AD 2014-04-11

[Federal Register Volume 79, Number 43 (Wednesday, March 5, 2014)]
[Rules and Regulations]
[Pages 12373-12375]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-04285]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0351; Directorate Identifier 2009-SW-049-AD; 
Amendment 39-17770; AD 2014-04-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France) (Airbus Helicopters)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model AS350B, BA, B1, B2, B3, and D, and Model AS355E, F, 
F1, F2, and N helicopters with certain tail rotor (T/R) blades. This AD 
requires installing additional rivets to secure each T/R blade trailing 
edge tab (tab), and inspecting for evidence of debonding of the tab 
after the rivets are installed. This AD was prompted by reports of T/R 
blade tab debonding. The actions of this AD are intended to prevent 
loss of a T/R blade tab, which could result in excessive vibration and 
loss of control of the helicopter.

DATES: This AD is effective April 9, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of April 9, 2014.

ADDRESSES: 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 
<a href="http://www.airbushelicopters.com/techpub">http://www.airbushelicopters.com/techpub</a>. You may review the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region,

[[Page 12374]]

2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 foreign authority's ADs, 
any incorporated-by-reference service information, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations Office (phone: 800-647-5527) is U.S. 
Department of Transportation, Docket Operations Office, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
<a href="/cdn-cgi/l/email-protection#2d4a4c5f54034f035f424c4e456d4b4c4c034a425b"><span class="__cf_email__" data-cfemail="f097918289de92de829f919398b0969191de979f86">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On April 22, 2013, at 78 FR 23692, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to Eurocopter France (now 
Airbus Helicopters) Model AS350B, BA, B1, B2, B3, D; and AS355E, F, F1, 
F2, and N helicopters with a T/R blade, part number (P/N) 355A12-0040-
00, 355A-12-0040-01, 355A12-0040-02, 355A12-0040-03, 355A-12-0040-04, 
355A12-0040-05, 355A-12-0040-07, 355A-12-0040-08, or 355A12-0040-14, 
all serial numbers (S/N); or P/N 355A12-0050-04, 355A12-0050-10, or 
355A12-0050-12, with a S/N 8400 through 9224. The NPRM proposed to 
require installing additional rivets to secure each tab, and inspecting 
for evidence of debonding of the tab after the rivets are installed. 
The proposed requirements were intended to prevent loss of a T/R blade 
tab, which could result in excessive vibration and loss of control of 
the helicopter.
    The NPRM was prompted by AD No. F-2004-178, dated November 10, 
2004, issued by the Direction Generale de l'Aviation Civile (DGAC), 
which is the aviation authority for France, for Model AS350B, BA, BB, 
B1, B2, B3, and D helicopters, fitted with certain T/R blades. The DGAC 
also issued AD No. F-2004-176, dated November 10, 2004, for Model 
AS355E, F, F1, F2, and N helicopters with certain T/R blades. The DGAC 
advises of reports of T/R blade tab debonding, and that the loss of the 
tab leads to a significant increase in the aircraft's vibration level. 
As a result, the ADs mandate compliance with the manufacturer's service 
information to install additional rivets on the tabs.
    Since we issued the NPRM, Eurocopter France changed its name to 
Airbus Helicopters. This AD reflects that change and updates the 
contact information to obtain service information.

Comments

    After our NPRM (78 FR 23692, April 22, 2013) was published, we 
received comments from one commenter.

Request

    American Eurocopter Corp. requested that we remove tail rotor blade 
P/Ns 355A12-0040-14, 355A12-0050-10, and 355A12-0050-12 from the 
applicability of our AD. The commenter stated that these tail rotor 
blades have trailing tabs that are integral with the tail rotor blade 
skin and not bonded on, and therefore are not susceptible to the unsafe 
condition identified in our AD. We agree and have made the requested 
change.

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, the DCAG, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are issuing this AD because we evaluated all information 
provided by the DGAC and determined the 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, except we have changed the 
applicability from Eurocopter France to Airbus Helicopters and removed 
tail rotor blades, P/N 355A12-0040-14, 355A12-0050-10, and 355A12-0050-
12, from the Applicability section. These changes are consistent with 
the intent of the proposals in the NPRM (78 FR 23692, April 22, 2013) 
and will not increase the economic burden on any operator nor increase 
the scope of the AD.

Differences Between This AD and the DGAC AD

    This AD does not include the Model AS350 BB because it does not 
have an FAA-issued type certificate. This AD requires compliance within 
100 hours time-in-service. The DGAC ADs require compliance within 100 
flying hours ``without exceeding 3 months.''

Related Service Information

    We reviewed Eurocopter Alert Service Bulletin (ASB) No. 64.00.05, 
Revision 2, dated February 15, 2007, for Model AS350B, BA, BB, B1, B2, 
B3, and D helicopters, and ASB No. 64.00.04, Revision 2, dated February 
15, 2007, for Model AS355E, F, F1, F2, and N helicopters.
    These ASBs specify, within 100 flying hours without exceeding three 
months, installing additional rivets on T/R blade tabs and inspecting 
each tab for debonding after the rivets have been installed. The DGAC 
classified these ASBs as mandatory and issued AD No. F-2004-176 and AD 
No. F-2004-178 to ensure the continued airworthiness of these 
helicopters.

Costs of Compliance

    We estimate that this AD affects 654 helicopters of U.S. registry 
and that labor costs average $85 a work-hour. Based on these estimates, 
we expect the following costs:
    <bullet> Installing rivets and inspecting for tab debonding takes 1 
hour for a labor cost of $85. Parts cost $100 for a total cost of $185 
per helicopter. The cost for the U.S. fleet totals $120,990.
    <bullet> Replacing the tab with an airworthy tab, if needed, takes 
4 hours for a total labor cost of $340. Parts cost $100, for a total 
cost of $440 per helicopter.

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 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

[[Page 12375]]

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.

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):

2014-04-11 Airbus Helicopters (Type Certificate Previously Held by 
Eurocopter France): Amendment 39-17770; Docket No. FAA-2013-0351; 
Directorate Identifier 2009-SW-049-AD.

 (a) Applicability

    This AD applies to Model AS350B, BA, B1, B2, B3, D; and AS355E, 
F, F1, F2, and N helicopters with a tail rotor (T/R) blade, part 
number (P/N) 355A12-0040-00, 355A-12-0040-01, 355A12-0040-02, 
355A12-0040-03, 355A-12-0040-04, 355A12-0040-05, 355A-12-0040-07, 
355A-12-0040-08, all serial numbers (S/N); or P/N 355A12-0050-04, 
with a S/N 8400 through 9224, certificated in any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as T/R blade trailing edge 
tab (tab) debonding. This condition could result in excessive 
vibration of the helicopter and loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective April 9, 2014.

 (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 100 hours time-in-service, install additional rivets on 
the trailing edge tab of each T/R blade, according to the following 
procedures, referencing Figure 1 of Eurocopter Alert Service 
Bulletin (ASB) No. 64.00.05, Revision 2, dated February 15, 2007, or 
ASB No. 64.00.04, Revision 2, dated February 15, 2007, whichever is 
applicable to your model helicopter:
    (1) Lightly sand the area to be drilled, using No. 80 then No. 
220 sandpaper.
    (2) Locate and drill eight 2.5 mm-diameter holes (T): 4 holes 
(T) 12 mm from the existing rivets (E) and on the centerline of the 
existing rivets (E), then 4 holes (T) 24 mm from the existing rivets 
(E) and on the centerline of the existing rivets (E).
    (3) Deburr and clean the area around the drilled holes.
    (4) Install 8 rivets (1) on tab (L). Any installation direction 
of the rivets is permissible (pressure face or suction face of the 
T/R blade).
    (5) Inspect the tab for debonding.
    (i) If there is no debonding, paint the area.
    (ii) If there is debonding, replace the tab.

 (f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, may approve AMOCs for this AD. Send your proposal 
to: Gary Roach, Aviation Safety Engineer, Regulations and Policy 
Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#5b3c3a292275397529343a38331b3d3a3a753c342d"><span class="__cf_email__" data-cfemail="fa9d9b8883d498d488959b9992ba9c9b9bd49d958c">[email&#160;protected]</span></a>.
    (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.

 (g) Additional Information

    The subject of this AD is addressed in the Direction Generale de 
l'Aviation Civile (DGAC) AD No. F-2004-176 and AD No. F-2004-178, 
both dated November 10, 2004. You may view the DCAG ADs on the 
Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> in Docket No. FAA-2013-0351.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail rotor 
blades.

(i) 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) Eurocopter Alert Service Bulletin 64.00.05, Revision 2, 
dated February 15, 2007.
    (ii) Eurocopter Alert Service Bulletin 64.00.04, Revision 2, 
dated February 15, 2007.
    (3) For Eurocopter 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 <a href="http://www.airbushelicopters.com/techpub">http://www.airbushelicopters.com/techpub</a>.
    (4) You may view this service information that is incorporated 
by reference at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Fort Worth, Texas, on February 19, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-04285 Filed 3-4-14; 8:45 am]
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