Document ID: FAA-2014-0757-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters, Inc. (Previously Eurocopter France) Helicopters
Posted Date: 2014-10-07T04:00Z

[Federal Register Volume 79, Number 194 (Tuesday, October 7, 2014)]
[Rules and Regulations]
[Pages 60334-60337]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-23594]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0757; Directorate Identifier 2014-SW-030-AD; 
Amendment 39-17988; AD 2014-20-15]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters, Inc. (Previously 
Eurocopter France) Helicopters

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

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding airworthiness directive (AD) 2012-02-13 for 
certain Airbus Helicopters, Inc. (Airbus Helicopters) Model EC130B4 
helicopters. AD 2012-02-13 required inspecting certain areas of the 
tailboom/Fenestron junction frame (junction frame) for a crack. This AD 
retains the requirements of AD 2012-02-13, expands the inspection area 
of the junction frame, and reduces the repetitive inspection interval. 
These actions are intended to detect a crack in the junction frame, 
which could result in detachment of the Fenestron and subsequent loss 
of control of the helicopter.

DATES: This AD becomes effective October 22, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of October 22, 
2014.
    We must receive comments on this AD by December 8, 2014.

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 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, any incorporated by reference service information, 
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 AD, contact Airbus 
Helicopters, Inc., 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, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.

[[Page 60335]]

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 January 23, 2012, we issued AD 2012-02-13, Amendment 39-16936 
(77 FR 5994, February 7, 2012), which required repetitively inspecting 
the right-hand side of the junction frame for a crack, and if there was 
a crack, replacing the tailboom before further flight.
    AD 2012-02-13 was prompted by AD No. 2011-0116, dated July 6, 2011 
(AD 2011-0116), issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition for 
Eurocopter France (now Airbus Helicopters) Model EC130B4 helicopters. 
EASA advises of several reports of cracks in the junction frame 
developing in the plane of the rivet head countersink on the right-hand 
side of the Fenestron and spreading to the web of the frame. EASA 
further advises that this condition could lead to structural failure 
resulting in Fenestron detachment and subsequent loss of control of the 
helicopter. EASA AD 2011-0116 required compliance with Eurocopter's 
service information to repetitively inspect the affected area and 
depending on findings, accomplish corrective actions.

Actions Since AD 2012-02-13 Was Issued

    Since we issued AD 2012-02-13, EASA has issued AD No. 2014-0114-E, 
dated May 8, 2014, which superseded EASA AD 2011-0116, for Airbus 
Helicopters Model EC130B4 helicopters, except those with Modification 
(MOD) 073880, those with MOD 074609, or those that have been repaired 
in accordance with certain Repair Design Approval Sheets. EASA advises 
that after issuing EASA AD 2011-0116, Airbus Helicopters developed MOD 
074609, which limits the risk of cracks appearing on the junction 
frame, and revised its service information to expand the area of 
inspection. EASA AD 2014-0114-E requires repetitively inspecting the 
entire circumference of the junction frame for a crack, and also 
requires altering the helicopter in accordance with MOD 074609 as a 
terminating action for the repetitive inspections.
    We have also determined that the repetitive inspection interval can 
be reduced to 40 hours time-in-service (TIS) as specified in the Airbus 
Helicopters service information.

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

    Airbus Helicopters, Inc. has published Emergency Alert Service 
Bulletin (EASB) No. 53A019, Revision 1, dated April 15, 2014 (EASB 
53A019). EASB 53A019 describes procedures for inspecting the entire 
circumference of the junction frame from the inside and outside for 
cracks. If there is a crack, EASB 53A019 requires contacting Airbus 
Helicopters for approved repair instructions. Finally, if there is not 
a crack, EASB 53A019 requires altering the helicopter in accordance 
with MOD 074609 before December 12, 2017.

AD Requirements

    This AD requires repetitively inspecting the circumference of the 
junction frame for a crack by complying with specified portions of the 
manufacturer's service bulletin, and replacing the junction frame if 
there is a crack. This AD also prohibits installing a tailboom without 
MOD 073880 on any helicopter.

Differences Between This AD and the EASA AD

    The EASA AD allows for flights for a certain period of time with 
known cracks, while this AD does not permit operations with known 
cracks. The EASA AD allows for an initial inspection which does not 
require stripping the paint, and then stripping the paint prior to 
inspection within 110 flight hours. This AD mandates stripping the 
paint as part of the initial inspection. The EASA AD requires altering 
the helicopter with MOD 074609 before December 31, 2017, and this AD 
does not. The EASA AD requires contacting Airbus Helicopters for repair 
instructions if there is a crack, while this AD requires replacing the 
junction frame.

Costs of Compliance

    We estimate that this AD affects 160 helicopters of U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. Inspecting the junction frame for a crack will 
require 1 work-hour at an average labor cost of $85 per hour, for a 
total cost per inspection cycle $85 per helicopter and $13,600 for the 
entire fleet. If required, replacing a tailboom will require 50 work-
hours and required parts will cost $60,000, for a cost per helicopter 
of $64,250.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
correct this known unsafe condition. Therefore, we find the risk to the 
flying public justifies waiving notice and comment prior to the 
adoption of this rule because the cracks are in a primary structure of 
the helicopter that may prevent further safe flight and the required 
corrective actions must be accomplished within 10 hours TIS, a very 
short time period for the air tour and helicopter emergency medical 
services operations of these helicopters.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined 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:

[[Page 60336]]

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 removing Airworthiness Directive (AD) 
2012-02-13, Amendment 39-16936 (77 FR 5994, February 7, 2012), and 
adding the following new AD:

2014-20-15 Airbus Helicopters, Inc. (Previously Eurocopter France): 
Amendment 39-17988; Docket No. FAA-2014-0757; Directorate Identifier 
2014-SW-030-AD.

(a) Applicability

    This AD applies to Model EC130B4 helicopters that do not have 
Modification (MOD) 073880 incorporated, all serial numbers, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as cracks on the tailboom/
Fenestron junction frame (junction frame). This condition could result 
in structural failure of the tailboom, detachment of the Fenestron, and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2012-02-13, Amendment 39-16936 (77 FR 5994, 
February 7, 2012).

(d) Effective Date

    This AD becomes effective October 22, 2014.

(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) Within 10 hours time-in-service (TIS):
    (i) Inspect the right-hand side of the junction frame for cracks in 
the web from the inside as depicted in Details C and D of Figure 2 of 
Airbus Helicopters Emergency Alert Service Bulletin No. 53A019, 
Revision 1, dated April 15, 2014 (EASB).
    (ii) Strip the paint around the entire circumference of the 
junction frame as depicted in Detail E of Figure 3 of the EASB. Apply a 
coat of primer to the stripped area. Apply varnish to the stripped 
area.
    (iii) Inspect the stripped area of the frame for cracks from the 
outside.
    (2) Thereafter at intervals not to exceed 40 hours TIS, inspect the 
frame by following the inspection requirements of paragraphs (f)(1)(i) 
and (f)(1)(iii) of this AD.
    (3) If there is a crack, before further flight, replace the 
junction frame with an airworthy junction frame.
    (4) Do not install a tailboom that does not incorporate MOD 073880 
on any helicopter.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2014-0114-E, dated May 8, 2014. You may view the 
EASA AD on the Internet at http://www.regulations.gov in Docket No. 
FAA-2014-0757.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tail 
Boom.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the incorporation 
by reference (IBR) 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 No. 53A019, 
Revision 1, dated April 15, 2014.
    (ii) Reserved.
    (3) For Airbus Helicopters, Inc. service information identified in 
this AD, contact Airbus Helicopters, Inc., 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas 76137. 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

[[Page 60337]]

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 September 22, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-23594 Filed 10-6-14; 8:45 am]
BILLING CODE 4910-13-P