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ADs updated daily at www.Tdata.com
2017-06-11 AIRBUS HELICOPTERS: ( c o r r e c t i o n ) Amendment 39-18835; Docket No. FAA-2016-4674; Directorate Identifier 2016-SW-001-AD.
TDATA NOTE: The FAA is making a correction to add a figure.  Figure 1  was
            missing from the FAA copy of the AD. The figure was present in
            the Federal Register, and was present in this Tdata release.

(a) APPLICABILITY

    This AD applies to Airbus Helicopters Model EC120B helicopters with an
    Air  Comm Corporation  (Air Comm)  air conditioning  kit installed  in
    accordance  with supplemental  type certificate  (STC) No.  SR00491DE,
    where the compressor is driven by a pulley installed aft of the  rotor
    brake, certificated in any category.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as failure of an air  conditioner
    compressor drive pulley (pulley)  or tail rotor output  wheel (wheel),
    leading to loss of tail rotor drive and helicopter control.

(c) AFFECTED ADS

    This  AD supersedes  Emergency AD  2015-24-51,  Directorate Identifier
    2015-SW-086-AD, dated November 27, 2015.

(d) EFFECTIVE DATE

    This AD becomes effective May 8, 2017.

(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 further flight and at intervals not to exceed 25 hours time-in-
    service disassemble the tail rotor drive system and remove the pulley.

(i) Visually inspect  the pulley splines for wear.  If any splines are not
    straight,  contain any inconsistent cross-sections end-to-end, or con-
    tain any localized material deformation or any material loss,  replace
    the pulley before further flight.

Note 1 to paragraph (f)(1)(i) of this AD:  End-to-end (fore-and-aft) move-
ment witness marks  and  polishing are acceptable as the pulley is allowed
to slip fore and aft on the wheel per its intended function.

(ii) Inspect  the  exposed  portion  of  each  wheel spline  for cracking,
     scoring,  metal pick-up,  and  wear  by using  Figure 1  to paragraph
     (f)(1)(ii) of this AD. To inspect for wear, position two 3 mm  (0.118
     inch)  rods  in  all diametrically  opposed  splines  and measure  to
     determine whether there is a minimum of 37.3 mm (1.47 inches)  across
     the outside diameter of the  rods. If there is any  cracking, scoring
     or metal pick-up, or if a  measurement is less than 37.3 mm,  replace
     the wheel.

                        ILLUSTRATION (Figure 1)

(2) Within 10 days after completing the initial inspection, report the in-
    formation  requested  in  Appendix 1 to this AD  by mail to the Denver
    Aircraft Certification Office, FAA, Technical Operations Center, 26805
    East 68th Avenue, Room 214, Denver, CO 80249, attn. Richard R. Thomas;
    by fax to (303) 342-1088; or by email to richard.r.thomas@faa.gov.

(3) Replacing  the Air Comm pulley  with  Airbus Helicopters output flange
    part number C632A2158201 constitutes terminating action for this AD.

(g) SPECIAL FLIGHT PERMITS

    Special flight permits are prohibited.

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Denver Aircraft Certification Office,  FAA,  may  approve
    AMOCs for this AD. Send your proposal to: Richard R. Thomas, Aerospace
    Engineer,  Denver  Aircraft  Certification  Office,   FAA,   Technical
    Operations Center, 26805 East 68th Avenue, Room 214, Denver, CO 80249;
    fax (303) 342-1088; email richard.r.thomas@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.

(i) ADDITIONAL INFORMATION

(i) Air  Comm  Service Bulletin  No.  SB-EC120-111815,  Revision A,  dated
    November 20, 2015,  which is not incorporated  by reference,  contains
    additional information about the subject of this AD.  For  service in-
    formation identified in this AD,  contact:  Air Comm Corporation, 1575
    West 124th Avenue,  Westminster, CO 80234,  telephone:  (303) 440-4075
    (during  business  hours)  or  (720) 233-8330  (after  hours);  email:
    service@aircommcorp.com, Web site: http://www.aircommcorp.com/contact.

(ii) You may view  a  copy of Supplemental Type Certificate No. SR00491DE,
     reissued  on  November 24, 2014,   on  the  Internet  at  http://www.
     regulations.gov by searching for  and  locating it in Docket No. FAA-
     2016-4674.

(iii) You may review a copy of the service information  at the FAA, Office
      of  the  Regional Counsel,  Southwest Region,  10101 Hillwood Pkwy.,
      Room 6N-321, Fort Worth, TX 76177.

(j) SUBJECT

    Joint Aircraft Service Component (JASC) Code:  6500,  Tail Rotor Drive
    System.

Issued in Fort Worth,  Texas,  on February 1, 2017. Scott A. Horn,  Acting
Manager, Rotorcraft Directorate, Aircraft Certification Service.

APPENDIX 1 TO AD 2017-06-11

Please report  the  following to the Denver Aircraft Certification Office,
FAA, Technical Operations Center,  by mail to 26805 East 68th Avenue, Room
214, Denver, CO 80249, attn. Richard R. Thomas;  by fax to (303) 342-1088;
or by email to richard.r.thomas@faa.gov:

(1) Condition of the splined joint.  Document any damage found with photo-
    graphs.

(2) Flight hours since the air-conditioning kit was installed.

(3) Aircraft serial number.

(4) Pulley serial number (etched on the pulley's face).

(5) Output wheel serial number from main gearbox, MAIN MODULE hard card.

(6) Primary operating location of the aircraft.

(7) Approximate average percentage of time the air conditioner is used.

(8) Operator and maintenance facility contact information.

(9) If parts  are  replaced,  will air conditioning system remain fully or
    partially operable?

FOR  FURTHER  INFORMATION  CONTACT:  Richard  R.  Thomas,  Aviation Safety
Engineer, Denver Aircraft Certification Office,  FAA, Technical Operations
Center,  26805 East 68th Avenue,  Room 214,  Denver,  CO 80249;  telephone
(303) 342-1085; fax (303) 342-1088; email richard.r.thomas@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4674; Directorate Identifier 2016-SW-001-AD;
Amendment 39-18835; AD 2017-06-11]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Emergency Airworthiness Directive
(Emergency AD) 2015-24-51 for Airbus Helicopters Model EC120B.
Emergency AD 2015-24-51 required inspections of the air conditioning
system. This supersedure revises the applicability, some of the
terminology, and the inspection requirements. This AD was prompted by a
report of an abnormal noise during flight of a Model EC120B helicopter that
resulted in a precautionary landing. We are issuing this AD to prevent an unsafe
condition on these products.

DATES: This AD becomes effective May 8, 2017.
We must receive comments on this AD by June 20, 2017.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the
online instructions for sending your comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-2016-
4674; 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 Supplemental Type Certificate (STC), the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (telephone 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
For service information identified in this final rule, contact Air
Comm Corporation, 1575 West 124th Avenue, Westminster, CO 80234,
telephone: (303) 440-4075 (during business hours) or (720) 233-8330
(after hours), email service@aircommcorp.com, Web site http://www.aircommcorp.com/contact. 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.

FOR FURTHER INFORMATION CONTACT: Richard R. Thomas, Aviation Safety
Engineer, Denver Aircraft Certification Office, FAA, Technical
Operations Center, 26805 East 68th Avenue, Room 214, Denver, CO 80249;
telephone (303) 342-1085; fax (303) 342-1088; email
richard.r.thomas@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.

Discussion

On November 27, 2015, we issued Emergency AD 2015-24-51, which was
made immediately effective to all known U.S. owners and operators of
Airbus Helicopters Model EC120B helicopters. Emergency AD 2015-24-51
applied to Model EC120B helicopters with an Air Comm Corporation (Air
Comm) air conditioning system installed in accordance with STC No.
SR00491DE. Emergency AD 2015-24-51 required, before further flight and
at intervals not to exceed 25 hours time-in-service (TIS), manually
inspecting the air conditioner compressor drive pulley (pulley) for
movement (play) between the pulley and the tail rotor output wheel
(wheel). If there was any movement, Emergency AD 2015-24-51 required
replacing the pulley and the wheel before further flight. If no play
existed, Emergency AD 2015-24-51 required an additional inspection for
wear and, if needed, replacing the pulley and the wheel. Emergency AD
2015-24-51 also required reporting information to the FAA to enable us
to obtain better insight into the cause of the unsafe condition.
Emergency AD 2015-24-51was prompted by a report that the operator
of an Airbus Helicopters Model EC120B helicopter heard an abnormal
noise during flight that gradually became more pronounced, resulting in
a precautionary landing. While applying power to land, the helicopter
yawed left. Application of the right pedal did not correct the
rotation, requiring the pilot to perform a hovering auto rotation. A
preliminary investigation showed that the pulley and wheel mating
splines had worn away, allowing the pulley to rotate freely on the
wheel. Failure of the pulley and wheel during flight may result in the
loss of tail rotor drive and subsequent loss of directional control.

Actions Since AD 2014-24-51 Was Issued

After Emergency AD 2015-24-51 was issued, we received a comment
from an operator requesting that we clarify the applicability of the
AD. The commenter notes that there are two different configurations for
the Air Comm conditioning system, the earlier of which has the output
flange that is terminating action in the AD already installed. However,
the applicability of Emergency AD 2015-24-51 does not distinguish
between the two configurations. Pictures from another operator we
received with an inspection report showed this earlier configuration
where the compressor is driven by a pulley mounted forward of the rotor
brake.
We agree with the request to clarify the applicability. Pulleys
installed forward of the rotor brake are not part of the tail rotor
drive train and their failure would not result in a loss of directional
control. We have revised this AD to apply only to those helicopters
with an Air Comm air conditioning kit installed in accordance with STC
No. SR00491DE where the compressor is driven by a pulley installed aft
of the rotor brake. Helicopters that have an Air Comm air conditioning
kit installed in accordance with STC No. SR00491DE where the compressor
is driven by a pulley forward of the rotor brake are excluded from this
AD's requirements.
We are replacing the term ``tail rotor output pinion'' used in
Emergency AD 2015-24-51 with ``tail rotor output wheel,'' because it is
the more commonly known term for this part.
We also received a comment from an operator stating that if play
between the pulley and the wheel is found during the inspection, and if
the Air Comm pulley is replaced with an Airbus output flange, the AD
should not require that the wheel be replaced if it passes the damage
and wear criteria in the Airbus Helicopters maintenance manual. We
agree that in the absence of wear, regardless of any play, the wheel
should not have to be replaced. We are revising the required actions in
this AD to remove the inspection for play and instead require an
inspection of the wheel for damage and wear, using criteria consistent with
that in the Airbus Helicopters maintenance manual.
We also obtained additional information from Air Comm about the
effect of the terminating action in Emergency AD 2015-24-51 and whether
it is necessary to deactivate the airconditioning system. As a result,
we are removing from the terminating action the requirement to fully or
partially deactivate the air conditioning system. Replacing the Air
Comm pulley with Airbus Helicopters output flange part number
C632A2158201 partially deactivates the system. With the Air Comm pulley
replaced, the system is sufficiently deactivated. Cooling will no
longer be available, but the evaporator blowers will remain operable to
circulate air. Neither the air conditioning system nor the helicopter
will be damaged by removing the compressor drive belt and leaving the
circuit breakers engaged.
We also have learned that this AD affects five helicopters of U.S.
registry, and not only the two helicopters noted in Emergency AD 2015-
24-51.

FAA's Determination

We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of this same type design and that air safety and the public
interest require adopting the AD requirements as proposed.

Related Service Information

We reviewed Air Comm Service Bulletin SB-EC120-111815, Revision A,
dated November 20, 2015. Air Comm reports that the pulley, mounted to
the Thomas coupling just aft of the main rotor brake caliper, is an
integral piece of the power transmission components for the tail rotor.
A field report indicated that the spline joint on the pulley can wear
beyond its capability to ensure power transmission to the tail rotor
shaft. Given that the installation is flight critical, the Air Comm
service bulletin specifies an inspection of the pulley-output wheel
interface. If excessive play or wear is found, the aircraft must be
made inoperable until unairworthy parts are replaced.

AD Requirements

This AD requires, before further flight and at intervals not to
exceed 25 hours TIS, removing the pulley and visually inspecting the
pulley splines for wear and inspecting the exposed portion of the wheel
splines for cracks, scoring, metal pick-up, and measuring for wear. If
any of the splines on the pulley are not straight, contain any
inconsistent cross-sections end-to-end, or contain any localized
material deformation or any material loss, this AD requires replacing
the pulley before further flight. If there is cracking, any scoring or
metal pick-up, or if a measurement shows wear, this AD requires
replacing the wheel before further flight.
This AD also requires reporting certain information to the FAA
within 10 days.
Replacing the Air Comm pulley with Airbus Helicopters output flange
part number C632A2158201 constitutes terminating action for this AD.

Differences Between This AD and the Service Information

The service information specifies recurring inspections after 100
flight hours, while this AD requires recurring inspections at intervals
not to exceed 25 hours TIS. The service information requires inspecting
the pulley and drive shaft (wheel) splines for excessive wear or
chatter and replacing the pulley and wheel if there is any play. This
AD requires replacing the pulley if any splines are not straight, have
inconsistent cross-sections, or contain material deformation or loss.
This AD requires replacing the wheel if cracking, scoring, or metal
pick-up are found, or measurement of the splines indicates excessive
wear. The service information requests that information be submitted to
Air Comm, while this AD requires the inspection results be reported to
the FAA.

Costs of Compliance

We estimate that this AD will affect 5 helicopters of U.S. Registry
and that labor costs average $85 a work-hour. Based on these estimates
we expect that inspecting the pulley and wheel will take about 7.5
work-hours for a cost of $638 per helicopter and $3,190 for the U.S.
fleet per inspection cycle. Replacing an Air Comm pulley will cost
$2,380 for parts and 0.5 additional work-hour for a cost of $2,423 per
helicopter. Replacing an Airbus wheel will cost $19,231 for parts and
10 additional work-hours for a cost of $20,081 per helicopter. The
optional terminating action of installing an Airbus output flange will
cost $2,327 for parts and 0.5 additional work-hour for a cost of $2,370
per helicopter. Reporting the required inspection information to the
FAA will take about 0.5 work-hour for a cost of about $43 per
helicopter and $215 for the U.S. fleet.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting required by this AD
is mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA at
800 Independence Ave. SW., Washington, DC 20591. ATTN: Information
Collection Clearance Officer, AES-200.

FAA's Justification and Determination of the Effective Date

Providing an opportunity for public comments prior to adopting
these AD requirements would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because the required corrective
actions must be accomplished before further flight.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
prior public comment before issuing this AD are impracticable and
contrary to the public interest and that good cause exists to make this
AD effective in less than 30 days.

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.

Regulatory Findings

We 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, 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):