Airworthiness Directives; Agusta S.p.A. Model A109C, A109E, and A109K2 Helicopters, 26316-26318 [E8-10054]
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Federal Register / Vol. 73, No. 91 / Friday, May 9, 2008 / Rules and Regulations
diverts milk during the month pursuant
to paragraph (d) of this section. The
total quantity of milk so diverted during
the month shall not exceed 25 percent
during the months of July through
November, January, and February, and
35 percent during the months of
December and March through June of
the producer milk physically received at
such plant (or such unit of plants in the
case of plants that pool as a unit
pursuant to § 1007.7(e)) during the
month, excluding the quantity of
producer milk received from a handler
described in § 1000.9(c), excluding the
total pounds of bulk milk received
directly from producers meeting for
conditions as described in
§ 1007.82(c)(2)(ii) and (iii), and for
which a transportation credit is
requested;
*
*
*
*
*
Dated: May 6, 2008.
Lloyd C. Day,
Administrator, Agricultural Marketing
Service.
[FR Doc. 08–1239 Filed 5–6–08; 2:32 pm]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0524; Directorate
Identifier 2007–SW–77–AD; Amendment 39–
15519; AD 2007–26–52]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A109C, A109E, and
A109K2 Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
rwilkins on PROD1PC63 with RULES
AGENCY:
SUMMARY: This document supersedes
Airworthiness Directive (AD) 2001–24–
07 R1 and adopts AD 2007–26–52,
which was sent previously to all known
U.S. owners and operators of Agusta
S.p.A. (Agusta) Model A109C, A109E,
and A109K2 helicopters by individual
letters. This AD requires inspections for
swelling, deformation, bonding
separation, or a crack on each main
rotor blade (MRB) with a certain tip cap
installed, and if any of these conditions
are found that exceed the prescribed
limits, replacing the MRB before further
flight. This amendment is prompted by
a report of the in-flight loss of part of a
tip cap. The actions specified in this AD
are intended to prevent an increase in
VerDate Aug<31>2005
15:48 May 08, 2008
Jkt 214001
vibration of the MRB and subsequent
loss of control of the helicopter.
DATES: Effective May 27, 2008, to all
persons except those persons to whom
it was made immediately effective by
Emergency AD 2007–26–52, issued on
December 20, 2007, 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 May 27,
2008. The Director of the Federal
Register approved the incorporation by
reference of Agusta Alert Bollettino
Tecnico No. 109–106, No. 109K–22, and
No. 109EP–1, all Revision B and all
dated December 19, 2000, listed in the
AD as of January 7, 2002 (66 FR 60144,
December 3, 2001).
Comments for inclusion in the Rules
Docket must be received on or before
July 8, 2008.
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,
21017 Cascina Costa di Samarate (VA)
Italy, Via Giovanni Agusta 520,
telephone 39 (0331) 229111, fax 39
(0331) 229605–222595.
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:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
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On June
16, 2004, the FAA issued AD 2001–24–
07 R1, Amendment 39–13687 (69 FR
35511, June 25, 2004). That AD required
inspecting each MRB, part number (P/N)
709–0103–01, tip cap, for either bonding
separation or a crack, and provided a
terminating action for the requirements
of the AD by replacing each tip cap with
an airworthy tip cap, P/N 709–0103–29–
109.
Since issuing that AD, there has been
one report of in-flight loss of part of a
tip cap, P/N 709–0103–29–109,
resulting in an emergency landing due
to an increase in vibrations. There has
also been one report of cracking on the
tip cap leading edge. Therefore, on
December 20, 2007, we issued
Emergency AD 2007–26–52, which
superseded AD 2001–24–07 R1 (69 FR
35511, June 25, 2004), to remove the
terminating action of replacing a tip cap
with tip cap, P/N 709–0103–29–109,
and to remove the serial number
limitation of AD 2001–24–07 R1. The
Emergency AD requires inspecting and
replacing certain MRBs, if necessary.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for Italy, a Member State of the
European Community, notified us that
an unsafe condition may exist on Agusta
Model A109C, A109E, and A109K2
helicopters. The EASA advises that an
incident occurred in which a Model
A109E helicopter lost part of the tip of
the MRB due to fracture of the welded
bead (joint line of shells). The
manufacturer advises that the
investigation relating to this tip cap
failure is still ongoing.
Agusta has issued Alert Bollettino
Tecnico No. 109–106 for the Model
A109C, No. 109K–22 for the Model
A109K2, and No. 109EP–1 for the Model
A109E, all Revision B and all dated
December 19, 2000, which describe
inspecting the MRB tip cap for bonding
separation and a crack; a tap inspection
of the tip cap for bonding separation in
the blade bond; and a dye-penetrant
inspection of the tip cap leading edge
along the welded joint line of the upper
and lower tip cap skin shells for a crack.
Since then, Agusta has issued Bollettino
Tecnico No. 109–125 for the Model
A109C, No. 109EP–85 for the Model
A109E, and No. 109K–48 for the Model
A109K2, all dated December 13, 2007,
which describe procedures for
inspecting the tip cap, P/N 709–0103–
29–109, for cracks and for damage on
the tip cap leading edge at the welded
bead (joint line of shells). The EASA
classified these bollettino tecnicos as
mandatory and issued EASA Emergency
AD No. 2007–0306–E, dated December
14, 2007, to ensure the continued
SUPPLEMENTARY INFORMATION:
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09MYR1
rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 73, No. 91 / Friday, May 9, 2008 / Rules and Regulations
airworthiness of these helicopters in
Italy.
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, the EASA, the agent
for Italy, has kept the FAA informed of
the situation described above. The FAA
has examined the findings of the EASA,
reviewed all available information, and
determined that AD action is necessary
for products of these 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 A109C, A109E, and
A109K2 helicopters of the same type
designs, the FAA issued Emergency AD
2007–26–52 to prevent an increase in
vibration of the MRB and subsequent
loss of control of the helicopter. The AD
requires, for any MRB with a serial
number with a prefix of either ‘‘EM–’’ or
‘‘A5–’’, except a MRB with a tip cap,
P/N 709–0103–29–109, within 10 hours
TIS and thereafter at intervals not to
exceed 25 hours time-in-service (TIS):
• A tap inspection of the upper and
lower sides of each tip cap for bonding
separation and in the tip cap to blade
bond area;
• A visual inspection of the upper
and lower side of each blade tip cap for
swelling or deformation; and
• A dye-penetrant inspection of the
tip cap leading edge along the welded
joint line of the upper and lower tip cap
skin shells for a crack.
The AD also requires visually inspecting
each MRB with a tip cap, P/N 709–
0103–29–109, for a crack on the leading
edge at the welded bead (joint line of
shells) using a 10x or higher power
magnifying glass, and if there is damage
other than a crack, inspecting the area
using a dye-penetrant inspection
method, within the following
compliance times:
• For a tip cap, P/N 709–0103–29–
109, with 600 or more hours TIS,
inspect within the next 5 hours TIS or
30 days, whichever occurs first, and
thereafter at intervals not to exceed 50
hours TIS; or
• For a tip cap with less than 600
hours TIS, inspect before reaching 600
hours TIS, and thereafter, at intervals
not to exceed 50 hours TIS.
If dwelling, deformation, a crack, or
bonding separation that exceeds the
prescribed limits is found in a MRB
with an affected prefix, except a MRB
with a tip cap, P/N 709–0103–29–109,
the MRB must be replaced with an
airworthy MRB before further flight. If a
VerDate Aug<31>2005
15:48 May 08, 2008
Jkt 214001
crack is found in a MRB with tip cap,
P/N 709–0103–29–109, then before
further flight the MRB must be replaced
with an airworthy MRB. The actions
must be accomplished in accordance
with the bollettino tecnicos described
previously.
The short compliance time involved
is required because the previously
described critical unsafe condition can
adversely affect the structural integrity
and controllability of the helicopter.
Therefore, the applicable inspections of
each affected MRB and replacing any
unairworthy MRB are required before
further flight, and 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 December 20, 2007 to
all known U.S. owners and operators of
Model A109C, A109E, and A109K2
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.
The FAA estimates that this AD will
affect 101 helicopters of U.S. registry (44
without a tip cap, P/N 709–0103–29–
109, plus 57 with that tip cap), and will
take, for MRBs with any tip cap, except
tip cap, P/N 709–0103–29–109,
approximately 6 work hours per
helicopter to accomplish the initial and
24 25-hour TIS repetitive inspections
(assuming they include dye-penetrant
inspections), and for MRBs with tip cap,
P/N 709–0103–29–109, installed,
approximately 8 work hours per
helicopter to accomplish the initial and
12 50-hour TIS repetitive inspections,
assuming that these inspections require
using a dye-penetrant method also, at an
average labor rate of $80 per work hour.
Based on these figures, we estimate the
total cost impact of the AD on U.S.
operators to be $495,360.
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–2008–0524;
Directorate Identifier 2007–SW–77–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
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26317
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), or you may visit
https://docketsinfo.dot.gov.
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
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Federal Register / Vol. 73, No. 91 / Friday, May 9, 2008 / Rules and Regulations
§ 39.13
that is likely to exist or develop on
products identified in this rulemaking
action.
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
2007–26–52 Agusta S.p.A.: Amendment 39–
15519. Docket No. FAA–2008–0524;
Directorate Identifier 2007–SW–77–AD.
Supersedes AD 2001–24–07 R1,
Amendment 39–13687, Docket No.
2001–SW–15–AD.
Applicability: Model A109C, A109E, and
A109K2 helicopters, with a main rotor blade
(MRB), Part Number (P/N) 709–0103–01–all
dash numbers, certificated in any category.
Compliance: Required as indicated.
(a) For a MRB with a serial number that has
a prefix of either ‘‘EM–’’ or ‘‘A5–’’, except a
MRB with a tip cap, P/N 709–0103–29–109,
installed, within 10 hours time-in-service
(TIS), unless accomplished previously, and
thereafter at intervals not to exceed 25 hours
TIS:
(1) Tap inspect the upper and lower sides
of each tip cap for bonding separation
between the metal shells and the honeycomb
core using a steel tap hammer, P/N 109–
3101–58–1, or a coin (quarter) in the area
indicated as honeycomb core on Figure 1 of
Alert Bollettino Tecnico (BT) No. 109–106,
No. 109K–22, or No. 109EP–1, all Revision B,
and all dated December 19, 2000, as
applicable to your model helicopter. Also,
tap inspect for bonding separation in the tip
cap to blade bond area (no bonding voids are
permitted in this area).
(2) Visually inspect the upper and lower
sides of each blade tip cap for swelling or
deformation.
(3) Dye-penetrant inspect the tip cap
leading edge along the welded joint line of
the upper and lower tip cap skin shells for
a crack in accordance with the Compliance
Instructions, steps 3. through 3.2.6., of the
applicable BT.
(4) If any swelling, deformation, crack, or
bonding separation that exceeds the
prescribed limits in the applicable
maintenance manual is found, replace the
blade with an airworthy blade before further
flight.
(b) For a MRB with a tip cap, P/N 709–
0103–29–109, installed, perform the
following in accordance with Table 1:
TABLE 1
For each tip cap:
Comply:
With 600 or more hours TIS ....................................................
Within the next 5 hours TIS or 30 days, whichever occurs first, and thereafter at
intervals not to exceed 50 hours TIS.
Before reaching 600 hours TIS, and thereafter, at intervals not to exceed 50
hours TIS.
rwilkins on PROD1PC63 with RULES
With less than 600 hours TIS ..................................................
(1) Using a 10x or higher power magnifying
glass, visually inspect the tip cap leading
edge welded bead (joint line between the two
metallic shells) for a crack in accordance
with the Compliance Instructions, steps 1.
through 2. of BT No. 109–125, No. 109EP–85,
or No. 109K–48, all dated December 13, 2007,
as applicable to your model helicopter.
(2) If there is damage other than a crack,
inspect the tip cap leading edge along the
welded joint line of the shells for a crack
using a dye penetrant method in accordance
with the Compliance Instructions, steps 3.
through 3.7. of BT No. 109–125, No. 109EP–
85, or No. 109K–48, all dated December 13,
2007, as applicable to your model helicopter.
(3) If a crack is present, remove the blade
and replace it with an airworthy blade before
further flight.
(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: Sharon
Miles, Rotorcraft Directorate, Fort Worth,
Texas 76193–0111, telephone (817) 222–
5122, fax (817) 222–5961, for information
about previously approved alternative
methods of compliance.
(d) The inspections shall be done in
accordance with the specified portions of the
service information described in paragraphs
(d)(1) and (d)(2) of this AD.
(1) The Director of the Federal Register
approved the incorporation by reference of
Agusta Bollettino Tecnico No. 109–125, No.
109EP–85, and No. 109K–48, all dated
VerDate Aug<31>2005
15:48 May 08, 2008
Jkt 214001
December 13, 2007, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Agusta Alert Bollettino Tecnico
No. 109–106, No. 109K–22, and No. 109EP–
1, all Revision B and all dated December 19,
2000, on January 7, 2002 (66 FR 60144,
December 3, 2001).
(3) Copies may be obtained from Agusta,
21017 Cascina Costa di Samarate (VA) Italy,
Via Giovanni Agusta 520, telephone 39
(0331) 229111, fax 39 (0331) 229605–222595.
(4) 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.
Note: The subject of this AD is addressed
in European Aviation Safety Agency (EASA)
AD No. 2007–0306–E, dated December 14,
2007.
(e) This amendment becomes effective on
May 27, 2008, to all persons except those
persons to whom it was made immediately
effective by Emergency AD 2007–26–52,
issued December 20, 2007, which contained
the requirements of this amendment.
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Issued in Fort Worth, Texas, on May 1,
2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–10054 Filed 5–8–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0527; Directorate
Identifier 2008–CE–027–AD; Amendment
39–15520; AD 2008–10–13]
RIN 2120–AA64
Airworthiness Directives; EADS
SOCATA Model TBM 700 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
E:\FR\FM\09MYR1.SGM
09MYR1
Agencies
[Federal Register Volume 73, Number 91 (Friday, May 9, 2008)]
[Rules and Regulations]
[Pages 26316-26318]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-10054]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0524; Directorate Identifier 2007-SW-77-AD;
Amendment 39-15519; AD 2007-26-52]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Model A109C, A109E, and
A109K2 Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document supersedes Airworthiness Directive (AD) 2001-24-
07 R1 and adopts AD 2007-26-52, which was sent previously to all known
U.S. owners and operators of Agusta S.p.A. (Agusta) Model A109C, A109E,
and A109K2 helicopters by individual letters. This AD requires
inspections for swelling, deformation, bonding separation, or a crack
on each main rotor blade (MRB) with a certain tip cap installed, and if
any of these conditions are found that exceed the prescribed limits,
replacing the MRB before further flight. This amendment is prompted by
a report of the in-flight loss of part of a tip cap. The actions
specified in this AD are intended to prevent an increase in vibration
of the MRB and subsequent loss of control of the helicopter.
DATES: Effective May 27, 2008, to all persons except those persons to
whom it was made immediately effective by Emergency AD 2007-26-52,
issued on December 20, 2007, 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 May 27, 2008. The Director of the Federal Register approved the
incorporation by reference of Agusta Alert Bollettino Tecnico No. 109-
106, No. 109K-22, and No. 109EP-1, all Revision B and all dated
December 19, 2000, listed in the AD as of January 7, 2002 (66 FR 60144,
December 3, 2001).
Comments for inclusion in the Rules Docket must be received on or
before July 8, 2008.
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, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta
520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
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: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: On June 16, 2004, the FAA issued AD 2001-24-
07 R1, Amendment 39-13687 (69 FR 35511, June 25, 2004). That AD
required inspecting each MRB, part number (P/N) 709-0103-01, tip cap,
for either bonding separation or a crack, and provided a terminating
action for the requirements of the AD by replacing each tip cap with an
airworthy tip cap, P/N 709-0103-29-109.
Since issuing that AD, there has been one report of in-flight loss
of part of a tip cap, P/N 709-0103-29-109, resulting in an emergency
landing due to an increase in vibrations. There has also been one
report of cracking on the tip cap leading edge. Therefore, on December
20, 2007, we issued Emergency AD 2007-26-52, which superseded AD 2001-
24-07 R1 (69 FR 35511, June 25, 2004), to remove the terminating action
of replacing a tip cap with tip cap, P/N 709-0103-29-109, and to remove
the serial number limitation of AD 2001-24-07 R1. The Emergency AD
requires inspecting and replacing certain MRBs, if necessary.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for Italy, a Member State of the European Community, notified us
that an unsafe condition may exist on Agusta Model A109C, A109E, and
A109K2 helicopters. The EASA advises that an incident occurred in which
a Model A109E helicopter lost part of the tip of the MRB due to
fracture of the welded bead (joint line of shells). The manufacturer
advises that the investigation relating to this tip cap failure is
still ongoing.
Agusta has issued Alert Bollettino Tecnico No. 109-106 for the
Model A109C, No. 109K-22 for the Model A109K2, and No. 109EP-1 for the
Model A109E, all Revision B and all dated December 19, 2000, which
describe inspecting the MRB tip cap for bonding separation and a crack;
a tap inspection of the tip cap for bonding separation in the blade
bond; and a dye-penetrant inspection of the tip cap leading edge along
the welded joint line of the upper and lower tip cap skin shells for a
crack. Since then, Agusta has issued Bollettino Tecnico No. 109-125 for
the Model A109C, No. 109EP-85 for the Model A109E, and No. 109K-48 for
the Model A109K2, all dated December 13, 2007, which describe
procedures for inspecting the tip cap, P/N 709-0103-29-109, for cracks
and for damage on the tip cap leading edge at the welded bead (joint
line of shells). The EASA classified these bollettino tecnicos as
mandatory and issued EASA Emergency AD No. 2007-0306-E, dated December
14, 2007, to ensure the continued
[[Page 26317]]
airworthiness of these helicopters in Italy.
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, the EASA, the agent for Italy, has kept
the FAA informed of the situation described above. The FAA has examined
the findings of the EASA, reviewed all available information, and
determined that AD action is necessary for products of these 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 A109C, A109E, and A109K2 helicopters of the same
type designs, the FAA issued Emergency AD 2007-26-52 to prevent an
increase in vibration of the MRB and subsequent loss of control of the
helicopter. The AD requires, for any MRB with a serial number with a
prefix of either ``EM-'' or ``A5-'', except a MRB with a tip cap, P/N
709-0103-29-109, within 10 hours TIS and thereafter at intervals not to
exceed 25 hours time-in-service (TIS):
A tap inspection of the upper and lower sides of each tip
cap for bonding separation and in the tip cap to blade bond area;
A visual inspection of the upper and lower side of each
blade tip cap for swelling or deformation; and
A dye-penetrant inspection of the tip cap leading edge
along the welded joint line of the upper and lower tip cap skin shells
for a crack. The AD also requires visually inspecting each MRB with a
tip cap, P/N 709-0103-29-109, for a crack on the leading edge at the
welded bead (joint line of shells) using a 10x or higher power
magnifying glass, and if there is damage other than a crack, inspecting
the area using a dye-penetrant inspection method, within the following
compliance times:
For a tip cap, P/N 709-0103-29-109, with 600 or more hours
TIS, inspect within the next 5 hours TIS or 30 days, whichever occurs
first, and thereafter at intervals not to exceed 50 hours TIS; or
For a tip cap with less than 600 hours TIS, inspect before
reaching 600 hours TIS, and thereafter, at intervals not to exceed 50
hours TIS.
If dwelling, deformation, a crack, or bonding separation that
exceeds the prescribed limits is found in a MRB with an affected
prefix, except a MRB with a tip cap, P/N 709-0103-29-109, the MRB must
be replaced with an airworthy MRB before further flight. If a crack is
found in a MRB with tip cap, P/N 709-0103-29-109, then before further
flight the MRB must be replaced with an airworthy MRB. The actions must
be accomplished in accordance with the bollettino tecnicos described
previously.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
structural integrity and controllability of the helicopter. Therefore,
the applicable inspections of each affected MRB and replacing any
unairworthy MRB are required before further flight, and 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 December 20, 2007 to all known U.S. owners and operators of
Model A109C, A109E, and A109K2 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.
The FAA estimates that this AD will affect 101 helicopters of U.S.
registry (44 without a tip cap, P/N 709-0103-29-109, plus 57 with that
tip cap), and will take, for MRBs with any tip cap, except tip cap, P/N
709-0103-29-109, approximately 6 work hours per helicopter to
accomplish the initial and 24 25-hour TIS repetitive inspections
(assuming they include dye-penetrant inspections), and for MRBs with
tip cap, P/N 709-0103-29-109, installed, approximately 8 work hours per
helicopter to accomplish the initial and 12 50-hour TIS repetitive
inspections, assuming that these inspections require using a dye-
penetrant method also, at an average labor rate of $80 per work hour.
Based on these figures, we estimate the total cost impact of the AD on
U.S. operators to be $495,360.
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-2008-0524; Directorate
Identifier 2007-SW-77-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), or you may visit
https://docketsinfo.dot.gov.
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
[[Page 26318]]
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:
2007-26-52 Agusta S.p.A.: Amendment 39-15519. Docket No. FAA-2008-
0524; Directorate Identifier 2007-SW-77-AD. Supersedes AD 2001-24-07
R1, Amendment 39-13687, Docket No. 2001-SW-15-AD.
Applicability: Model A109C, A109E, and A109K2 helicopters, with
a main rotor blade (MRB), Part Number (P/N) 709-0103-01-all dash
numbers, certificated in any category.
Compliance: Required as indicated.
(a) For a MRB with a serial number that has a prefix of either
``EM-'' or ``A5-'', except a MRB with a tip cap, P/N 709-0103-29-
109, installed, within 10 hours time-in-service (TIS), unless
accomplished previously, and thereafter at intervals not to exceed
25 hours TIS:
(1) Tap inspect the upper and lower sides of each tip cap for
bonding separation between the metal shells and the honeycomb core
using a steel tap hammer, P/N 109-3101-58-1, or a coin (quarter) in
the area indicated as honeycomb core on Figure 1 of Alert Bollettino
Tecnico (BT) No. 109-106, No. 109K-22, or No. 109EP-1, all Revision
B, and all dated December 19, 2000, as applicable to your model
helicopter. Also, tap inspect for bonding separation in the tip cap
to blade bond area (no bonding voids are permitted in this area).
(2) Visually inspect the upper and lower sides of each blade tip
cap for swelling or deformation.
(3) Dye-penetrant inspect the tip cap leading edge along the
welded joint line of the upper and lower tip cap skin shells for a
crack in accordance with the Compliance Instructions, steps 3.
through 3.2.6., of the applicable BT.
(4) If any swelling, deformation, crack, or bonding separation
that exceeds the prescribed limits in the applicable maintenance
manual is found, replace the blade with an airworthy blade before
further flight.
(b) For a MRB with a tip cap, P/N 709-0103-29-109, installed,
perform the following in accordance with Table 1:
Table 1
------------------------------------------------------------------------
For each tip cap: Comply:
------------------------------------------------------------------------
With 600 or more hours TIS............. Within the next 5 hours TIS or
30 days, whichever occurs
first, and thereafter at
intervals not to exceed 50
hours TIS.
With less than 600 hours TIS........... Before reaching 600 hours TIS,
and thereafter, at intervals
not to exceed 50 hours TIS.
------------------------------------------------------------------------
(1) Using a 10x or higher power magnifying glass, visually
inspect the tip cap leading edge welded bead (joint line between the
two metallic shells) for a crack in accordance with the Compliance
Instructions, steps 1. through 2. of BT No. 109-125, No. 109EP-85,
or No. 109K-48, all dated December 13, 2007, as applicable to your
model helicopter.
(2) If there is damage other than a crack, inspect the tip cap
leading edge along the welded joint line of the shells for a crack
using a dye penetrant method in accordance with the Compliance
Instructions, steps 3. through 3.7. of BT No. 109-125, No. 109EP-85,
or No. 109K-48, all dated December 13, 2007, as applicable to your
model helicopter.
(3) If a crack is present, remove the blade and replace it with
an airworthy blade before further flight.
(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: Sharon
Miles, Rotorcraft Directorate, Fort Worth, Texas 76193-0111,
telephone (817) 222-5122, fax (817) 222-5961, for information about
previously approved alternative methods of compliance.
(d) The inspections shall be done in accordance with the
specified portions of the service information described in
paragraphs (d)(1) and (d)(2) of this AD.
(1) The Director of the Federal Register approved the
incorporation by reference of Agusta Bollettino Tecnico No. 109-125,
No. 109EP-85, and No. 109K-48, all dated December 13, 2007, in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Agusta Alert Bollettino Tecnico No.
109-106, No. 109K-22, and No. 109EP-1, all Revision B and all dated
December 19, 2000, on January 7, 2002 (66 FR 60144, December 3,
2001).
(3) Copies may be obtained from Agusta, 21017 Cascina Costa di
Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331)
229111, fax 39 (0331) 229605-222595.
(4) 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.
Note: The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2007-0306-E, dated December 14, 2007.
(e) This amendment becomes effective on May 27, 2008, to all
persons except those persons to whom it was made immediately
effective by Emergency AD 2007-26-52, issued December 20, 2007,
which contained the requirements of this amendment.
Issued in Fort Worth, Texas, on May 1, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-10054 Filed 5-8-08; 8:45 am]
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