Document ID: FAA-2018-0177-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2018-03-09T05:00Z

[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)]
[Rules and Regulations]
[Pages 10360-10363]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04647]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0177; Product Identifier 2017-SW-138-AD; Amendment 
39-19218; AD 2018-05-09]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

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

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. 
This AD requires inspecting the tail rotor (T/R) flapping hinge link 
(hinge) and reporting the results. This AD is prompted by a report of a 
damaged flapping hinge link. The actions of this AD are intended to 
prevent an unsafe condition on these products.

DATES: This AD becomes effective March 26, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 26, 2018.
    We must receive comments on this AD by May 8, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the

[[Page 10361]]

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-2018-
0177; 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, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
Docket Operations (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 
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. It is also available 
on the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0177.

FOR FURTHER INFORMATION CONTACT: Martin R. Crane, Aviation Safety 
Engineer, Regulations & Policy Section, Rotorcraft Standards Branch, 
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].

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

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued Emergency AD No. 2017-0232-E, dated November 
21, 2017, to correct an unsafe condition for Airbus Helicopters Model 
AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. The EASA AD 
was prompted by the in-flight failure of a pin in a hinge attaching the 
T/R. EASA advises that damage to the hinge on a T/R blade was reported 
and that an investigation is ongoing to determine the root cause of the 
damage. EASA further advises that this condition could lead to failure 
of the hinge, unbalance of the T/R, and detachment of the T/R gearbox 
and hub with subsequent loss of control of the helicopter. To correct 
this unsafe condition, the EASA AD requires a one-time inspection of 
the flapping hinges, and depending on the findings, corrective actions. 
It also requires reporting the findings and sending any cracked 
components to Airbus Helicopters to support the investigation.

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 these same 
type designs.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Emergency Alert Service Bulletin 
(EASB) No. 64.00.43, Revision 0, dated November 21, 2017, for Model 
AS332-series helicopters. This service information describes procedures 
for visually and dye penetrant inspecting the hinges of all five T/Rs.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

AD Requirements

    This AD requires, within 25 hours time-in-service (TIS):
     Performing a tactile inspection of each hinge for friction 
points;
     Measuring for play in the drag plane;
     Measuring the tightening torque of each spindle bolt.
    [cir] If the tightening torque is not within the minimum and 
maximum torque, dye-penetrant inspecting the spindle bolt for a crack 
and removing the spindle bolt and hexagonal castellated nut from 
service;
    [cir] If the tightening torque is within the minimum and maximum 
torque, inspecting the spindle bolt for corrosion and fretting.
     Inspecting the bearing race inner ring and bearing needles 
for spalling and replacing the bearing race if there is any spalling;
     Measuring the thickness of each stop washer and removing 
the stop washer from service if the thickness is less than 1.5 mm (.060 
inch); and
     Inspecting the inner ring for brinelling.
    [cir] If there is brinelling deeper than 0.1 mm (.004 inch), 
repairing the hinge.
    [cir] If there is brinelling 0.1 mm (.004 inch) or less, dye-
penetrant inspecting the inner ring for a crack.
    This AD also requires, within 10 days after the inspection, 
reporting the results of each inspection and measurement to Airbus 
Helicopters.

Differences Between This AD and the EASA AD

    The EASA AD requires compliance within 25 hours TIS or at the next 
50 hour inspection of the T/R, whichever is later; this AD requires 
compliance within 25 hours TIS. The EASA AD requires returning parts to 
Airbus Helicopters, and this AD does not.

Interim Action

    We considered this AD interim action. The inspection reports that 
are required by this AD will enable Airbus Helicopters to obtain better 
insight into the cause of the damaged flapping hinge link, and 
eventually develop final action to address the unsafe condition. Once

[[Page 10362]]

final action has been identified, we might consider further rulemaking.

Costs of Compliance

    We estimate that this AD affects 20 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 hour, 
inspecting 5 T/R hinges will require 8 hours, and required materials 
cost would be minimal, for a cost per helicopter of $680 and a cost of 
$13,600 to the U.S. fleet. Reporting the inspection findings would 
require about 30 minutes, for a cost per helicopter of $43 and a cost 
of $860 to the U.S. fleet. If required, dye-penetrant inspecting the 
spindle bolt or inner ring would require about 1 hour, and required 
materials cost would be minimal, for a cost per helicopter of $85. If 
required, replacing a spindle bolt would require about 1 hour, and 
required parts would cost $625, for a cost per helicopter of $710.
    If required, replacing the bearing race would require about 1 hour, 
and required parts would cost $585, for a cost per helicopter of $670.
    If required, replacing the inner ring would require about 1 hour, 
and required parts would cost $1,986, for a cost per helicopter of 
$2,071.

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

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because the inspections required by this AD must be accomplished within 
25 hours TIS, a relatively short period of time for these helicopters 
as they are primarily used for offshore operations. Therefore, we find 
good cause that notice and opportunity for prior public comment are 
impracticable.
    In addition, for the reason stated above, we find that good cause 
exists for making this amendment 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

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 adding the following new airworthiness 
directive (AD):

2018-05-09 Airbus Helicopters: Amendment 39-19218; Docket No. FAA-
2018-0177; Product Identifier 2017-SW-138-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a tail rotor 
(T/R) flapping hinge link (hinge). This condition could result in 
unbalance of the T/R, detachment of the T/R gearbox and hub, and 
subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective March 26, 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 25 hours time-in-service, inspect each T/R hinge as 
follows:
    (i) Point each T/R blade downward and perform a tactile 
inspection of each hinge for friction points. Record whether there 
is a friction point.
    (ii) Measure play in the drag plane depicted as ``J'' in Figure 
1 of Airbus Helicopters Emergency Alert Service Bulletin No. 
64.00.43, Revision 0, dated November 21, 2017 (EASB 64.00.43), and 
record the measurement.
    (iii) Measure the tightening torque of each spindle bolt and 
record the measurement.
    (A) If the tightening torque is less than 564 inch-pounds or 
more than 955 inch-pounds, before further flight, dye-penetrant 
inspect the spindle bolt for a crack and record whether there is a 
crack. Remove the spindle bolt and the hexagonal castellated nut 
from service.
    (B) If the tightening torque is between 564 inch-pounds and 955 
inch-pounds, inspect

[[Page 10363]]

the spindle bolt for corrosion and fretting and record whether there 
is corrosion or fretting. If there is corrosion or fretting that 
cannot be removed by hand with an abrasive pad, before further 
flight, dye-penetrant inspect the spindle bolt for a crack in areas 
Z1 and Z2 as depicted in Figure 2 of EASB 64.00.43. If there is a 
crack, before further flight, record that there is a crack and 
remove from service the spindle bolt, hexagonal castellated nut, 
inner ring, stop washers, needle bearings or set of needle bearings, 
seals, and split washer.
    (iv) Remove the inner ring and stop washers.
    (v) Inspect the bearing race inner ring and bearing needles for 
spalling. If there is any spalling, before further flight, record 
that there is spalling and replace the bearing race.
    (vi) Measure the thickness of each stop washer. If the thickness 
is less than 1.5 mm (.060 inch), before further flight, remove the 
stop washer from service. Record that the stop washer was removed 
from service because of thickness.
    (vii) Inspect the inner ring for brinelling.
    (A) If there is brinelling more than 0.1 mm (.004 inch) in 
depth, before further flight, record that there is brinelling and 
repair the hinge.
    (B) If there is brinelling 0.1 mm (.004 inch) or less in depth, 
before further flight, turn the inner ring to position the area with 
brinelling on the T/R hub pin side. Record the brinelling and the 
turning of the inner ring. Dye-penetrant inspect the inner ring for 
a crack in the area depicted as ``Z3'' of Figure 3 of EASB 64.00.43. 
If there is a crack, before further flight, record that there is a 
crack in the inner ring and remove from service the spindle bolt, 
hexagonal castellated nut, inner ring, stop washers, needle bearings 
or set of needle bearings, seals, and split washer.
    (2) Within 10 days after the inspection, submit a report of the 
measurements and findings of the inspection required by paragraph 
(e)(1) of this AD, as specified in the Appendix of EASB 64.00.43, to 
[email protected].

 (f) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a 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 OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 30 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are 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.

(g) 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: 
Martin R. Crane, Aviation Safety Engineer, Regulations & Policy 
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; 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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) Emergency AD No. 2017-0232-E, dated November 21, 2017. 
You may view the EASA AD on the internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2018-0177.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6420 Tail Rotor 
Head.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 64.00.43, Revision 0, dated November 21, 2017.
    (ii) Reserved.

    Note 1 to paragraph (j)(2):  Airbus Helicopters EASB No. 
64.00.43, Revision 0, dated November 21, 2017, is co-published as 
one document along with Airbus Helicopters EASB No. 64.00.21, 
Revision 0, dated November 21, 2017, which is not incorporated by 
reference.

    (3) For Airbus Helicopters service information 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may 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://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on February 26, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-04647 Filed 3-8-18; 8:45 am]
 BILLING CODE 4910-13-P