
[Federal Register Volume 81, Number 43 (Friday, March 4, 2016)]
[Rules and Regulations]
[Pages 11407-11409]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04678]



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  Federal Register / Vol. 81, No. 43 / Friday, March 4, 2016 / Rules 
and Regulations  

[[Page 11407]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2568; Directorate Identifier 2014-SW-026-AD; 
Amendment 39-18424; AD 2016-05-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-07-52 for 
certain Airbus Helicopters (previously Eurocopter France) Model AS350B, 
AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2014-07-
52 required repetitively inspecting certain reinforcement angles of the 
rear structure to tailboom junction frame (reinforcement angles) for a 
crack at 10 hour time-in-service (TIS) intervals, repairing any cracked 
reinforcement angle, and allowed an optional repetitive inspection with 
a 165 hour TIS inspection interval as a terminating action for the 10 
hour TIS inspections. This AD retains the inspection requirements of AD 
2014-07-52 and requires the inspection of the area around each 
reinforcement angle screw hole as terminating action to the 10 hour TIS 
inspections. We are issuing this AD to detect a crack in the 
reinforcement angle, which if not corrected, could result in loss of 
the tailboom and subsequent loss of control of the helicopter.

DATES: This AD is effective April 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of June 25, 2014 
(79 FR 33054, June 10, 2014).

ADDRESSES: For service information identified in this final rule, 
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, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177.

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-2015-
2568; 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 (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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2014-07-52, Amendment 39-17858 (79 FR 33054, June 
10, 2014) and add a new AD. AD 2014-07-52 applied to Airbus Helicopters 
Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, 
AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters with Modification (MOD) 07 3215 or with a reinforcement 
angle part number (P/N) 350A08.2493.21 or P/N 350A08.2493.23 installed. 
AD 2014-07-52 required, for helicopters with 640 or more hours TIS, 
repetitively inspecting each reinforcement angle for a crack every 10 
hours TIS. As an optional action, AD 2014-07-52 allowed a repetitive 
165 hour TIS inspection of the reinforcement angle under each attaching 
screw for a crack. AD 2014-07-52 was prompted by Emergency AD No. 2014-
0076-E, dated March 25, 2014, issued by EASA, which is the Technical 
Agent for the Member States of the European Union. EASA advises that 
during the inspection of several AS355 helicopters, cracks found in the 
reinforcement angles had initiated on the non-visible surface of the 
angle, and that this condition, if not corrected, could lead to further 
crack propagation and subsequent loss of the tailboom, resulting in 
loss of control of the helicopter. The EASA AD requires repetitive 
inspections of the reinforcement angles, and states that a terminating 
action is under investigation.
    The NPRM published in the Federal Register on July 23, 2015 (80 FR 
43645). The NPRM proposed to retain the 10 hour TIS repetitive 
inspections of the reinforcement angle and require (instead of allow as 
an option) the 165 hour TIS inspection of the junction frame bores as 
terminating action for the 10 hour TIS inspections. The NPRM also 
proposed to revise the applicability to only include helicopters with 
reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23, and not 
include helicopters with MOD 07 3215. Since MOD 07 3215 installed 
reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23, AD 2014-
07-52 was written to apply to helicopters with either the reinforcement 
angle P/Ns or with MOD 07 3215, so that operators could more easily 
determine whether AD 2014-07-52 applied to their aircraft. Airbus 
Helicopters then developed MOD 07 3232, which removes reinforcement 
angle P/N 350A08.2493.21 and P/N 350A08.2493.23. We removed MOD 07 3215 
from the applicability because we did not want the AD to apply to a 
helicopter with both MOD 07 3215 and MOD 07 3232 in its aircraft 
records, as it would not have reinforcement angle P/N 350A08.2493.21 or 
P/N 350A08.2493.23 installed. The proposed requirements were intended 
to detect a

[[Page 11408]]

crack in the reinforcement angle, which if not corrected, could result 
in loss of the tailboom and subsequent loss of control of the 
helicopter.
    Since the NPRM was issued, a group email address has been 
established for requesting an FAA alternative method of compliance for 
a helicopter of foreign design. We have revised this contact 
information in this final rule to reflect the new email address.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (79 FR 33054, 
June 10, 2014).

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 and that air safety and the public interest require 
adopting the AD requirements as proposed.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Differences Between This AD and the EASA AD

    This AD is not applicable to the AS350BB as that model is not type 
certificated in the U.S. This AD applies to Airbus Helicopters Model 
AS350C and AS350D1 helicopters because these helicopters have a similar 
design. Finally, the EASA AD requires operators to contact Airbus 
Helicopters if there is a crack, and this AD does not, however it does 
require repairing the crack before further flight.

Related Service Information Under 1 CFR Part 51

    Airbus Helicopters issued Emergency Alert Service Bulletin (EASB) 
No. 05.00.70 for Model AS350B, BA, BB, Bl, B2, B3, and D helicopters, 
and EASB No. 05.00.62 for Model AS355E, F, F1, F2, N, and NP 
helicopters, both Revision 0 and dated March 24, 2014. EASB No. 
05.00.70 and EASB No. 05.00.62 describe procedures for inspecting the 
angle reinforcements for a crack. 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.

Costs of Compliance

    We estimate that this AD affects 822 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 work-hour, 
inspecting the reinforcement angles for a crack without removing the 
screws requires 1.0 work-hour, for a cost per helicopter of $85 and a 
total cost of $69,870 for the U.S. fleet, per inspection cycle. 
Removing the screws and inspecting the reinforcement angle requires 2 
work-hours, for a cost per helicopter of $170 and a total cost of 
$139,740 for the U.S. fleet, per inspection cycle. If required, 
repairing a cracked reinforcement angle requires about 10 work-hours, 
and required parts cost about $300, for a total cost per helicopter of 
$1,150.

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 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 removing Airworthiness Directive (AD) 
2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014), and adding 
the following new AD:

2016-05-06 Airbus Helicopters (previously Eurocopter France): 
Amendment 39-18424; Docket No. FAA-2015-2568; Directorate Identifier 
2014-SW-026-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters, with a 
reinforcement angle part number (P/N) 350A08.2493.21 or P/N 
350A08.2493.23 installed, certificated in any category.

    Note 1 to paragraph (a) of this AD:  Helicopters with 
Modification (MOD) 073232 do not have P/N 350A08.2493.21 or P/N 
350A08.2493.23 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a rear 
structure to tailboom junction frame reinforcement angle 
(reinforcement angle), which if not detected could result in loss of 
the tail boom and subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-07-52, Amendment 39-17858 (79 FR 
33054, June 10, 2014).

[[Page 11409]]

(d) Effective Date

    This AD becomes effective April 8, 2016.

(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) For helicopters with 640 or more hours time-in-service (TIS) 
since installation of MOD 073215 or since installation of an 
applicable reinforcement angle, within 10 hours TIS, and thereafter 
at intervals not exceeding 10 hours TIS, inspect each reinforcement 
angle for a crack as depicted in Figure 1 of Airbus Helicopters 
Emergency Alert Service Bulletin No. 05.00.70 for Model AS350B, 
AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 
helicopters and Airbus Helicopters Emergency Alert Service Bulletin 
No. 05.00.62 for AS355E, AS355F, AS355F1, AS355F2, AS355N, and 
AS355NP helicopters, both Revision 0 and dated March 24, 2014.
    (2) If there is a crack, before further flight, repair the 
reinforcement angle in a manner approved by the manager listed in 
paragraph (h)(1) of this AD.
    (3) Within 165 hours TIS after the first inspection required by 
paragraph (f)(1) of this AD, and thereafter at intervals not 
exceeding 165 hours TIS, remove screw No. 5 from the reinforcement 
angle, thoroughly clean the area around the hole and inspect the 
reinforcement angle for a crack. If there is not a crack, reinstall 
the screw. Sequentially repeat the steps required by this paragraph 
for screws No. 6 through No. 12. If there is a crack, comply with 
paragraph (f)(2) of this AD. Accomplishment of the inspection 
required by this paragraph terminates the repetitive inspections 
required by paragraph (f)(1) of this AD.

(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, 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.
    (3) AMOCs approved previously in accordance with AD 2014-07-52, 
Amendment 39-17858 (79 FR 33054, June 10, 2014) are approved as 
AMOCs for the corresponding requirements of paragraph (f)(2) of this 
AD.

(i) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD 2014-0076-E, dated March 25, 2014. You may view the 
EASA AD on the Internet at http://www.regulations.gov in Docket No. 
FAA-2015-2568.

(j) Subject

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

(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.
    (3) The following service information was approved for IBR on 
June 25, 2014 (79 FR 33054, June 10, 2014).
    (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 05.00.62, Revision 0, dated March 24, 2014.
    (ii) Airbus Helicopters EASB No. 05.00.70, Revision 0, dated 
March 24, 2014.

    Note 2 to paragraph (k)(3):  Airbus Helicopters EASB No. 
05.00.62 and EASB No. 05.00.70, both Revision 0 and dated March 24, 
2014, are co-published as one document along with Airbus Helicopters 
EASB No. 05.00.45 and EASB No. 05.00.41, both Revision 0 and dated 
March 24, 2014, which are not incorporated by reference in this AD.

    (4) For Airbus Helicopters service information identified in 
this final rule, 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.
    (5) 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.
    (6) 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 25, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-04678 Filed 3-3-16; 8:45 am]
 BILLING CODE 4910-13-P


