[Federal Register Volume 78, Number 186 (Wednesday, September 25, 2013)]
[Rules and Regulations]
[Pages 58868-58872]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-23017]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0146; Directorate Identifier 2012-SW-060-AD;
Amendment 39-17559; AD 2013-16-21]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. (Type Certificate
Currently Held by Agusta Westland S.p.A) (Agusta) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding an airworthiness directive (AD) for Agusta
Model A109E helicopters that required reducing the tail rotor (T/R)
blade life limit, modifying a T/R hub and grip assembly, re-identifying
two T/R assemblies, clarifying the never-exceed speed (Vne) limitation,
and reducing the inspection interval. Since we issued that AD, the
manufacturer has redesigned a T/R grip bushing (bushing) that reduces
the loads, which caused the T/R cracking, on the T/R blades. This
action requires installing the new bushing and re-identifying the T/R
hub-and-grip and hub-and-blade assemblies and requires a recurring
inspection of each bushing. These actions are intended to prevent
fatigue failure of a T/R blade and subsequent loss of control of the
helicopter.
DATES: This AD is effective October 30, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of October 30,
2013.
ADDRESSES: For service information identified in this AD, contact
Agusta
[[Page 58869]]
Westland, Customer Support & Services, Via Per Tornavento 15, 21019
Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone 39-0331-
711133; fax 39-0331-711180; or at http://www.agustawestland.com/technical-bullettins. You may review the referenced service information
at the FAA, Office of the Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the foreign authority's AD,
any incorporated-by-reference service information, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (phone: 800-647-5527) is U.S.
Department of Transportation, Docket Operations Office, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On February 25, 2013, at 78 FR 12651, the Federal Register
published our notice of proposed rulemaking (NPRM), which proposed to
amend 14 CFR part 39 to supersede AD 2002-25-51, Amendment 39-13060 (68
FR 9504, February 28, 2003), which required for Agusta Model A109E
helicopters reducing the tail rotor (T/R) blade life limit, modifying a
T/R hub and grip assembly, re-identifying two T/R assemblies,
clarifying the never-exceed speed (Vne) limitation, and reducing the
inspection interval.
The NPRM was prompted by AD No. 2007-0010, dated January 31, 2007,
issued by the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union. EASA
issued EASA AD No. 2007-0010 to correct an unsafe condition for the
Agusta Model A109E. EASA advises that Agusta has designed a new bushing
that when installed on the T/R grip assembly reduces the loads acting
upon the T/R blades. EASA further advises that following installation
of the re-designed bushing, the inspection interval of the T/R blade
bushing may be extended from 150 flight hours to 200 flight hours.
Accordingly, the NPRM proposed to require:
Before each start of the helicopter engines, visually
checking both sides of each T/R blade for a crack. An owner/operator
(pilot) may perform this check and must enter compliance into the
aircraft records in accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR
91.417(a)(2)(v). A pilot may perform this check because it involves
only a visual check for a crack and can be performed equally well by a
pilot or a mechanic. This procedure is an exception to our standard
maintenance regulations.
For helicopters with T/R hub and blade assembly, part
number (P/N) 109-8131-02-151, before further flight, modifying each T/R
hub and blade assembly by installing a new bushing in each grip
assembly and two zero-hours time-in-service (TIS) T/R blades; and re-
identifying the hub and grip assembly and the T/R hub and blade
assembly with different P/Ns.
For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-157, within 25 hours TIS and thereafter at intervals not to
exceed 25 hours TIS, and before further flight any time there is an
increase in vibration levels, using a 5x or higher power magnifying
glass, visually inspecting each T/R blade for a crack.
On or before accumulating 200 hours TIS on the T/R hub and
grip assembly, and thereafter at intervals not to exceed 200 hours TIS,
inspecting the linings and measuring the internal diameter of the
bushings. If the internal diameter of the bushing exceeds 41.35
millimeters, replacing the bushing.
If there is a crack, before further flight, replacing the
T/R blade.
Revising the Airworthiness Limitations section of the
maintenance manual to reflect that a T/R blade, P/N 109-8132-01-111,
which has not been operated as part of T/R hub and blade assembly, P/N
109-8131-02-151, has a retirement life of 1,000 hours TIS.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 12651,
February 25, 2013).
FAA's Determination
These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, EASA, its technical representative,
has notified us of the unsafe condition described in the EASA AD. We
are issuing this AD because we evaluated all information provided by
EASA and determined the unsafe condition exists and is likely to exist
or develop on other helicopters of the same type design and that air
safety and the public interest require adopting the AD requirements as
proposed.
Related Service Information
We reviewed Alert Bollettino Tecnico No. 109EP-30, Revision C,
dated September 29, 2006, which describes procedures for checking/
inspecting for cracks on both the upper and lower surfaces of T/R
blades, P/N 109-8132-01-111; replacing each bushing, P/N 109-0132-55
and spacer P/N 109-0132-13, with bushing, P/N 109-8131-30-109, and
instituting a recurring inspection of each bushing; and cancelling the
VNE limitations when the newly-designed bushing is installed
on each T/R grip assembly, P/N 109-8131-29-101, a ``new'' pair of T/R
blades, P/N 109-8132-01-111, is installed, and the T/R hub-and-grip and
hub-and-blade assemblies are re-identified.
Costs of Compliance
We estimate that this AD will affect 75 helicopters of U.S.
Registry. Based on an average labor rate of $85 per hour, we estimate
that operators will incur the following costs in order to comply with
this AD:
Visually inspecting the T/R blades requires about 0.5 work
hours for a cost per helicopter of $43 and a total cost to U.S.
operators of $3,225 per inspection cycle.
Replacing a cracked T/R blade requires about 2 work hours,
and required parts cost about $25,320, for a total cost per helicopter
of $25,490.
Modifying the hub assembly with new T/R blades and
bushings requires about 16 work hours, and required parts would cost
about $58,690, for a total cost per helicopter of $60,050.
Inspecting the T/R bushings requires about 7 work hours,
for a cost per helicopter of $595 and a total cost to U.S. operators of
$44,625 per inspection cycle.
Revising the Airworthiness Limitations section of the
maintenance manual requires about .25 work hour, for a cost per
helicopter of $22 and a total cost to U.S. operators of $1,650.
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
[[Page 58870]]
the FAA Administrator. Subtitle VII: Aviation Programs, describes in
more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2002-25-51, Amendment 39-13060 (68 FR 9504, February 28, 2003), and
adding the following new AD:
2013-16-21 AGUSTA S.p.A. (Agusta): Amendment 39-17559; Docket No.
FAA-2013-0146; Directorate Identifier 2012-SW-060-AD.
(a) Applicability
This AD applies to Agusta Model 109E helicopters with tail rotor
(T/R) hub and blade assembly, part number (P/N) 109-8131-02-151 and
P/N 109-8131-02-157, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a fatigue crack in a T/R
blade. This condition could result in failure of the T/R blade and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2002-25-51, Docket No. 2002-SW-55-AD,
Amendment 39-13060 (68 FR 9504, February 28, 2003).
(d) Effective Date
This AD becomes effective October 30, 2013.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Before each start of the helicopter engines, visually check
both sides of each T/R blade for a crack in the inspection area
depicted in Figure 1 to paragraph (f)(1) of this AD. This action may
be performed by the owner/operator (pilot) holding at least a
private pilot certificate, and must be entered into the aircraft
records showing compliance with this AD in accordance with 14 CFR
43.9 (a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417, 121.380, or 135.439.
[[Page 58871]]
[GRAPHIC] [TIFF OMITTED] TR25SE13.000
(2) For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-151 (consisting of two T/R blades, P/N 109-8132-01-111, and
one T/R hub and grip assembly, P/N 109-8131-02-127), before further
flight, modify each T/R hub and blade assembly by installing a new
bushing, P/N 109-8131-30-109, in each grip assembly and two zero-
hour time-in-service (TIS) T/R blades, P/N 109-8132-01-111; re-
identifying the hub and grip assembly as P/N 109-8131-02-159; and
re-identifying the T/R hub and blade assembly as P/N 109-8131-02-157
in accordance with the Compliance Instructions, Part V, paragraphs
2. through 13., of Agusta Bollettino Tecnico No. 109EP-30, Revision
C, dated September 29, 2006 (BT). A T/R blade, P/N 109-8132-01-111,
which has been operated as part of T/R hub and blade assembly, P/N
109-8131-02-151, must be retired regardless of TIS and may not be
used as part of the T/R hub and blade assembly, P/N 109-8131-02-157.
Returning the removed T/R blades, grips, or bushings to Agusta is
not required.
(3) For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-157 (consisting of two T/R blades, P/N 109-8132-01-111, and
one T/R hub and grip assembly, P/N 109-8131-02-159), within 25 hours
TIS, and thereafter at intervals not to exceed 25 hours TIS, and
before further flight any time there is an increase in vibration
levels, using a 5x or higher power magnifying glass, visually
inspect each T/R blade for a crack in accordance with the Compliance
Instructions, Part III, paragraphs 1. through 5. of the BT.
Reporting to Agusta is not required.
(4) On or before accumulating 200 hours TIS on the T/R hub and
grip assembly, P/N 109-8131-02-159, and thereafter at intervals not
to exceed 200 hours TIS, inspect the linings and measure the
internal diameter of the bushings, P/N 109-8131-30-109, by referring
to Figure 2 of the BT. If the internal diameter of the bushing
exceeds 41.35 millimeters, replace the bushing.
(5) If there is a crack in a T/R blade, before further flight,
replace the cracked T/R blade.
(6) Revise the Airworthiness Limitations section of the
maintenance manual to reflect that a T/R blade, P/N 109-8132-01-111,
which has not been operated as part of T/R hub and blade assembly,
P/N 109-8131-02-151, has retirement life of 1,000 hours TIS.
(g) Special Flight Permits
Special flight permits will not be issued.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas, 76137; telephone (817) 222-
5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(i) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2007-0010, dated January 31, 2007. You may view
a copy of the EASA AD on the Internet at http://www.regulations.gov
in Docket No. FAA-2013-0146.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor
Blades.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Agusta Bollettino Tecnico No. 109EP-30, Revision C, dated
September 29, 2006, excluding Figure 1.
(ii) Reserved.
(3) For Agusta service information identified in this AD,
contact Agusta Westland, Customer Support & Services, Via Per
Tornavento 15, 21019 Somma Lombardo (VA) Italy, ATTN: Giovanni
Cecchelli; telephone 39-0331-711133; fax 39-0331-711180; or at
http://www.agustawestland.com/technical-bullettins.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may also view this service information that is
incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: http://
[[Page 58872]]
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 2, 2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-23017 Filed 9-24-13; 8:45 am]
BILLING CODE 4910-13-P