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[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)]
[Proposed Rules]
[Pages 43645-43647]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17952]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2568; Directorate Identifier 2014-SW-026-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede 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 currently requires 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 allows an 
optional repetitive inspection with a 165 hour TIS inspection interval 
as a terminating action for the 10 hour TIS inspections. This proposed 
AD would retain the inspection requirements of AD 2014-07-52 and 
require the inspection of the area around each reinforcement angle 
screw hole as terminating action to the 10 hour TIS inspections. These 
proposed actions are intended 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: We must receive comments on this proposed AD by September 21, 
2015.

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 proposed 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 proposed 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 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: 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: 

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On May 21, 2014, we issued AD 2014-07-52, Amendment 39-17858, 79 FR 
33054, June 10, 2014) for Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters with Modification 
(MOD) 07 3215 installed or with a reinforcement angle, part-number (P/
N) 350A08.2493.21 or 350A08.2493.23, installed. AD 2014-07-52 requires, 
for helicopters with 640 or more hours TIS, within 10 hours TIS and 
thereafter at

[[Page 43646]]

intervals not exceeding 10 hours TIS, repetitively inspecting each 
reinforcement angle for a crack. If there is a crack, AD 2014-07-52 
requires, before further flight, repairing the reinforcement angle. As 
an optional terminating action for the repetitive 10 hour TIS 
inspections, AD 2014-07-52 allows 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, to correct an unsafe condition for 
Airbus Helicopters Model AS350B, AS350BA, AS350BB, AS350B1, AS350B2, 
AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters with MOD 07 3215 or with at least one reinforcement angle, 
P/N 350A08.2493.21 or P/N 350A08.2493.23, installed. 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.

Actions Since AD 2014-07-52 Was Issued

    Since we issued AD 2014-07-52 (79 FR 33054, June 10, 2014), we have 
determined that the optional terminating action in AD 2014-07-52 should 
be a required terminating action. This NPRM would retain the actions in 
AD 2014-07-52 but would require the 165-hour TIS visual inspection as 
terminating action for the 10-hour TIS inspections. In addition, 
because MOD 07 3215 installed reinforcement angle P/Ns 350A08.2493.21 
and 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. 
Because a helicopter with both MOD 07 3215 and MOD 07 3232 in its 
aircraft records would not have reinforcement angle P/N 350A08.2493.21 
or P/N 350A08.2493.23 installed, this NPRM would revise the 
applicability to no longer include helicopters with MOD 07 3215 and to 
include a note clarifying that the AD would not apply if MOD 07 3232 is 
installed.

Comments

    After AD 2014-07-52 (79 FR 33054, June 10, 2014), was published, we 
received comments from three commenters.

Request

    Two commenters requested that the AD not be applicable to aircraft 
with MOD 07 3232 installed, as this modification improved the 
attachment at the junction frame to prevent cracking.
    We partially agree. Although AD 2014-07-52 does not apply to 
helicopters with MOD 07 3232 installed, we have revised the language in 
the proposed AD so that this exclusion is more clear.
    Two commenters requested that we increase the time between 
inspections or allow the repetitive inspections to end if no cracks are 
found after a few inspections. The commenters stated that the 
inspection frequency of the repetitive 165-hour TIS inspection is 
excessive and that if correctly installed, the doublers do not crack. 
One commenter stated that in practice the 165-hour inspection is being 
completed at every 100-hour inspection to avoid repeated grounding of 
the aircraft. Another commenter stated that frequent removal of the 
bolts and nuts could affect the airworthiness of the aircraft.
    We do not agree. Analysis has demonstrated that cracking has been 
found in more than one location, which indicates there may be more than 
one cause of the cracking. The uncertainty regarding the root cause of 
the cracking supports requiring the 165-hour TIS inspections without 
any changes.

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 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

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 of this NPRM.

Proposed AD Requirements

    This proposed AD would retain the 10 hour TIS repetitive inspection 
of the junction frame required by AD 2014-07-52 (79 FR 33054, June 10, 
2014), and would also require the repetitive 165 hour TIS inspection of 
the junction frame bores as a terminating action for the 10 hour TIS 
inspection. This proposed AD would also revise the applicability 
paragraph by no longer including helicopters with MOD 07 3215.

Differences Between This Proposed AD and the EASA AD

    This proposed AD is not applicable to the AS350BB as that model is 
not type certificated in the U.S. This proposed 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 
proposed AD does not, however it does require repairing the crack 
before further flight.

Interim Action

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

Costs of Compliance

    We estimate that this proposed AD would affect 822 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this proposed AD. At an average labor rate of 
$85 per hour, inspecting the reinforcement angles for a crack without 
removing the screws would require 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 would require 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 would require about 
10 work-hours, and

[[Page 43647]]

required parts would 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 products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2014-07052, Amendment 39-17858 (79 FR 33054, June 10, 2014), and adding 
the following new AD:

Airbus Helicopters (previously Eurocopter France): 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).

(d) Comments Due Date

    We must receive comments by September 21, 2015.

(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 07 3215 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 Permit

    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 
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.
    (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.

    Issued in Fort Worth, Texas, on July 15, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-17952 Filed 7-22-15; 8:45 am]
 BILLING CODE 4910-13-P
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