```

[Federal Register Volume 80, Number 53 (Thursday, March 19, 2015)]
[Rules and Regulations]
[Pages 14297-14299]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05715]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0579; Directorate Identifier 2014-SW-020-AD; 
Amendment 39-18115; AD 2015-05-05]
RIN 2120-AA64

Airworthiness Directives; Agusta S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-04-14 for 
Agusta S.p.A. (Agusta) Model A109S, AW109SP, A119, and AW119 MKII 
helicopters. AD 2014-04-14 required removing certain rod end assemblies 
from service because of reports of fractures. This new AD retains the 
requirements of AD 2014-04-14 but expands the scope of applicable rod 
end assemblies. This AD was prompted by reports of additional fractured 
rod end assemblies. We are issuing this AD to prevent failure of a rod 
end assembly, which could result in damage to the main rotor assembly 
and loss of control of the helicopter.

DATES: This AD is effective April 23, 2015.

ADDRESSES: For service information identified in this AD, contact 
AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 
Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-
664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may view this referenced service information 
at the FAA, Office of the Regional Counsel,

[[Page 14298]]

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 European Aviation Safety 
Agency (EASA) AD, the economic evaluation, any comments received, and 
other information. The street address for the Docket Operations Office 
(phone: 800-647-5527) is U.S. Department of Transportation, Docket 
Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2014-04-14, Amendment 39-17773 (79 FR 11699, March 
3, 2014) for Agusta Model A109S, AW109SP, A119, and AW119 MKII 
helicopters with a main rotor lag damper assembly (lag damper), part 
number (P/N) 109-0112-39-103, 109-0112-39-105, 109-0112-05-105, or 109-
0112-05-107, installed with a rod end assembly, P/N M004-01H007-041 or 
P/N M004-01H007-045, with a serial number from 84 through 132 or from 
4964 through 5011, and add a new AD. The NPRM published in the Federal 
Register on August 18, 2014 (79 FR 48698). AD 2014-04-14 required 
removing the rod end assemblies from service. AD 2014-04-14 was 
prompted by AD No. 2012-0208, dated October 5, 2012, issued by EASA, 
which is the Technical Agent for the Member States of the European 
Union, to correct an unsafe condition for Agusta Model A109LUH, A109S, 
AW109SP, A119, and AW119 MKII helicopters. EASA advises of cases of in-
flight fractures of rod end assembly, P/N M004-01H007-045, installed on 
main rotor lag dampers on Model A109LUH and AW109SP helicopters. An 
investigation revealed that two batches of rod end assemblies, P/N 
M004-01H007-041 and M004-01H007-045, could have cracks, according to 
EASA. EASA states that this condition, if not corrected, could lead to 
main rotor damage, possibly resulting in loss of control of the 
helicopter. The actions of AD 2014-04-14 were intended to prevent such 
damage and loss of control of the helicopter.

Actions Since AD 2014-04-14 Was Issued

    Between the time we published the NPRM for AD 2014-04-14 (78 FR 
44042, July 23, 2013) and the Final Rule for AD 2014-04-14 (79 FR 
11699, March 3, 2014), EASA issued AD No. 2013-0290, dated December 9, 
2013. EASA advises in AD No. 2013-0290 that a new case of a fractured 
rod end assembly has been reported and that additional batches of rod 
end assembly, P/N M004-01H007-041 and P/N M004-01H007-045, as well as 
batches of P/N 109-0112-11-101 and P/N 109-0112-22-105 could also have 
cracks. EASA expanded the applicability of its AD to include the 
additional rod end assemblies.
    We consequently issued the NPRM (79 FR 48698, August 18, 2014) to 
amend 14 CFR part 39 to remove AD 2014-04-14 and add a new AD. The NPRM 
proposed to retain the requirements of AD 2014-04-14 but expand the 
scope of applicable rod end assemblies. The NPRM also proposed to add a 
provision requiring compliance with the AD if the rod end assembly is 
removed during maintenance before 25 hours time-in-service (TIS).

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (79 FR 48698, August 
18, 2014).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Italy and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Italy, EASA, its technical representative, 
has notified us of the unsafe condition described in the EASA AD. We 
are issuing this AD because we evaluated all information provided by 
EASA and determined the unsafe condition exists and is likely to exist 
or develop on other helicopters of these same type designs and that air 
safety and the public interest require adopting the AD requirements as 
proposed, except we have correctly stated the design holder's name as 
Agusta S.p.A. instead of AgustaWestland S.p.A. as specified by the 
current FAA type certificate. This change is consistent with the intent 
of the proposals in the NPRM (79 FR 48698, August 18, 2014) and will 
not increase the economic burden on any operator nor increase the scope 
of the AD.

Differences Between This AD and the EASA AD

    The EASA AD calls for replacing certain rod end assemblies with 
airworthy rod end assemblies within 25 hours TIS, 2 months, or the next 
time maintenance of the applicable helicopters involves removing the 
rod end assembly. This AD does not have a calendar time requirement. 
The EASA AD applies to Agusta Model A109LUH helicopters. This AD does 
not apply to Model A109LUH helicopters because that model does not have 
a U.S. type certificate.

Related Service Information

    We reviewed AgustaWestland Bollettino Tecnico (BT) No. 109S-49 for 
Model A109S helicopters, BT No. 109SP-052 for Model AW109SP 
helicopters, and BT No. 119-50 for Model A119 and AW119 MKII 
helicopters. All of the BTs are revision A, and dated December 3, 2013. 
The BTs specify a one-time inspection of each rod end assembly to 
determine its serial number. The BTs then require removal from service 
of certain serial-numbered rod end assemblies because fractures had 
been reported on rod ends in these batches. According to the BTs, no 
one was injured in the helicopters, and no helicopters were damaged 
because of these fractures.

Costs of Compliance

    We estimate that this AD affects 91 helicopters of U.S. Registry 
and that labor costs average $85 a work-hour. Based on these estimates, 
we expect the following costs:
     Replacing a rod end assembly requires 1.5 work-hours for a 
labor cost of $128. Parts cost $3,918 for a total cost of $4,046 per 
helicopter, $368,186 for the U.S. fleet.
    According to the manufacturer's service information, costs of this 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage by 
manufacturers. Accordingly, we have included all costs in our cost 
estimate.

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.

[[Page 14299]]

    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    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 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, 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.

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) 
2014-04-14, Amendment 39-17773 (79 FR 11699, March 3, 2014), and adding 
the following new AD:

2015-05-05 Agusta S.p.A.: Amendment 39-18115; Docket No. FAA-2014-
0579; Directorate Identifier 2014-SW-020-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters, 
with a main rotor lag damper assembly (lag damper), part number (P/
N) 109-0112-39-103 or 109-0112-39-105, installed on rod end 
assembly, P/N M004-01H007-041 with a serial number (S/N) 1 through 
202; or rod end assembly, P/N M004-01H007-045 with a S/N 1RW through 
202RW or 4964 through 5011.
    (2) Agusta Model A119 and AW119 MKII helicopters, with a lag 
damper, P/N 109-0112-05-105 or 109-0112-05-107, installed on rod end 
assembly, P/N 109-0112-11-101 with a S/N 1 through 78; or rod end 
assembly, P/N 109-0112-11-105 with a S/N 1RW through 78RW; or rod 
end assembly, P/N M004-01H007-045 with a S/N 1RW through 202RW or 
4964 through 5011.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a rod end 
assembly, which could result in fracture of the rod end assembly, 
damage to the main rotor, and subsequent loss of control of the 
helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-04-14, amendment 39-17773 (79 FR 
11699, March 3, 2014).

(d) Effective Date

    This AD becomes effective April 23, 2015.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Within 25 hours time-in-service or the next time maintenance 
of the helicopter involves removing the rod end assembly, whichever 
occurs first, remove the rod end assembly from service.
    (2) Do not install a rod end assembly, P/N M004-01H007-041 with 
a S/N 1 through 202; P/N M004-01H007-045 with a S/N 1RW through 
202RW or 4964 through 5011; P/N 109-0112-11-101 with a S/N 1 through 
78; or P/N 109-0112-11-105 with a S/N 1RW through 78RW, on any 
helicopter.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5110; email 
[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.

(h) Additional Information

    (1) AgustaWestland S.p.A. Bollettino Tecnico (BT) No. 109S-49, 
BT No. 109SP-052, and BT No. 119-50, all Revision A, and all dated 
December 3, 2013, which are not incorporated by reference, contain 
additional information about the subject of this AD. For service 
information identified in this AD, contact AgustaWestland, Product 
Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) 
Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-
0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review a copy of the service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.
    (2) The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) AD No. 2013-0290, dated December 9, 2013. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2014-0579.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

    Issued in Fort Worth, Texas, on March 4, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-05715 Filed 3-18-15; 8:45 am]
 BILLING CODE 4910-13-P
```