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2018-19-10 AIRBUS HELICOPTERS: Amendment 39-19410; Docket No. FAA-2018-0438; Product Identifier 2017-SW-062-AD.
(a) APPLICABILITY

    This AD  applies to  Airbus Helicopters Model AS355E, AS355F, AS355F1,
    AS355F2, and AS355N helicopters, certificated in any category.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as degradation of a main  gearbox
    (MGB) oil cooler fan assembly bearing. This condition could result  in
    loss  of  MGB  and  engine oil  cooling  function,  loss  of the  rear
    transmission, and subsequent loss of control of the helicopter.

(c) EFFECTIVE DATE

    This AD becomes effective October 30, 2018.

(d) 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.

(e) REQUIRED ACTIONS

(1) Within 165 hours time-in-service (TIS):

(i) Measure the tail rotor (T/R) drive vibration level  without  balancing
    the T/R drive, and record the amplitude value.

(ii) Clean the oil cooler fan.

(iii) Measure the T/R drive vibration  level  without  balancing  the  T/R
      drive, and record the amplitude value.

(iv) Calculate  the difference  between the two amplitude values.  If  the
     difference is greater than 0.75 inch per second (ips), before further
     flight, replace each oil cooler fan assembly bearing.

(2) After the effective date of this AD,  do not install an oil cooler fan
    assembly bearing with more than 0 hours TIS unless the requirements of
    this AD have been accomplished.

(f) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager,  Safety Management Section,  Rotorcraft Standards Branch,
    FAA,  may approve AMOCs  for  this AD.  Send  your  proposal  to:  Rao
    Edupuganti, Aviation Safety Engineer,  Regulations and Policy Section,
    Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
    76177; telephone (817) 222-5110;email 9-ASW-FTW-AMOC-Requests@faa.gov.

(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.

(g) ADDITIONAL INFORMATION

(1) Airbus Helicopters Alert Service Bulletin No. AS355-05.00.77, Revision
    0 dated July 3, 2017, which is not incorporated by reference, contains
    additional information about the subject  of this AD.  For service in-
    formation identified in this AD,  contact Airbus Helicopters,  2701 N.
    Forum Drive,  Grand Prairie, TX  75052;  telephone  (972) 641-0000  or
    (800) 232-0323; fax (972) 641-3775 or at http://www.helicopters.airbus
    .com/website/en/ref/Technical-Support_73.html.  You may review  a copy
    of the service information at the FAA, Office of the Regional Counsel,
    Southwest Region, 10101 Hillwood Pkwy, Rm. 6N-321, Ft Worth, TX 76177.

(2) The subject of this AD is addressed in European Aviation Safety Agency
    (EASA) AD No. 2017-0159, dated August 25, 2017.  You may view the EASA
    AD on the  Internet at http://www.regulations.gov  in  Docket No. FAA-
    2018-0438.

(h) SUBJECT

    Joint Aircraft Service Component (JASC) Code:  6510, Tail Rotor Drive-
    shaft.

Issued in Fort Worth, Texas, on September 12, 2018. Scott A. Horn,  Deputy
Director for Regulatory  Operations, Compliance &  Airworthiness Division,
Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety Engineer,
Regulations and Policy Section,  Rotorcraft Standards Branch,  FAA,  10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email rao.
edupuganti@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0438; Product Identifier 2017-SW-062-AD; Amendment
39-19410; AD 2018-19-10]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters. This AD requires measuring a vibration level in the tail
rotor (T/R) drive. This AD was prompted by reports of bearing
degradation. The actions of this AD are intended to prevent an unsafe
condition on these helicopters.

DATES: This AD is effective October 30, 2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.
html. You may review the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2018-0438; or in person at Docket
Operations 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 Docket Operations (phone:
800-647-5527) is U.S. Department of Transportation, Docket Operations,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Section, Rotorcraft Standards Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email rao.edupuganti@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On May 17, 2018, at 83 FR 22886, the Federal Register published our
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR
part 39 by adding an AD that would apply to Airbus Helicopters Model
AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. The NPRM
proposed to require measuring the T/R drive vibration level without
balancing, cleaning the fan, and repeating the vibration level
measurement. If the difference between the two amplitude values is
greater than 0.75 inch per second (ips), the NPRM proposed to require
replacing each T/R fan bearing. The proposed requirements were intended
to prevent degradation of the main gearbox (MGB) oil cooler fan bearing
(bearing), which could result in loss of MGB and engine oil cooling
function, loss of the rear transmission, and subsequent loss of control
of the helicopter.
The NPRM was prompted by AD No. 2017-0159, dated August 25, 2017,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters. EASA advises of two occurrences on Model AS355 military
helicopters in which the MGB bearing installed on the T/R drive shaft
experienced significant degradation. EASA states that while
investigation has not determined the cause of the failures, this
condition may also occur on other Model AS355 helicopters due to design
commonality. According to EASA, this condition, if not detected and
corrected, could result in loss of MGB and engine oil cooling function,
loss of the rear transmission, and subsequent loss of control of the
helicopter. To address this unsafe condition and as an interim measure,
the EASA AD requires two vibration level measurements of the forward
portion of the tail rotor drive line, one before and one after cleaning
the MGB oil cooler fan, and replacing the bearings if excessive level
or level trends are detected. The EASA AD also specifies that after the
effective date of the AD, only those MGB oil cooler fan assembly
bearings that are new or that have passed the vibration level
measurements may be installed.

Comments

We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, 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.

Interim Action

We consider this AD to be an interim action. The manufacturer is
currently developing a terminating action for the unsafe condition
described in this AD. If a terminating action is identified, we may
consider further rulemaking then.

Related Service Information

Airbus Helicopters has issued Alert Service Bulletin No. AS355-
05.00.77, Revision 0, dated July 3, 2017, which contains procedures for
checking the condition of the fan assembly bearings by measuring the
vibration levels of the first section of the T/R drive.

Costs of Compliance

We estimate that this AD affects 104 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD.
At an average labor rate of $85 per work-hour, measuring the
vibration levels requires about 5 work-hours, for a cost of $425 per
helicopter and $44,200 for the U.S. fleet. If required, replacing both
fan assembly bearings requires about 8 work-hours, and required parts
cost $1,064, for a cost of $1,744 per helicopter.

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 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

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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):