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2014-16-24 AIRBUS HELICOPTERS DEUTSCHLAND GMBH (PREVIOUSLY EUROCOPTER DEUTSCHLAND GMBH) HELICOPTERS: Amendment 39-17948; Docket No. FAA-2014-0034; Directorate Identifier 2013-SW-006-AD.
(a) APPLICABILITY

    This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2,
    and EC135T2+  helicopters, with  a main  rotor hub  (MRH) shaft,  part
    number (P/N)  L623M1006101, L623M1206101,  L623M1006102, L623M1206102,
    L623M1006103, or L623M1206103 installed, certificated in any category.

(b) UNSAFE CONDITION

    This AD  defines the  unsafe condition  as a  crack in  the MRH  shaft
    flange, which could result in  failure of the MRH and  subsequent loss
    of control of the helicopter.

(c) AFFECTED ADS

    This AD  supersedes AD  2012-10-53,  Amendment  39-17254 (77 FR 69558,
    November 20, 2012).

(d) EFFECTIVE DATE

    This AD becomes effective September 25, 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) Before  further  flight,  and  thereafter at intervals not to exceed 6
    hours time-in-service (TIS), check the MRH shaft lower flange and  the
    visible area of the MRH shaft upper flange for a crack. Figures 1  and
    2 to Paragraph (f)(1) of this AD are examples of cracks that have been
    discovered in the MRH shaft lower flange. 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.

                        ILLUSTRATION (Figure 1)

                        ILLUSTRATION (Figure 2)

(2) For MRH shafts with 400 or  more hours TIS,  within 50 hours TIS,  and
    thereafter at intervals not to exceed 50 hours TIS:

(i) Remove the rotor-hub cap.

(ii) Clean the upper and lower MRH shaft flange as depicted in Figure 2 of
     Eurocopter  Alert  Service Bulletin  No.  EC135-62A-029,  Revision 7,
     dated October 22, 2012, and visually inspect for a crack.

(3) If  there  is  a  crack in the upper or lower MRH shaft flange, before
    further flight, replace  that MRH shaft  with an airworthy  MRH shaft.
    Replacing the  MRH shaft  with an  MRH shaft  having a  P/N listed  in
    paragraph (a) of  this AD does  not constitute terminating  action for
    the requirements of this AD.

(g) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Safety Management Group, 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 gary.b.roach@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) Any  AMOC  approved  previously  in accordance with AD No. 2012-10-53,
    Amendment 39-17254 (77 FR 69558, November 20, 2012), is approved as an
    AMOC for the corresponding requirements in paragraph (f) of this AD.

(h) ADDITIONAL INFORMATION

    The subject of this AD is addressed in European Aviation Safety Agency
    (EASA) AD No.  2012-0085R5,  dated October 30, 2012. You  may view the
    EASA AD on  the Internet at  http://www.regulations.gov in Docket  No.
    FAA-2014-0034.

(i) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head.

(j) 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 No. EC135-62A-029, Revision 7, dated
    October 22, 2012, excluding Figure 1.

(ii) Reserved.

(3) For  Eurocopter  service  information  identified in this AD,  contact
    Airbus Helicopters, Inc.,  2701 N. Forum Drive,  Grand Prairie,  Texas
    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
    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  August 8, 2014. Lance  T. Gant, Acting
Directorate  Manager,   Rotorcraft  Directorate,   Aircraft  Certification
Service.

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 gary.b.
roach@faa.gov.
PREAMBLE 

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-10-53 for
Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters) Model
EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters.
AD 2012-10-53 required, before further flight and at specified
intervals, checking and inspecting the upper and lower main rotor hub
(MRH) shaft flanges for a crack, and inspecting the lower hub-shaft
flange bolt attachment areas for a crack. Since we issued AD 2012-10-
53, it has been determined that it is safe to increase the visual
inspection intervals of the MRH shaft flanges from 10 hours time-in-
service (TIS) to 50 hours TIS and remove the inspection of the lower
MRH shaft flange bolt attachment areas. This new AD continues to
require checking and inspecting the upper and lower MRH shaft flanges
for a crack. These actions are intended to detect a crack on the MRH
shaft flange, which if not corrected, could result in failure of the
MRH and subsequent loss of control of the helicopter.

DATES: This AD is effective September 25, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
25, 2014.

ADDRESSES: For service information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.airbushelicopters.com/techpub. You may view this
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.

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-2014-
0034; or in person at the Docket Management Facility 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 information, the economic evaluation, any
comments received, and other information. The address for the Docket
Office (phone: 800-647-5527) is Document Management Facility, U.S.
Department of Transportation, Docket Operations, 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
gary.b.roach@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On May 18, 2012, we issued Emergency AD 2012-10-53, which
superseded Emergency AD 2012-10-51. Emergency AD 2012-10-53 was
published in the Federal Register as a Final rule; request for comments
on November 20, 2012, at 77 FR 69558. AD 2012-10-53 required a
repetitive pilot check of the lower MRH shaft flange for a crack, a
repetitive inspection of the upper and lower MRH shaft flanges and bolt
attachment areas for a crack, and replacing the MRH shaft if there is a
crack. AD 2012-10-53 was prompted by three reported incidents of
cracking on the lower hub-shaft flanges of EC135 model helicopters.
After we issued AD 2012-10-53, Eurocopter revised Alert Service
Bulletin (ASB) No. EC135-62A-029, now at Revision 7, dated October 22,
2012, which contains the procedures for the repetitive pilot checks and
inspections. The inspection interval for the visual inspection of the
MRH shaft flanges was increased to 50 flight hours based on results
from full scale component testing. The note regarding the preflight
check states that the time between two preflight checks must not exceed
6 flight hours, and clarifies that one flight may comprise of multiple
take-offs and landings and a flight starts when the helicopter takes
off and ends when the helicopter is on the ground with the engines shut
off. Eurocopter also removed the visual inspection of
the blade bolt attachment areas from the ASB.
EASA also revised its AD, now at EASA AD 2012-0085R5, dated October
30, 2012, to correct this unsafe condition. EASA advises that based on
results of the further full scale component testing, it has been
determined that the interval for the repetitive visual inspections of
the upper and lower hub shaft flanges can be extended to 50 flight
hours. EASA AD No. 2012-0085R5 also references ECD ASB No. EC135-62A-
029, Revision 7, dated October 22, 2012, for related information. EASA
considers AD 2012-0085R5 to be interim AD action and further AD action
may follow.
On January 16, 2014, we issued a notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to supersede AD 2012-10-53. The NPRM
published in the Federal Register on January 31, 2014 (79 FR 5325). The
NPRM proposed to continue to require the repetitive visual pilot check
and inspection of the upper and lower MRH shaft flanges, as well as the
replacement requirements of AD 2012-10-53. An owner/operator (pilot)
may perform the required visual check and must enter compliance with
the applicable paragraph of the AD 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 looking at the visible area of the MRH shaft flanges and can be
performed equally well by a pilot or a mechanic. This check is an
exception to our standard maintenance regulations. Further, the NPRM
proposed to increase the repetitive visual inspection interval for MRH
shafts with 400 hours or more TIS from 10 hours TIS to 50 hours TIS.
Any alternative method of compliance (AMOC) previously approved in
accordance with AD 2012-10-53 would continue to be considered approved
as an AMOC for the corresponding requirements in this AD.
Since we issued the NPRM, Eurocopter Deutschland GmbH changed its
name to Airbus Helicopters Deutschland GmbH. This AD reflects that
change and updates the contact information to obtain service
documentation.

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 5325,
January 31, 2014).

FAA's Determination

These helicopters have been approved by the aviation authority of
Germany and are approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA ADs. 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 except for the name change
previously described and a minor editorial change to meet current
publishing requirements. The reference to ``the applicability of this
AD'' in paragraph (f)(3) of this AD has been changed to reference
``paragraph (a) of this AD.'' These changes are consistent with the
intent of the proposals in the NPRM (79 FR 5325, January 31, 2014) and
will not increase the economic burden on any operator.

Differences Between This AD and the EASA AD

EASA considers its AD action to be an interim action; we do not
consider this AD to be an interim AD action because the requirements
for the applicable part-numbered MRH shafts are not expected to change.
The EASA AD requires you to report the findings and send the removed
MRH to ECD (now Airbus Helicopters), while this AD does not. The EASA
AD requires the initial visual check within 3 days, while this AD
requires the initial visual check before further flight. The EASA AD
does not specify affected MRH shaft part numbers; this AD does because
the FAA anticipates Airbus Helicopters will produce new part-numbered
MRH shafts without the same unsafe condition.

Related Service Information

We reviewed Eurocopter ASB No. EC135-62A-029, Revision 7, dated
October 22, 2012, which describes procedures for preflight checking the
visible area of the upper and lower MRH shaft flanges and performing a
repetitive visual inspection of the upper and lower MRH shaft for
cracks. EASA classified this ASB as mandatory and issued AD No. 2012-
0085R5 to ensure the continued airworthiness of these helicopters.

Costs of Compliance

We estimate that this AD affects 244 helicopters of U.S. Registry.
We estimate inspecting the MRH shaft flanges requires 2.5 work-hours at
an average labor rate of $85 per work-hour, for a total cost per
helicopter of $212 and a total cost to U.S. operators of $51,728 per
inspection cycle. Replacing an MRH shaft requires about 8 work-hours
and required parts cost $55,715, for a total cost per helicopter of
$56,395.

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 have 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 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.

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

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]


2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-10-53 (77 FR 69558, November 20, 2012), and adding the following
new AD: