
[Federal Register Volume 82, Number 90 (Thursday, May 11, 2017)]
[Rules and Regulations]
[Pages 21913-21916]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-09376]



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 Rules and Regulations
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  Federal Register / Vol. 82, No. 90 / Thursday, May 11, 2017 / Rules 
and Regulations  

[[Page 21913]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6651; Directorate Identifier 2016-SW-015-AD; 
Amendment 39-18867; AD 2017-09-05]
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, AS332L1, AS332L2, and 
EC225LP helicopters. This AD requires repetitively checking screws in 
the emergency flotation gear. This AD is prompted by a report that a 
screw ruptured on a Model AS332 helicopter's emergency flotation gear. 
These actions are intended to correct an unsafe condition on these 
products.

DATES: This AD becomes effective May 26, 2017.
    We must receive comments on this AD by July 10, 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-
6651; 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 (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.airbushelicopters.com/techpub. 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: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
matthew.fuller@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

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA Emergency AD No. 2015-0239-E, dated 
December 18, 2015, to correct an unsafe condition for Airbus 
Helicopters Model AS 332 C, AS 332 C1, AS 332 L, AS 332 L1, AS 332 L2, 
and EC 225 LP helicopters with emergency flotation gear. EASA advises 
that a screw ruptured on the rear upper fitting on the left-hand (LH) 
emergency flotation gear of an AS332 helicopter. EASA states that this 
condition, if not detected and corrected, could result in the failure 
of an emergency flotation system when ditching and unstable floating of 
the helicopter, possibly resulting in injury to the occupants. EASA 
consequently requires repetitive inspections of the lower attachment 
screws of rear upper fitting on the rear LH and right-hand (RH) 
emergency flotation gears. According to EASA, the root cause of the 
failure has not yet been identified.

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

    We have reviewed Airbus Helicopters Emergency Alert Service 
Bulletin (EASB) No. 05.01.06, Revision 0, dated December 18, 2015, for 
Model AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters and for 
military Model AS332B, AS332B1, AS332F1, AS332M, and AS332M1 
helicopters, and EASB No. 05A047, Revision 0, dated December 18, 2015, 
for Model EC225LP helicopters. This service information specifies 
repetitively

[[Page 21914]]

inspecting the lower screws of the rear upper fitting on the rear LH 
and RH emergency floating gears for the presence of the heads and 
stressing the screw heads using a tool to make sure that the screw head 
does not move. If all screw heads are present, the service information 
requires no further action. If at least one screw head is missing or 
moves, the service information specifies replacing the two lower screws 
and the upper screw and informing Airbus Helicopters.

AD Requirements

    This AD requires, within 15 hours time-in-service (TIS) and 
thereafter before each flight over water, visually checking the rear 
upper fittings of the LH and RH emergency flotation gears for the 
presence of screw heads and looseness. An owner/operator (pilot) may 
perform the required visual check and must enter compliance with the 
applicable paragraph of the AD into the helicopter maintenance records 
in accordance with 14 CFR 43.9(a)(1) through (4) and 91.417(a)(2)(v). A 
pilot may perform this check because it involves visually checking the 
rear upper fittings of the LH and RH emergency flotation gears for the 
presence of screw heads and twisting the screws by hand, which can be 
performed equally well by a pilot or a mechanic. This check is an 
exception to our standard maintenance regulations. If any screw heads 
are missing, loose, or twist off with hand pressure, this AD requires 
replacing all screws in the fitting before the next flight over water.

Differences Between This AD and the EASA AD

    The EASA AD allows using tools for the inspection, while this AD 
requires checking by hand. The EASA AD requires that repetitive 
inspections occur at intervals not to exceed 15 hours TIS, while this 
AD requires the repetitive checks before each flight over water. The 
EASA AD requires contacting Airbus Helicopters if a screw is missing or 
loose, while this AD does not.

Interim Action

    We consider this AD interim action. The design approval holder is 
currently investigating the root cause for this unsafe condition and 
may develop a modification that will address this unsafe condition. If 
this modification is developed, approved and available, we might 
consider additional rulemaking.

Costs of Compliance

    We estimate that this AD affects 24 helicopters of U.S. Registry 
and that labor costs average $85 per work-hour. Based on these 
estimates, we expect the following costs:
     Checking the screws requires about 1/10 of a work-hour and 
no parts are needed, for a cost of $9 per helicopter and $216 for the 
U.S. fleet.
     Replacing the screws requires 8 work-hours for a labor 
cost of $680. Parts cost $150 for a total cost of $830 per helicopter.

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 within 15 hours TIS.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and 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):

2017-09-05 Airbus Helicopters: Amendment 39-18867; Docket No. FAA-
2016-6651; Directorate Identifier 2016-SW-015-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, AS332L1, AS332L2, and EC225LP helicopters with emergency 
flotation gear installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a rear upper 
screw fitting on the emergency flotation gear. This condition, if 
not detected and corrected, could result in failure of the emergency 
flotation system and subsequent capsizing of the helicopter.

(c) Effective Date

    This AD becomes effective May 26, 2017.

(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

    Within 15 hours time-in-service, and before each flight over 
water thereafter:

[[Page 21915]]

    (1) Visually check each emergency flotation gear left hand and 
right hand rear upper fitting to determine whether the heads of the 
lower screws are present. Figure 1 to paragraph (e)(1) of this AD 
depicts where the lower three screws (noted as B and E) are located. 
Check each screw for looseness by determining whether it can be 
rotated by hand. The actions required by paragraph (e)(1) of this AD 
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 Title 14 
Code of Federal Regulations (14CFR) Sec. Sec.  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.
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[[Page 21916]]

    (2) If a screw head is missing or if a screw is loose, before 
further flight over water, replace all screws in the fitting. 
Replacing the screws is not a terminating action for the repetitive 
checks required by this AD.

(f) Special Flight Permits

    Special flight permits are prohibited for flight over water.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
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.

(h) Additional Information

    (1) Airbus Helicopters Emergency Alert Service Bulletin No. 
05.01.06, and Airbus Helicopters Emergency Alert Service Bulletin 
No. 05A047, both Revision 0, and both dated December 18, 2015, which 
are not incorporated by reference, contain additional information 
about the subject of this AD. For 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.airbushelicopters.com/techpub. 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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) Emergency AD No. 2015-0239-E, dated December 
18, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2016-6651.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 3212, Emergency 
Flotation Section.

    Issued in Fort Worth, Texas, on April 24, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-09376 Filed 5-10-17; 8:45 am]
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