Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters, 7061-7063 [05-2591]
Download as PDF
<![CDATA[
Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–13495 (69 FR
9201, February 27, 2004), and by adding
a new airworthiness directive (AD), to
read as follows:
Eurocopter France: Docket No. FAA–2005–
20293; Directorate Identifier 2004–SW–
34–AD. Supersedes AD 2004–01–51,
Amendment 39–13495, Docket No.
2003–SW–56–AD.
Applicability: Model AS355E, F, F1, F2,
and N helicopters with a pre-MOD 077212
combiner gearbox that has 10 or less hours
time-in-service installed, certificated in any
category.
Compliance: Before further flight, unless
accomplished previously.
To prevent an engine overspeed, an engine
shutdown, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Before further flight, replace each preMOD 077212 combiner gearbox with a
combiner gearbox modified by replacing the
freewheel rollers in accordance with MOD
077212.
Note 1: Eurocopter France Alert Telex No.
63.00.21 R2, dated February 4, 2004, pertains
to the subject AD.
(b) Performing paragraph (a) of this AD is
terminating action for the 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 Safety Management Group,
FAA, for information about previously
approved alternative methods of compliance.
(d) Special flight permits will not be
issued.
Note 2: The subject of this AD is addressed
in Direction Generale de L’Aviation Civile,
France, AD No. F–2004–021, dated March 3,
2004.
Issued in Fort Worth, Texas, on January 24,
2005.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 05–2590 Filed 2–9–05; 8:45 am]
16:17 Feb 09, 2005
Jkt 205001
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send or deliver your
comments to the address listed under
the caption ADDRESSES. Include the
docket number ‘‘FAA–2005–20292,
Directorate Identifier 2004–SW–26–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. 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 or signed 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) or you may visit
https://dms.dot.gov.
Federal Aviation Administration
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate jul<14>2003
[Docket No. FAA–2005–20292; Directorate
Identifier 2004–SW–26–AD]
DEPARTMENT OF TRANSPORTATION
1. The authority citation for part 39
continues to read as follows:
BILLING CODE 4910–13–P
14 CFR Part 39
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
7061
Airworthiness Directives; Agusta
S.p.A. Model A109E Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for Agusta S.p.A. (Agusta) Model
A109E helicopters. This proposal would
require visually inspecting each main
transmission support fitting (fitting)
attachment bolt (bolt) for a fracture, a
crack, or looseness, and verifying the
torque on each fitting bolt. This
proposal is prompted by two incidents
of fatigue failure of the bolts that secure
the transmission rear support fittings to
the helicopter. The actions specified by
this proposed AD are intended to detect
a fracture, a crack, or looseness of a
fitting bolt, and prevent fatigue failure
of a fitting bolt and subsequent loss of
control of the helicopter.
DATES: Comments must be received on
or before April 11, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590;
• Fax: 202–493–2251; or
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., 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 proposed AD from
Agusta, 21017 Cascina Costa di
Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111,
fax 39 (0331) 229605–222595.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5227) is located at the plaza level of the
Department of Transportation NASSIF
Building in Room PL–401 at 400
Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
The Ente Nazionale per l’Aviazione
Civile (ENAC), the airworthiness
authority for Italy, notified the FAA that
an unsafe condition may exist on Agusta
Model A109E helicopters. ENAC
advises of the need to check the bolts
that secure the fittings to the structure
by following the manufacturer’s
Bollettino Tecnico No. 109EP–43, dated
March 3, 2004.
E:\FR\FM\10FEP1.SGM
10FEP1
7062
Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
Agusta has issued Bollettino Tecnico
No. 109EP–43, dated March 25, 2004,
which specifies a periodic visual
inspection to verify the integrity of the
slippage marks, and successively
checking the torque of the bolts to
exclude the possible presence of
looseness and/or a fracture or a crack.
ENAC classified this bollettino tecnico
as mandatory and issued AD No. 2004–
099, dated March 29, 2004, to ensure the
continued airworthiness of these
helicopters in Italy.
This helicopter model is
manufactured in Italy and is 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, ENAC has kept us
informed of the situation described
above. We have examined the findings
of ENAC, reviewed all available
information, and determined that AD
action is necessary for products of this
type design that are certificated for
operation in the United States.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of the same type
design registered in the United States.
Therefore, the proposed AD would
require inspecting the fitting bolts, part
number (P/N) NAS625–14, for a
fracture, a crack, or looseness within 5
hours time-in-service (TIS), and then at
intervals not to exceed 10 hours TIS
until performing a torque inspection of
each fitting bolt. The torque inspection
would have to be accomplished before
further flight if looseness is found, or
within 25 hours TIS if looseness is not
found. If a fracture or a crack is found
on any bolt in any fitting, replacing all
4 of the bolts in a fitting with airworthy
fitting bolts would be required before
further flight. If any torque inspection
reveals that the torque of any bolt in a
fitting is not between 11.3—15.8 Nm
(100—140 inch-pounds), all 4 of the
bolts in the fitting would have to be
replaced with airworthy fitting bolts
before further flight. The actions would
be required to be accomplished in
accordance with the bolletino tecnico
described previously.
We estimate that this proposed AD
would affect 58 helicopters of U.S.
registry. Three inspections (one initial,
one repetitive, and the torque
inspection) would take approximately 4
work hours to accomplish at an average
labor rate of $65 per work hour. (The
manufacturer states that it shall
recognize a warranty credit of up to
$200 per helicopter for the labor).
Required parts would cost
approximately $1,600 per helicopter
($100 per fitting bolt for 16 fitting bolts).
VerDate jul<14>2003
16:17 Feb 09, 2005
Jkt 205001
Based on these figures, the total
estimated cost impact of the proposed
AD on U.S. operators is $115,420,
assuming that no warranty credit is
available and that all affected fitting
bolts are replaced.
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
Regulatory Findings
1. The authority citation for part 39
continues to read as follows:
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would not have a substantial direct
effect on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
PART 39—AIRWORTHINESS
DIRECTIVES
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:
Agusta S.p.A.: Docket No. FAA–200X–
XXXXX; Directorate Identifier 2004–SW–
26–AD.
Applicability: Model A109E helicopters,
certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To detect a fracture, a crack, or looseness
of a main transmission support fitting
(fitting) attachment bolt (bolt), and prevent
fatigue failure of a fitting bolt and subsequent
loss of control of the helicopter, accomplish
the following:
(a) Within 5 hours time-in-service (TIS),
and then at intervals not to exceed 10 hours
TIS until a torque inspection of each fitting
bolt is accomplished in accordance with
paragraph (b) of this AD, inspect each fitting
bolt, part number NAS625–14, for a fracture,
a crack, or looseness using a light and a
mirror in accordance with Part I, steps 1.
through 4., of Agusta Bollettino Tecnico No.
109EP–43, dated March 25, 2004 (BT).
(1) On each of the 4 fittings, if a fracture
or a crack is found in any bolt, replace all
4 bolts in the fitting with airworthy fitting
bolts before further flight.
(2) If looseness is found in any bolt in any
fitting, inspect each of the 4 bolts on each of
the 4 fittings (16 bolts total) to determine if
the torque is between 11.3–15.8 Nm (100–140
inch-pounds). If the indicated torque is not
within the acceptable range on any bolt in a
fitting, before further flight, remove all 4
bolts in the fitting and replace them with
airworthy fitting bolts in accordance with
Part II, steps 5.1 through 9. of the BT.
(b) Within 25 hours TIS, inspect each bolt
in each fitting to determine if the torque is
between 11.3–15.8 Nm (100–140 inchpounds). If the indicated torque is not within
the acceptable range on any bolt, before
further flight, remove all 4 bolts in the fitting
and replace them with airworthy fitting bolts
in accordance with Part II, steps 5.1 through
9., of the BT.
(c) Accomplishing the inspections
specified in paragraphs (a) and (b) constitute
terminating actions for the requirements of
this AD.
(d) 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 Safety Management Group,
Rotorcraft Directorate, FAA, for information
about previously approved alternative
methods of compliance.
(e) Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
E:\FR\FM\10FEP1.SGM
10FEP1
Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
to operate the helicopter to a location where
the requirements of this AD can be
accomplished, provided that no fracture or
crack or looseness was found during the
inspections required by this AD.
Note: The subject of this AD is addressed
in Ente Nazionale per l’Aviazione Civile
(Italy) AD No. 2004–099, dated March 29,
2004.
14 CFR Part 39
Submit comments in
triplicate to the Federal Aviation
Administration (FAA), Office of the
Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2004–SW–
16–AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may
also send comments electronically to
the Rules Docket at the following
address: 9-asw-adcomments@faa.gov.
Comments may be inspected at the
Office of the Regional Counsel between
9 a.m. and 3 p.m., Monday through
Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Fred
Guerin, Aviation Safety Engineers, FAA,
Los Angeles Aircraft Certification
Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712, telephone (562) 627–5232, fax
(562) 627–5210.
SUPPLEMENTARY INFORMATION:
[Docket No. 2004–SW–16–AD]
Comments Invited
RIN 2120–AA64
Interested persons are invited to
participate in the making of the
proposed rule by submitting such
written data, views, or arguments as
they may desire. Communications
should identify the Rules Docket
number and be submitted in triplicate to
the address specified above. All
communications received on or before
the closing date for comments will be
considered before taking action on the
proposed rule. The proposals contained
in this document may be changed in
light of the comments received.
Comments are specifically invited on
the overall regulatory, economic,
environmental, and energy aspects of
the proposed rule. All comments
submitted will be available, both before
and after the closing date for comments,
in the Rules Docket for examination by
interested persons. A report
summarizing each FAA-public contact
concerned with the substance of this
proposal will be filed in the Rules
Docket.
Commenters wishing the FAA to
acknowledge receipt of their mailed
comments submitted in response to this
proposal must submit a self-addressed,
stamped postcard on which the
following statement is made:
‘‘Comments to Docket No. 2004–SW–
16–AD.’’ The postcard will be date
stamped and returned to the
commenter.
Issued in Fort Worth, Texas, on February
1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–2591 Filed 2–9–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Airworthiness Directives; MD
Helicopters, Inc. Model 600N
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
superseding an existing airworthiness
directive (AD) for the MD Helicopters,
Inc. (MDHI) Model 600N helicopters.
That AD currently requires certain
inspections of both upper tailboom
attachments, nutplates, and angles for a
crack or thread damage, and repairing or
replacing any cracked or damaged part.
Also, that AD requires replacing certain
tailboom attachment bolts, adding a
washer to each bolt, and modifying both
upper access covers. This action would
require installing six additional
inspection holes in the aft fuselage skin
panels and inspecting the upper and
lower tailboom attachment fittings, the
upper longerons, and the angles and
nutplates for cracks. Also, the AD would
provide a terminating action of
modifying the fuselage aft section to
strengthen the tailboom attachments
and longerons. This proposal is
prompted by an analysis that shows that
certain tailboom attachments and
longerons may develop cracks. The
actions specified by the proposed AD
are intended to prevent failure of a
tailboom attachment, loss of the
tailboom, and subsequent loss of control
of the helicopter.
DATES: Comments must be received on
or before April 11, 2005.
VerDate jul<14>2003
16:17 Feb 09, 2005
Jkt 205001
ADDRESSES:
Discussion
On November 28, 2001, the FAA
issued Emergency AD 2001–24–51 for
MDHI Model 600N helicopters and
issued the final rule; request for
comments on April 2, 2002
(Amendment 39–12706 (67 FR 17934,
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
7063
April 12, 2002)). That AD requires
implementing the procedures described
in MD Helicopters, Inc. Service Bulletin
SB600N–03, dated November 2, 2001
(SB600N–03), for inspecting both upper
tailboom attachments, nutplates, and
angles for a crack or thread damage and
repairing or replacing damaged parts. In
addition, if one bolt is broken, the AD
requires replacing all four bolts. Also,
adding a washer to each bolt and
modifying both upper access covers as
well as a 25-hour time-in-service (TIS)
repetitive borescope inspection of the
tailboom attachments, nutplates, and
angles is required. That action was
prompted by the discovery of cracked
bolts and attachments on several
helicopters. The requirements of that
AD are intended to prevent failure of a
tailboom attachment, loss of the
tailboom, and subsequent loss of control
of the helicopter.
Since issuing that AD, the FAA has
reviewed an analysis by the
manufacturer and has determined that
the tailboom fittings, part number (P/N)
500N3422–BSC (BSC is interchangeable
with basic) and –3, and the upper
longerons, P/N 500N3120–3 and –4, will
develop cracks due to the same design
error as the current AD. Also, the FAA
has reviewed MDHI Service Bulletin
SB600N–039, dated December 9, 2003,
which provides information pertaining
to adding six inspection holes in the
fuselage and certain inspections of the
tailboom attachment fittings and upper
longerons for cracks. Also, MDHI has
issued Technical Bulletin TB 600N–007,
dated January 12, 2004, which provides
information pertaining to modifying the
fuselage aft section to strengthen
tailboom attachment fittings and
longerons.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of the same type
design. Therefore, the proposed AD
would supersede AD 2001–24–51 to
require the following:
• Before further flight, drill an
inspection hole at fuselage station L167
and R167 (L indicates Left and R
indicates Right) on each side of the
fuselage.
• Within 25 hours time-in-service
(TIS):
• Drill two additional inspection
holes on each side of the fuselage at
L166, R166, L153, and R153.
• Visually inspect the lower
attachment fittings and the upper
longerons through inspection holes at
L166, R166, L153 and R153,
respectively.
• Thereafter, at specified intervals,
remove the plug buttons from the
inspection holes at L167, R167, L166,
E:\FR\FM\10FEP1.SGM
10FEP1
]]>Agencies
[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7061-7063]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2591]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20292; Directorate Identifier 2004-SW-26-AD]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This proposal
would require visually inspecting each main transmission support
fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or
looseness, and verifying the torque on each fitting bolt. This proposal
is prompted by two incidents of fatigue failure of the bolts that
secure the transmission rear support fittings to the helicopter. The
actions specified by this proposed AD are intended to detect a
fracture, a crack, or looseness of a fitting bolt, and prevent fatigue
failure of a fitting bolt and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before April 11, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically;
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590;
Fax: 202-493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., 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 proposed AD
from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send or deliver your comments to the
address listed under the caption ADDRESSES. Include the docket number
``FAA-2005-20292, Directorate Identifier 2004-SW-26-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed rulemaking. 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 or
signed 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) or you may visit https://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
The Ente Nazionale per l'Aviazione Civile (ENAC), the airworthiness
authority for Italy, notified the FAA that an unsafe condition may
exist on Agusta Model A109E helicopters. ENAC advises of the need to
check the bolts that secure the fittings to the structure by following
the manufacturer's Bollettino Tecnico No. 109EP-43, dated March 3,
2004.
[[Page 7062]]
Agusta has issued Bollettino Tecnico No. 109EP-43, dated March 25,
2004, which specifies a periodic visual inspection to verify the
integrity of the slippage marks, and successively checking the torque
of the bolts to exclude the possible presence of looseness and/or a
fracture or a crack. ENAC classified this bollettino tecnico as
mandatory and issued AD No. 2004-099, dated March 29, 2004, to ensure
the continued airworthiness of these helicopters in Italy.
This helicopter model is manufactured in Italy and is 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, ENAC has kept us informed of the
situation described above. We have examined the findings of ENAC,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type design registered in the
United States. Therefore, the proposed AD would require inspecting the
fitting bolts, part number (P/N) NAS625-14, for a fracture, a crack, or
looseness within 5 hours time-in-service (TIS), and then at intervals
not to exceed 10 hours TIS until performing a torque inspection of each
fitting bolt. The torque inspection would have to be accomplished
before further flight if looseness is found, or within 25 hours TIS if
looseness is not found. If a fracture or a crack is found on any bolt
in any fitting, replacing all 4 of the bolts in a fitting with
airworthy fitting bolts would be required before further flight. If any
torque inspection reveals that the torque of any bolt in a fitting is
not between 11.3--15.8 Nm (100--140 inch-pounds), all 4 of the bolts in
the fitting would have to be replaced with airworthy fitting bolts
before further flight. The actions would be required to be accomplished
in accordance with the bolletino tecnico described previously.
We estimate that this proposed AD would affect 58 helicopters of
U.S. registry. Three inspections (one initial, one repetitive, and the
torque inspection) would take approximately 4 work hours to accomplish
at an average labor rate of $65 per work hour. (The manufacturer states
that it shall recognize a warranty credit of up to $200 per helicopter
for the labor). Required parts would cost approximately $1,600 per
helicopter ($100 per fitting bolt for 16 fitting bolts). Based on these
figures, the total estimated cost impact of the proposed AD on U.S.
operators is $115,420, assuming that no warranty credit is available
and that all affected fitting bolts are replaced.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Agusta S.p.A.: Docket No. FAA-200X-XXXXX; Directorate Identifier
2004-SW-26-AD.
Applicability: Model A109E helicopters, certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To detect a fracture, a crack, or looseness of a main
transmission support fitting (fitting) attachment bolt (bolt), and
prevent fatigue failure of a fitting bolt and subsequent loss of
control of the helicopter, accomplish the following:
(a) Within 5 hours time-in-service (TIS), and then at intervals
not to exceed 10 hours TIS until a torque inspection of each fitting
bolt is accomplished in accordance with paragraph (b) of this AD,
inspect each fitting bolt, part number NAS625-14, for a fracture, a
crack, or looseness using a light and a mirror in accordance with
Part I, steps 1. through 4., of Agusta Bollettino Tecnico No. 109EP-
43, dated March 25, 2004 (BT).
(1) On each of the 4 fittings, if a fracture or a crack is found
in any bolt, replace all 4 bolts in the fitting with airworthy
fitting bolts before further flight.
(2) If looseness is found in any bolt in any fitting, inspect
each of the 4 bolts on each of the 4 fittings (16 bolts total) to
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range
on any bolt in a fitting, before further flight, remove all 4 bolts
in the fitting and replace them with airworthy fitting bolts in
accordance with Part II, steps 5.1 through 9. of the BT.
(b) Within 25 hours TIS, inspect each bolt in each fitting to
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range
on any bolt, before further flight, remove all 4 bolts in the
fitting and replace them with airworthy fitting bolts in accordance
with Part II, steps 5.1 through 9., of the BT.
(c) Accomplishing the inspections specified in paragraphs (a)
and (b) constitute terminating actions for the requirements of this
AD.
(d) 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 Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
(e) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199
[[Page 7063]]
to operate the helicopter to a location where the requirements of
this AD can be accomplished, provided that no fracture or crack or
looseness was found during the inspections required by this AD.
Note: The subject of this AD is addressed in Ente Nazionale per
l'Aviazione Civile (Italy) AD No. 2004-099, dated March 29, 2004.
Issued in Fort Worth, Texas, on February 1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2591 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P
