contrary to the public interest, and
good cause existed to make the AD
effective immediately by individual
letters issued on July 16, 2010 to all
known U.S. owners and operators of
Agusta Model A119 and AW119 MKII
helicopters. These conditions still exist,
and the AD is hereby published in the
Federal Register as an amendment to 14
CFR 39.13 to make it effective to all
persons.
We estimate that this AD will affect
32 helicopters of U.S. registry. Each
inspection of both control boxes will
take 11⁄2 hours and each control box
replacement will take approximately 8
work hours (2 per helicopter). The
average labor rate is $85 per work hour.
It will cost approximately $12,852 for a
pilot control box and $11,768 for a copilot control box. Based on these
figures, we estimate the total cost
impact of the AD on U.S. operators to
VerDate Mar<15>2010
15:12 Aug 17, 2010
Jkt 220001
be $835,440 ($26,108 per helicopter,
assuming 1 inspection of each control
box and replacing both control boxes on
each helicopter).
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2010–0806;
Directorate Identifier 2010–SW–071–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of our docket web site,
you can find and read the comments to
any of our dockets, including the name
of the individual who sent the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78).
Fmt 4700
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
We have 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.
For the reasons discussed above, I
certify that the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
Frm 00020
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
PO 00000
Authority for This Rulemaking
Sfmt 4700
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
■
2010–15–51 Agusta S.p.A.: Amendment 39–
16397. Docket No. FAA–2010–0806;
Directorate Identifier 2010–SW–071–AD.
Applicability: 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.
Compliance: Required as indicated.
To detect a missing, or improperly fitted,
engine rotary variable differential transformer
(RVDT) control gear locking pin (locking
pin), P/N MS16555–628, which could lead to
loss of manual engine throttle control, and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Within 5 hours time-in-service (TIS)
unless accomplished previously, and
thereafter at intervals not to exceed 50 hours
TIS, remove the cover of the pilot and copilot control boxes and inspect the locking
E:\FR\FM\18AUR1.SGM
18AUR1
Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
erowe on DSK5CLS3C1PROD with RULES
pins for proper position by following the
Compliance Instructions, Parts I and II,
paragraphs 2. through 4.1 for the pilot control
box and paragraphs 5. through 7.1 for the copilot control box, in Agusta Alert Bollettino
Tecnico No. 119–39, dated July 2, 2010.
(b) If 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 control box with an
airworthy control box that has been
inspected in accordance with paragraph (a) of
this AD. Replacing the control box does not
constitute terminating action for the
inspection requirements of this AD.
(c) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Safety
Management Group, FAA, ATTN: Rao
Edupuganti, Aviation Safety Engineer,
Rotorcraft Directorate, Regulations and Policy
Group, 2601 Meacham Blvd., Fort Worth,
Texas 76137, telephone (817) 222–4389, fax
(817) 222–5961, for information about
previously approved alternative methods of
compliance.
(d) The Joint Aircraft System/Component
(JASC) Code is 6700: Rotors Flight Control.
(e) The inspections shall be done in
accordance with the specified portions of
Agusta Alert Bollettino Tecnico No. 119–39,
dated July 2, 2010. The Director of the
Federal Register approved this incorporation
by reference in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be
obtained from Agusta, Via Giovanni Agusta,
520 21017 Cascina Costa di Samarate (VA),
Italy, telephone 39 0331–229111, fax 39
0331–229605/222595, or at https://
customersupport.agusta.com/
technical_advice.php. Copies may be
inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 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/
code_of_federal_regulations/
ibr_locations.html.
(f) This amendment becomes effective on
September 2, 2010, to all persons except
those persons to whom it was made
immediately effective by Emergency AD
2010–15–51, issued July 16, 2010, which
contained the requirements of this
amendment.
Note: The subject of this AD is addressed
in European Aviation Safety Agency AD
2010–0142–E, dated July 5, 2010.
Issued in Fort Worth, Texas, on August 4,
2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2010–19816 Filed 8–17–10; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
15:12 Aug 17, 2010
Jkt 220001
DEPARTMENT OF TRANSPORTATION
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
50865
Discussion
14 CFR Part 39
[Docket No. FAA–2010–0329 Directorate
Identifier 2010–CE–016–AD; Amendment
39–16400; AD 2010–17–08]
RIN 2120–AA64
Airworthiness Directives; Various
Aircraft Equipped With Rotax Aircraft
Engines 912 A Series Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
Due to high fuel pressure, caused by
exceeding pressure in front of the mechanical
fuel pump (e.g. due to an electrical fuel
pump), in limited cases a deviation in the
fuel supply could occur. This can result in
exceeding of the fuel pressure and might
cause engine malfunction and/or massive
fuel leakage.
We are issuing this AD to prevent the
pump from causing excessive fuel
pressure, which could result in engine
malfunction or a massive fuel leak.
These conditions could cause loss of
control of the airplane or a fire. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
DATES: This AD becomes effective
September 22, 2010.
On September 22, 2010, 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; e-mail:
sarjapur.nagarajan@faa.gov.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
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 June 8, 2010 (75 FR 32315).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Due to high fuel pressure, caused by
exceeding pressure in front of the mechanical
fuel pump (e.g. due to an electrical fuel
pump), in limited cases a deviation in the
fuel supply could occur. This can result in
exceeding of the fuel pressure and might
cause engine malfunction and/or massive
fuel leakage.
Non-compliance with these instructions
could result in engine damages, personal
injuries or death.
The MCAI requires replacing the
affected fuel pumps with a different part
number fuel pump.
The MCAI applies to all versions of
Bombardier-Rotax GmbH 912 A, 912 F,
and 912 S series engines. Versions of the
912 F series and 912 S series engines are
type certificated in the United States.
However, the Model 912 A series engine
installed in various aircraft does not
have an engine type certificate; instead,
the engine is part of the aircraft type
design.
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.
E:\FR\FM\18AUR1.SGM
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Agencies
[Federal Register Volume 75, Number 159 (Wednesday, August 18, 2010)]
[Rules and Regulations]
[Pages 50863-50865]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-19816]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0806; Directorate Identifier 2010-SW-071-AD;
Amendment 39-16397; AD 2010-15-51]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A119 and AW119 MKII
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 2010-15-51, which was sent
previously to all known U.S. owners and operators of Agusta S.p.A.
(Agusta) Model A119 and AW119 MKII helicopters by individual letters.
This AD requires, within 5 hours time-in-service (TIS), and thereafter
at intervals not to exceed 50 hours TIS, removing the cover of each
pilot and co-pilot control box assembly (control box) and inspecting
each rotary variable differential transformer (RVDT) control gear
locking pin (locking pin) for proper position. If a locking pin is
recessed, extended, or missing, this AD requires replacing the control
box before further flight. This amendment is prompted by a report that
an RVDT locking pin that was installed on a Model AW119 MKII helicopter
moved from its proper position, resulting in loss of connectivity of
the pilot and co-pilot throttle controls. The actions specified by this
AD are intended to prevent the RVDT locking pin from moving from its
proper position, which could lead to loss of manual engine throttle
control, and subsequent loss of control of the helicopter.
DATES: Effective September 2, 2010, to all persons except those persons
to whom it was made immediately effective by Emergency AD 2010-15-51,
issued on July 16, 2010, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 2, 2010.
Comments for inclusion in the Rules Docket must be received on or
before October 18, 2010.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from
Agusta, Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA),
Italy, telephone 39 0331-229111, fax 39 0331-229605/222595, or at
https://customersupport.agusta.com/technical_advice.php.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information 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 Docket Operations office (telephone (800) 647-5527) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group,
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-4389,
fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: On July 16, 2010, we issued Emergency AD
2010-15-51 for the specified model helicopters, which requires, within
5 hours TIS, and thereafter at intervals not to exceed 50 hours TIS,
removing the cover of the pilot and co-pilot control boxes and
inspecting each RVDT locking pin for proper position. If a locking pin
is recessed, extended, or missing, the AD requires replacing the
control box before further flight. That action was prompted by a report
that an RVDT locking pin that was installed on a Model AW119 MKII
helicopter moved from its proper position, resulting in loss of
connectivity of the pilot and co-pilot throttle controls. Investigation
revealed that the pilot's locking pin had moved from its proper
position, which resulted in the loss of the co-pilot throttle control.
This condition, if not detected and corrected, could result in loss of
manual engine throttle control, 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 Community, notified us that
an unsafe condition may exist on Agusta Model A119 and AW119 MKII
helicopters. EASA advises of a nonconformity of certain control boxes,
unseating of a locking pin, and loss of the pilot and co-pilot engine
throttle synchronicity. EASA states this condition, if not detected and
corrected, could lead to the loss of manual engine throttle control and
consequent loss of control of the helicopter.
Agusta has issued Alert Bollettino Tecnico No. 119-39, dated July
2, 2010 (ABT). The ABT describes procedures for inspecting the pilot
and co-pilot control box for correct positioning of the locking pin.
The ABT states that the investigation is still in progress to find a
solution to the malfunction. The instructions in the ABT are prescribed
as precautionary pending future corrective action. EASA classified this
ABT as mandatory and issued Emergency AD 2010-0142-E, dated July 5,
2010, to ensure the continued airworthiness of these helicopters. This
AD differs from EASA Emergency AD No. 2010-0142-E in that we use the
term ``hours time-in-service'' rather than ``flight hours.'' Also, we
clarify the inspection requirements and do not use the calendar date of
August 31, 2010 as a required compliance time.
These helicopter models are manufactured in Italy and are type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, EASA has kept the FAA informed of the
situation described. We have examined the findings of EASA, reviewed
all available information, and determined that AD action is necessary
for products of these
[[Page 50864]]
type designs that are certificated for operation in the United States.
Since the unsafe condition described is likely to exist or develop
on other Agusta Model A119 and AW119 MKII helicopters of the same type
design, we issued Emergency AD 2010-15-51 to detect a missing or
improperly fitted RVDT locking pin, which could lead to loss of manual
engine throttle control, and subsequent loss of control of the
helicopter. The AD requires, within 5 hours TIS, and thereafter at
intervals not to exceed 50 hours TIS, removing the cover of the pilot
and co-pilot control boxes and inspecting the locking pins for proper
position. If 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, replacing the control box with an airworthy control box that
has been inspected in accordance with paragraph (a) of the AD is
required. Replacing the control box does not constitute terminating
action for the inspection requirements of the AD. The actions must be
accomplished in accordance with specified portions of the ABT described
previously.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability of the helicopter. The actions previously described are
required within short compliance times: 5 hours TIS and then at
intervals not to exceed 50 hours TIS for the initial and repetitive
inspections and before further flight for any required control box
replacement; therefore, this AD must be issued immediately.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on July 16, 2010 to all known U.S. owners and operators of
Agusta Model A119 and AW119 MKII helicopters. These conditions still
exist, and the AD is hereby published in the Federal Register as an
amendment to 14 CFR 39.13 to make it effective to all persons.
We estimate that this AD will affect 32 helicopters of U.S.
registry. Each inspection of both control boxes will take 1\1/2\ hours
and each control box replacement will take approximately 8 work hours
(2 per helicopter). The average labor rate is $85 per work hour. It
will cost approximately $12,852 for a pilot control box and $11,768 for
a co-pilot control box. Based on these figures, we estimate the total
cost impact of the AD on U.S. operators to be $835,440 ($26,108 per
helicopter, assuming 1 inspection of each control box and replacing
both control boxes on each helicopter).
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2010-0806; Directorate
Identifier 2010-SW-071-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the AD. We will consider all
comments received by the closing date and may amend the AD in light of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of our
docket web site, you can find and read the comments to any of our
dockets, including the name of the individual who sent the comment. You
may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78).
Regulatory Findings
We have 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.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD. See the AD docket to examine the economic evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2010-15-51 Agusta S.p.A.: Amendment 39-16397. Docket No. FAA-2010-
0806; Directorate Identifier 2010-SW-071-AD.
Applicability: 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.
Compliance: Required as indicated.
To detect a missing, or improperly fitted, engine rotary
variable differential transformer (RVDT) control gear locking pin
(locking pin), P/N MS16555-628, which could lead to loss of manual
engine throttle control, and subsequent loss of control of the
helicopter, accomplish the following:
(a) Within 5 hours time-in-service (TIS) unless accomplished
previously, and thereafter at intervals not to exceed 50 hours TIS,
remove the cover of the pilot and co-pilot control boxes and inspect
the locking
[[Page 50865]]
pins for proper position by following the Compliance Instructions,
Parts I and II, paragraphs 2. through 4.1 for the pilot control box
and paragraphs 5. through 7.1 for the co-pilot control box, in
Agusta Alert Bollettino Tecnico No. 119-39, dated July 2, 2010.
(b) If 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 control box with an airworthy control
box that has been inspected in accordance with paragraph (a) of this
AD. Replacing the control box does not constitute terminating action
for the inspection requirements of this AD.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Safety Management Group, FAA, ATTN: Rao
Edupuganti, Aviation Safety Engineer, Rotorcraft Directorate,
Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas
76137, telephone (817) 222-4389, fax (817) 222-5961, for information
about previously approved alternative methods of compliance.
(d) The Joint Aircraft System/Component (JASC) Code is 6700:
Rotors Flight Control.
(e) The inspections shall be done in accordance with the
specified portions of Agusta Alert Bollettino Tecnico No. 119-39,
dated July 2, 2010. The Director of the Federal Register approved
this incorporation by reference in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from Agusta, Via Giovanni
Agusta, 520 21017 Cascina Costa di Samarate (VA), Italy, telephone
39 0331-229111, fax 39 0331-229605/222595, or at https://customersupport.agusta.com/technical_advice.php. Copies may be
inspected at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 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/code_of_federal_regulations/ibr_locations.html.
(f) This amendment becomes effective on September 2, 2010, to
all persons except those persons to whom it was made immediately
effective by Emergency AD 2010-15-51, issued July 16, 2010, which
contained the requirements of this amendment.
Note: The subject of this AD is addressed in European Aviation
Safety Agency AD 2010-0142-E, dated July 5, 2010.
Issued in Fort Worth, Texas, on August 4, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-19816 Filed 8-17-10; 8:45 am]
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