AD 2017-26-04

We are superseding Airworthiness Directive (AD) 2009-25-07 for Airbus Helicopters Model EC120B helicopters. AD 2009-25-07 required amending the rotorcraft flight manual supplement (RFMS) and pre-flight checking the emergency flotation gear before each flight over water. Since we issued AD 2009-25-07, Airbus Helicopters developed a terminating action and identified an additional part-

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numbered emergency floatation gear part with the unsafe condition. This new AD retains the requirements of AD 2009-25-07, expands the applicability, and adds a terminating action for the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these helicopters.

Final rule.

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) 2009-25-07, Amendment 39-16126 (74 FR 65682, December 11, 2009), and adding the following new AD:

2017-26-04 Airbus Helicopters (Previously Eurocopter France): Amendment 39-19135; Docket No. FAA-2017-0671; Product Identifier 2016-SW-072-AD.

(a) Applicability

This AD applies to Airbus Helicopters (previously Eurocopter France) Model EC120B helicopters, certificated in any category, with a Lighting and Ancillary Control Unit (LACU) part-number (P/N) 040101AB or 040101BA with a float arm pushbutton P/N 045004A111A installed.

(b) Unsafe Condition

This ADdefines the unsafe condition as failure of a ``float arm'' pushbutton, which could result in inoperative floats being used in an emergency water ditching, causing damage to the helicopter or injury to occupants.

(c) Affected ADs

This AD supersedes AD 2009-25-07, Amendment 39-16126 (74 FR 65682, December 11, 2009).

(d) Effective Date

This AD becomes effective January 24, 2018.

(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, amend the EC120B Rotorcraft Flight Manual Supplement (RFMS) for the Aerazur emergency flotation gear, by inserting a copy of this AD into the Limitations section of the RFMS or by making pen and ink changes to that section to add the information in Figure 1 to paragraph (f)(1) of this AD:

Figure 1 to Paragraph (f)(1)--Amendment to RFMS ------------------------------------------------------------------------

------------------------------------------------------------------------- Arm the emergency flotation gear by pressing the LACU ``FLOAT ARM''
pushbutton.
--If both lights of the pushbutton remain lit, flight over water is
permitted.
--If one or both lights of the pushbutton do not remain lit, FLIGHT
OVER WATER IS PROHIBITED. ------------------------------------------------------------------------

(2) Before each flight over water:
(i) Perform a functional check to determine whether flight over water is permitted under the Limitations section in paragraph (f)(1) of this AD. For purposes of this AD, ``flight over water'' means flight beyond the power-off gliding distance from shore. ``Shore'' is an area of land adjacent to the water and above the high water mark but does not include land area that is intermittently under water. The actions required by this paragraph 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 14 CFR 43.9(a)(1) through (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.
(ii) If the LACU fails the functional check required by paragraph (f)(2)(i) of this AD, place a placard over the ``float arm'' pushbutton that reads ``INOP.''
(3) Within 300 hours time-in-service, replace float arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304-2500- 00. Installing float arm pushbutton P/N 304-2500-00 is terminating action for the functional check and placard required by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(4) Do not install float arm pushbutton P/N 045004A111A on any helicopter.

(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: George Schwab, Aviation Safety Engineer, Safety Management 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.

(h) Additional Information

(1) Airbus Helicopters Emergency Alert Service Bulletin No. 04A007, Revision 1, dated June 30, 2016, and Airbus Helicopters Alert Service Bulletin No. EC120-31A008, Revision 0, dated June 30, 2016, 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/website/technical-expert/. You may review a copy of the service information at the FAA, Office of

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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) AD No. 2016-0180, dated September 13, 2016. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA-2017-0671.

(i) Subject

Joint Aircraft Service Component (JASC) Code: 2560 Emergency Equipment.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2009-25-07 (74 FR 65682, December 11, 2009) (2009- 25-07), and add a new AD. AD 2009-25-07 applied to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2009-25-07 required amending the limitations section of RFMS to prohibit flight over water if the ``float arm'' pushbutton does not remain lit, conducting a pilot check to determine whether the ``float arm'' pushbutton remains lit before any flight over water, and placarding the ``float arm'' pushbutton as inoperative if the functional check is unsuccessful.
The NPRM published in the Federal Register on July 14, 2017 (82 FR 32501). The NPRM was prompted by AD No. 2016-0180, dated September 13, 2016 (AD 2016-0180), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Model EC120B helicopters. EASA advises thatAirbus Helicopters has designed an improved latching pushbutton, which when installed becomes a terminating action for the repetitive functional checks of the float arm pushbuttons. EASA also states that lighting and ancillary control unit (LACU) part number (P/N) 040101BA is equipped with the same faulty pushbutton and must be included in the applicability.
Accordingly, the NPRM proposed to retain the RFMS amendment and repetitive functional check requirements of AD 2009-25-07, add LACU P/N 040101BA to the applicability paragraph, require replacing the float arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304-2500- 00 within 300 hours time-in-service (TIS), and prohibit installing float arm pushbutton P/N 045004A111A on any helicopter. Replacing the float arm pushbutton was also proposed as a terminating action for the repetitive functional checks prior to flight overwater. An owner/ operator (pilot) may perform the functional check required by this AD and must entercompliance with that paragraph 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 only a functional check to determine whether the emergency flotation gear has been armed and can be performed equally well by a pilot or a mechanic. This check is an exception to our standard maintenance regulations.
The proposed requirements were intended to prohibit flight over water if a functional test indicates that the emergency flotation gear cannot be armed, which would preclude deployment of the floats in an emergency water ditching, resulting in subsequent damage to the helicopter and injury to occupants.
Since the NPRM was issued, the FAA's Aircraft Certification Service has changed its organization structure. The new structure replaces product directorates with functional divisions. We have revised some of the office titles and nomenclature throughout this Final rule to reflect the new organizational changes. Additional information about the new structure can be found in the Notice published on July 25, 2017 (82 FR 34564).

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

We have reviewed the relevant information and determined that an 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.

Differences Between This AD and the EASA AD

The EASA AD requires installing the LACU float arm pushbutton within 13 months; this AD requires the installation within 300 hours TIS.

Related Service Information

We reviewed Airbus Helicopters Emergency Alert Service Bulletin No. 04A007, Revision 1, dated June 30, 2016 (EASB), for Airbus Helicopters Model EC120B helicopters. The EASB describes procedures for a pre- flight check of the float arm pushbutton while arming the emergency flotation gear and prohibits operators from flight over water if the float arm pushbutton fails.
We also reviewed Airbus Helicopters Alert Service Bulletin No. EC120-31A008, Revision 0, dated June 30, 2016 (ASB), for Airbus Helicopters Model EC120B helicopters. The ASB describes procedures for replacing the float arm pushbutton with a new design pushbutton and for re-labeling the modified LACU with a new P/N label.

Costs of Compliance

We estimate this AD will affect 53 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, the cost of revising the limitations section of the RFMS and of the pre- flight functional check is negligible. Replacing the float arm pushbutton will require about 2 work-hours, and required parts cost about $311, for a cost per helicopter of $481 and a total cost of $25,493 to the U.S. fleet.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I,

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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.