81 FR 40492 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 120 (June 22, 2016)

Page Range		40492-40495
FR Document		2016-14467
We are superseding Airworthiness Directive (AD) 2000-05-17 and AD 2001-04-12, which apply to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2000-05-17 and AD 2001-04-12 required repetitive visual checks of the engine-to-main gearbox (MGB) coupling tube assembly (coupling tube) for a crack and replacing any cracked tube with an airworthy tube. This new AD requires removing certain engine mount parts from service, measuring the height of the engine mounting base for certain helicopters, replacing the engine mount if a certain height is exceeded, inspecting the flared coupling on certain helicopters for a crack, and replacing the coupling if it is cracked. Since we issued AD 2000-05-17 and AD 2001-04-12, there have been reports of additional cracks in coupling tubes. These actions are intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter.
Federal Register, Volume 81 Issue 120 (Wednesday, June 22, 2016)
[Federal Register Volume 81, Number 120 (Wednesday, June 22, 2016)]
[Rules and Regulations]
[Pages 40492-40495]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-14467]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0105; Directorate Identifier 2008-SW-58-AD; 
Amendment 39-18562; AD 2016-12-13]
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) 2000-05-17 and 
AD 2001-04-12, which apply to Eurocopter France (now Airbus 
Helicopters) Model EC120B helicopters. AD 2000-05-17 and AD 2001-04-12 
required repetitive visual checks of the engine-to-main gearbox (MGB) 
coupling tube assembly (coupling tube) for a crack and replacing any 
cracked tube with an airworthy tube. This new AD requires removing 
certain engine mount parts from service, measuring the height of the 
engine mounting base for certain helicopters, replacing the engine 
mount if a certain height is exceeded, inspecting the flared coupling 
on certain helicopters for a crack, and replacing the coupling if it is 
cracked. Since we issued AD 2000-05-17 and AD 2001-04-12, there have 
been reports of additional cracks in coupling tubes. These actions are 
intended to prevent coupling tube failure, loss of engine drive, and a 
subsequent forced landing of the helicopter.

DATES: This AD is effective July 27, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 27, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 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 view this 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0105.

[[Page 40493]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0105; 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 
Direction Generale de L'Aviation Civile (DGAC) 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: James Blyn, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On May 29, 2015, we issued a notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to remove AD 2000-05-17 (65 FR 13875, March 15, 
2000) and AD 2001-04-12 (66 FR 13232, March 5, 2001) and add a new AD. 
AD 2000-05-17 applied to Model EC120B helicopters with engine coupling 
tube part number (P/N) C631A1002101 and required recurring inspections 
of each coupling tube for a crack and replacing any cracked coupling 
tube with a reinforced coupling tube P/N C631A1101101. AD 2001-04-12 
applied to Model EC120B helicopters with engine coupling tube P/N 
C631A1101101 and required repetitive visual checks of each coupling 
tube for a crack. AD 2000-05-17 and AD 2001-04-12 were prompted by 
reports of cracks on the reinforced coupling tube and were intended to 
prevent coupling tube failure, loss of engine drive, and a subsequent 
forced landing.
    The NPRM published in the Federal Register on June 16, 2015 (80 FR 
34335). The NPRM was prompted by reports of additional cracks in 
coupling tubes. Eurocopter France (now Airbus Helicopters) determined 
that the washer-type engine mount may, in certain cases, induce 
excessive loading on the coupling tube, which results in binding that 
increases component wear of the inner diameter of the mounting base. 
Because of this, the DGAC, on behalf of the European Aviation Safety 
Agency (EASA), issued AD No. F-2003-325 R1, dated May 12, 2004, for 
Model EC120B helicopters with engine coupling tube, P/N C631A1101101, 
and with an engine mount containing certain parts listed in Eurocopter 
Alert Service Bulletin (ASB) No. 04A005, dated July 16, 2003. DGAC AD 
No. F-2003-325 R1 requires inspections for helicopters with an engine 
mount block modified in accordance with Eurocopter Service Bulletin 
(SB) No. 71-003, Revision 1, dated July 18, 2002; replacing any 
coupling tube that has a crack; and increasing the life limit of the 
coupling tube from 1,000 flight hours to 20,000 flight hours. Also, 
DGAC AD No. F-2003-325 R1 requires, for helicopters with a new spring-
loaded engine suspension modification in accordance with Eurocopter SB 
No. 71-005, Revision 0, dated May 14, 2004, increasing the life limit 
of the coupling tube to 20,000 flight hours and canceling the 
repetitive inspections of the coupling tube.
    The NPRM proposed to require, for helicopters with certain engine 
mounts, before further flight, removing from service certain engine 
mount parts and measuring the height of the engine mounting base. If 
the height is more than 10.5 millimeters, the NPRM proposed replacing 
the engine mount with an engine mount that does not have the affected 
parts. For certain other helicopters, the NPRM proposed to require 
within 25 hours time-in-serice (TIS) replacing the spring-type engine 
suspension system, dye-penetrant inspecting the flared coupling for a 
crack, and replacing any cracked flared coupling. The NPRM also 
proposed removing coupling tube P/N C631A1002101 from service and 
prohibiting installation of that coupling tube on any helicopter.
    Since the NPRM was issued, the FAA Southwest Regional Office has 
relocated and a group email address has been established for requesting 
an FAA alternative method of compliance for a helicopter of foreign 
design. We have revised the contact information throughout this final 
rule to reflect the new address and new email address.

Comments

    After our NPRM (80 FR 34335, June 16, 2015) was published, we 
received comments from one commenter.

Request

    Airbus Helicopters disagrees with the proposed requirement to 
replace the spring-type engine suspension system in accordance with 
Eurocopter SB No. 71-005 for helicopters with an improved engine mount 
under Eurocopter SB No. 71-003. Airbus Helicopters states there have 
been no coupling tube failures since incorporation of Eurocopter SB No. 
71-003, and therefore the proposed requirement would not increase 
safety levels.
    We disagree. Installing the improved engine mount specified in 
Eurocopter SB No. 71-003 extends the compliance time for a recurring 
visual inspection of the coupling tube from 5 hours TIS to 25 hours 
TIS. When issued, that recurring inspection was considered a short-term 
interim action until an effective modification or action was developed, 
approved, and available. Eurocopter SB No. 71-005 contained such an 
effective action to cancel that interim action and was developed and 
approved in May 2004.
    Airbus Helicopters requested that, if we mandate the proposed 
requirement to replace the spring-type engine suspension system in 
accordance with Eurocopter SB No. 71-005, we change the proposed 
compliance time from 25 hours TIS to 18 months to allow for 
availability of parts.
    We disagree. Eurocopter SB No. 71-005 was approved May 13, 2004. 
The NPRM was published June 16, 2015. The substantial amount of time 
that has passed since the approval of the service information and 
publication of our NPRM provided operators with enough notice of our 
proposal to mandate that procedure such that availability of parts 
should not be an issue.

FAA's Determination

    This helicopter has been approved by the aviation authority of 
France and is approved for operation in the United States. Pursuant to 
our bilateral agreement with France, the DGAC on behalf of EASA, has 
kept the FAA informed of the situation described above. We are issuing 
this AD because we evaluated all information provided by the DGAC, 
reviewed the relevant information, considered the comments received, 
and determined the unsafe condition exists and is likely to exist or 
develop on other helicopters of this same type design and that air 
safety and the public interest require adopting the AD requirements as 
proposed.

Related Service Information Under 1 CFR Part 51

    Eurocopter issued ASB No. 04A005, Revision 0, dated July 16, 2003, 
which prohibits, after June 30, 2004, operating an engine mount made up 
of the following parts: Support arm, P/N C714A1107201; swaged support 
arm, P/N C714A1106201; left-hand support bracket, P/N C714A1101102; and 
right-

[[Page 40494]]

hand support bracket, P/N C714A1101103. ASB No. 04A005 also specifies 
measuring the height of the engine mounting base and, if the height is 
more than 10.5 millimeters, replacing the engine mount with an engine 
mount that does not have the specified P/N. ASB No. 04A005 does not 
apply to helicopters modified with an improved engine mount in 
accordance with SB No. 71-003. ASB No. 04A005 also does not apply to 
helicopters with a serial number 1170 or larger, as the specified 
engine mounts are not installed on those helicopters.
    Eurocopter also issued SB No. 71-005, Revision 0, dated May 14, 
2004, which contains procedures to modify the spring-type engine 
suspension system and dye-penetrant inspect the flared coupling 
assembly.
    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.

Other Related Service Information

    Eurocopter issued SB No. 71-003, Revision 1, dated July 18, 2002, 
which contains procedures to improve the engine mount. Eurocopter also 
issued ASB No. 05A003, Revision 2, dated July 16, 2003, for helicopters 
that have not been modified with an improved engine mount in accordance 
with SB No. 71-003, which specifies inspecting the coupling tube for a 
crack every 5 hours and establishing a coupling tube life limit of 
1,000 hours. For helicopters that have been modified with an improved 
engine mount, ASB No. 05A003 specifies inspecting the coupling tube for 
a crack every 25 hours and increasing the coupling tube life limit to 
20,000 hours. ASB No. 05A003 was revised to Revision 3, dated May 11, 
2004, to specify an optional spring-type engine suspension modification 
and cancel the repetitive inspection for this modified configuration.

Differences Between This AD and the DGAC AD

    This AD requires the installation of the spring-type engine 
suspension modification specified in Eurocopter SB No. 71-005 and does 
not require the repetitive inspection of the coupling tube and the 
engine mount base. This AD also does not require you to contact the 
manufacturer.

Costs of Compliance

    We estimate that this AD will affect 23 helicopters of the 115 
helicopters of U.S. Registry. At an average labor rate of $85 per work-
hour, we estimate that operators may incur the following costs in order 
to comply with this AD.
    Installing new mounting arms and brackets requires about 12 work-
hours and required parts cost $9,194, for a total cost per helicopter 
of $10,214 and $234,922 for the U.S. fleet. Installing the mounting 
spring kit requires about 14 work-hours and required parts cost 
$14,621, for a total cost per helicopter of $15,811 and $363,653 for 
the U.S. fleet. Dye-penetrant inspecting the coupling tube requires 
about 1 work-hour for a cost per helicopter of $85 and $1,955 for the 
U.S. fleet.

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 a regulatory, 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

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:
0
a. Removing Airworthiness Directive (AD) 2000-05-17, Amendment 39-11627 
(65 FR 13875, March 15, 2000); and AD 2001-04-12, Amendment 39-12131 
(66 FR 13232, March 5, 2001); and
0
b. Adding the following new AD:

2016-12-13 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-18562; Docket No. FAA-2014-0105; Directorate Identifier 
2008-SW-58-AD.

(a) Applicability

    This AD applies to Model EC120B helicopters with an engine-to-
main gearbox coupling tube assembly (coupling tube), part number (P/
N) C631A1101101 or P/N C631A1002101, installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a coupling 
tube. This condition could result in coupling tube failure, loss of 
engine drive, and a subsequent forced landing of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2000-05-17, Amendment 39-11627 (65 FR 
13875, March 15, 2000) and AD 2001-04-12, Amendment 39-12131 (66 FR 
13232, March 5, 2001).

(d) Effective Date

    This AD becomes effective July 27, 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 a serial number up to and including 
1169, not modified with an improvement of the engine mount in 
accordance with Eurocopter Service Bulletin (SB) No. 71-003, 
Revision 1, dated July 18, 2002 (SB 71-003), or not modified by 
installing a spring-type engine suspension system in accordance with 
Eurocopter SB No. 71-005, Revision 0, dated May 14, 2004 (SB 71-
005), before further flight:

[[Page 40495]]

    (i) Remove from service the following engine mount parts:
    (A) Support arm, P/N C714A1107201;
    (B) Swaged support arm, P/N C714A1106201;
    (C) Left-hand support bracket, P/N C714A1101102; and
    (D) Right-hand support bracket, P/N C714A1101103.
    (ii) Measure the height of the engine mounting base as depicted 
in Figure 1 of Eurocopter Alert SB No. 04A005, Revision 0, dated 
July 16, 2003. If the height is more than 10.5 millimeters, replace 
the engine mount with an engine mount that does not have the parts 
identified in paragraph (f)(1)(i) of this AD.
    (2) For helicopters with a serial number 1170 and larger or 
helicopters modified with an improvement of the engine mount in 
accordance with SB 71-003:
    (i) Within 25 hours TIS, replace the spring-type engine 
suspension system and perform a dye-penetrant inspection of the 
flared coupling for a crack by following the Accomplishment 
Instructions, paragraphs 2.B.2.a through 2.B.2.c of SB 71-005.
    (ii) If there is a crack in the flared coupling, before further 
flight, replace the coupling with an airworthy coupling.
    (3) For helicopters with coupling tube, P/N C631A1002101, 
installed, before further flight, remove coupling tube, P/N 
C631A1002101, from service. Do not install coupling tube, P/N 
C631A1002101, on any helicopter.

(g) Special Flight Permits

    Special flight permits may be issued provided there are no 
cracks in the coupling tube attachment fitting.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: James Blyn, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].
    (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

    (1) Eurocopter Alert Service Bulletin (ASB) No. 05A003, Revision 
2, dated July 16, 2003; Eurocopter ASB No. 05A003, Revision 3, dated 
May 11, 2004; and Eurocopter Service Bulletin No. 71-003, Revision 
1, dated July 18, 2002; which are not incorporated by reference, 
contain additional information about the subject of this final rule. 
For Eurocopter service information identified in this final rule, 
contact Airbus Helicopters, 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 
a copy of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177.
    (2) The subject of this AD is addressed in Direction Generale de 
L'Aviation Civile (DGAC) AD No. F-2003-325 R1, Revision 1, dated May 
12, 2004. You may view the DGAC AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0105.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6310, Engine/
Transmission Coupling--Coupling Tube, Engine Mount, and Engine Mount 
Base.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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. 04A005, Revision 0, 
dated July 16, 2003.
    (ii) Eurocopter Service Bulletin No. 71-005, Revision 0, dated 
May 14, 2004.
    (3) For Eurocopter service information identified in this final 
rule, contact Airbus Helicopters, 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, 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.
    (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 June 9, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-14467 Filed 6-21-16; 8:45 am]
 BILLING CODE 4910-13-P
40492 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations

(e) Reason FAA; or Transport Canada Civil Aviation DEPARTMENT OF TRANSPORTATION
This AD was prompted by the discovery of (TCCA); or Bombardier, Inc.’s TCCA Design
a number of incorrectly calibrated angle of Approval Organization (DAO). If approved by Federal Aviation Administration
attack (AOA) transducers installed in the the DAO, the approval must include the
stall protection system. We are issuing this DAO-authorized signature. 14 CFR Part 39
AD to detect and replace incorrectly
calibrated AOA transducers; incorrect (j) Related Information
calibration of the transducers could result in [Docket No. FAA–2014–0105; Directorate
Refer to Mandatory Continuing
late activation of the stick pusher. Identifier 2008–SW–58–AD; Amendment 39–
Airworthiness Information (MCAI) Canadian 18562; AD 2016–12–13]
(f) Compliance AD CF–2015–18, dated July 16, 2015, for
Comply with this AD within the related information. This MCAI may be
found in the AD docket on the Internet at RIN 2120–AA64
compliance times specified, unless already
done. http://www.regulations.gov by searching for
Airworthiness Directives; Airbus
and locating Docket No. FAA–2016–7265.
(g) Retained Replacement of AOA Helicopters (Previously Eurocopter
Transducers With No Changes (k) Material Incorporated by Reference France) Helicopters
This paragraph restates the requirements (1) The Director of the Federal Register
AGENCY: Federal Aviation
paragraph (g) of AD 2016–08–05, with no approved the incorporation by reference
changes. Within 2,500 flight hours or 12 Administration (FAA), DOT.
(IBR) of the service information listed in this
months, whichever occurs first after May 18, paragraph under 5 U.S.C. 552(a) and 1 CFR ACTION: Final rule.
2016 (the effective date of AD 2016–08–05), part 51.
replace the AOA transducers identified in SUMMARY: We are superseding
(2) You must use this service information
paragraph 1.A., ‘‘Effectivity,’’ of Bombardier
as applicable to do the actions required by
Airworthiness Directive (AD) 2000–05–
Service Bulletin 670BA–27–069, dated March 17 and AD 2001–04–12, which apply to
30, 2015, with correctly calibrated AOA this AD, unless this AD specifies otherwise.
(3) The following service information was Eurocopter France (now Airbus
transducers, in accordance with the Helicopters) Model EC120B helicopters.
Accomplishment Instructions of Bombardier approved for IBR on May 18, 2016, (81 FR
Service Bulletin 670BA–27–069, dated March 21709, April 13, 2016). AD 2000–05–17 and AD 2001–04–12
30, 2015. (i) Bombardier Service Bulletin 670BA–27– required repetitive visual checks of the
069, dated March 30, 2015. engine-to-main gearbox (MGB) coupling
(h) Retained Parts Installation Prohibition, tube assembly (coupling tube) for a
With a Change to the Affected Parts (ii) Reserved.
(4) For service information identified in crack and replacing any cracked tube
Language
this AD, contact Bombardier, Inc., 400 Côte- with an airworthy tube. This new AD
This paragraph restates the parts requires removing certain engine mount
installation prohibition specified in Vertu Road West, Dorval, Québec H4S 1Y9,
Canada; Widebody Customer Response parts from service, measuring the height
paragraph (h) of AD 2016–08–05, with a
change to the affected parts language. As of Center North America toll-free telephone: 1– of the engine mounting base for certain
May 18, 2016 (the effective date of AD 2016– 866–538–1247 or direct-dial telephone: 1– helicopters, replacing the engine mount
08–05), no person may install, on any 514–855–2999; fax: 514–855–7401; email: if a certain height is exceeded,
airplane, an AOA transducer having a part ac.yul@aero.bombardier.com; Internet: inspecting the flared coupling on certain
number and serial number listed in http://www.bombardier.com. helicopters for a crack, and replacing
paragraph 1.A., ‘‘Effectivity,’’ of Bombardier (5) You may view this service information the coupling if it is cracked. Since we
Service Bulletin 670BA–27–069, dated March at the FAA, Transport Airplane Directorate, issued AD 2000–05–17 and AD 2001–
30, 2015. 1601 Lind Avenue SW., Renton, WA. For 04–12, there have been reports of
(i) Other FAA AD Provisions information on the availability of this additional cracks in coupling tubes.
The following provisions also apply to this material at the FAA, call 425–227–1221. These actions are intended to prevent
AD: (6) You may view this service information coupling tube failure, loss of engine
(1) Alternative Methods of Compliance that is incorporated by reference at the drive, and a subsequent forced landing
(AMOCs): The Manager, New York Aircraft National Archives and Records of the helicopter.
Certification Office (ACO), ANE–170, FAA, Administration (NARA). For information on DATES: This AD is effective July 27,
has the authority to approve AMOCs for this the availability of this material at NARA, call 2016.
AD, if requested using the procedures found 202–741–6030, or go to: http://www.archives.
in 14 CFR 39.19. In accordance with 14 CFR The Director of the Federal Register
gov/federal-register/cfr/ibr-locations.html.
39.19, send your request to your principal approved the incorporation by reference
inspector or local Flight Standards District Issued in Renton, Washington, on June 13, of certain publications listed in this AD
Office, as appropriate. If sending information 2016. as of July 27, 2016.
directly to the ACO, send it to ATTN: Dionne Palermo, ADDRESSES: For service information
Program Manager, Continuing Operational
Acting Manager, Transport Airplane identified in this final rule, contact
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; Directorate, Aircraft Certification Service. Airbus Helicopters, 2701 N. Forum
telephone: 516–228–7300; fax: 516–794– [FR Doc. 2016–14579 Filed 6–21–16; 8:45 am] Drive, Grand Prairie, TX 75052;
5531. Before using any approved AMOC, BILLING CODE 4910–13–P telephone (972) 641–0000 or (800) 232–
notify your appropriate principal inspector, 0323; fax (972) 641–3775; or at http://
or lacking a principal inspector, the manager www.airbushelicopters.com/techpub.
of the local flight standards district office/ You may view this referenced service
certificate holding district office. The AMOC information at the FAA, Office of the
sradovich on DSK3TPTVN1PROD with RULES

approval letter must specifically reference Regional Counsel, Southwest Region,
this AD.
10101 Hillwood Pkwy., Room 6N–321,
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement Fort Worth, TX 76177. It is also
in this AD to obtain corrective actions from available on the Internet at http://
a manufacturer, the action must be www.regulations.gov by searching for
accomplished using a method approved by and locating Docket No. FAA–2014–
the Manager, New York ACO, ANE–170, 0105.

VerDate Sep<11>2014 16:06 Jun 21, 2016 Jkt 238001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\22JNR1.SGM 22JNR1
40494 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations

hand support bracket, P/N operators may incur the following costs List of Subjects in 14 CFR Part 39
C714A1101103. ASB No. 04A005 also in order to comply with this AD. Air transportation, Aircraft, Aviation
specifies measuring the height of the Installing new mounting arms and safety, Incorporation by reference,
engine mounting base and, if the height brackets requires about 12 work-hours Safety.
is more than 10.5 millimeters, replacing and required parts cost $9,194, for a
the engine mount with an engine mount total cost per helicopter of $10,214 and Adoption of the Amendment
that does not have the specified P/N. $234,922 for the U.S. fleet. Installing the Accordingly, under the authority
ASB No. 04A005 does not apply to mounting spring kit requires about 14 delegated to me by the Administrator,
helicopters modified with an improved work-hours and required parts cost the FAA amends 14 CFR part 39 as
engine mount in accordance with SB $14,621, for a total cost per helicopter follows:
No. 71–003. ASB No. 04A005 also does of $15,811 and $363,653 for the U.S.
not apply to helicopters with a serial fleet. Dye-penetrant inspecting the PART 39—AIRWORTHINESS
number 1170 or larger, as the specified coupling tube requires about 1 work- DIRECTIVES
engine mounts are not installed on those hour for a cost per helicopter of $85 and
helicopters. ■ 1. The authority citation for part 39
$1,955 for the U.S. fleet.
Eurocopter also issued SB No. 71– continues to read as follows:
005, Revision 0, dated May 14, 2004, Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701.
which contains procedures to modify Title 49 of the United States Code § 39.13 [Amended]
the spring-type engine suspension specifies the FAA’s authority to issue
system and dye-penetrant inspect the rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by:
flared coupling assembly. Section 106, describes the authority of ■ a. Removing Airworthiness Directive
This service information is reasonably the FAA Administrator. Subtitle VII, (AD) 2000–05–17, Amendment 39–
available because the interested parties Aviation Programs, describes in more 11627 (65 FR 13875, March 15, 2000);
have access to it through their normal detail the scope of the Agency’s and AD 2001–04–12, Amendment 39–
course of business or by the means authority. 12131 (66 FR 13232, March 5, 2001);
identified in the ADDRESSES section. and
We are issuing this rulemaking under ■ b. Adding the following new AD:
Other Related Service Information the authority described in Subtitle VII,
2016–12–13 Airbus Helicopters (Previously
Part A, Subpart III, Section 44701,
Eurocopter issued SB No. 71–003, Eurocopter France): Amendment 39–
‘‘General requirements.’’ Under that 18562; Docket No. FAA–2014–0105;
Revision 1, dated July 18, 2002, which
section, Congress charges the FAA with Directorate Identifier 2008–SW–58–AD.
contains procedures to improve the
promoting safe flight of civil aircraft in
engine mount. Eurocopter also issued (a) Applicability
air commerce by prescribing regulations
ASB No. 05A003, Revision 2, dated July This AD applies to Model EC120B
for practices, methods, and procedures
16, 2003, for helicopters that have not helicopters with an engine-to-main gearbox
the Administrator finds necessary for
been modified with an improved engine coupling tube assembly (coupling tube), part
safety in air commerce. This regulation
mount in accordance with SB No. 71– number (P/N) C631A1101101 or P/N
is within the scope of that authority
003, which specifies inspecting the C631A1002101, installed, certificated in any
because it addresses an unsafe condition category.
coupling tube for a crack every 5 hours
that is likely to exist or develop on
and establishing a coupling tube life (b) Unsafe Condition
products identified in this rulemaking
limit of 1,000 hours. For helicopters that
action. This AD defines the unsafe condition as a
have been modified with an improved crack in a coupling tube. This condition
engine mount, ASB No. 05A003 Regulatory Findings could result in coupling tube failure, loss of
specifies inspecting the coupling tube engine drive, and a subsequent forced
for a crack every 25 hours and We have determined that this AD will landing of the helicopter.
increasing the coupling tube life limit to not have federalism implications under
Executive Order 13132. This AD will (c) Affected ADs
20,000 hours. ASB No. 05A003 was
revised to Revision 3, dated May 11, not have a substantial direct effect on This AD supersedes AD 2000–05–17,
2004, to specify an optional spring-type the States, on the relationship between Amendment 39–11627 (65 FR 13875, March
the national government and the States, 15, 2000) and AD 2001–04–12, Amendment
engine suspension modification and 39–12131 (66 FR 13232, March 5, 2001).
cancel the repetitive inspection for this or on the distribution of power and
modified configuration. responsibilities among the various (d) Effective Date
levels of government. This AD becomes effective July 27, 2016.
Differences Between This AD and the For the reasons discussed above, I
DGAC AD (e) Compliance
certify that this AD:
This AD requires the installation of You are responsible for performing each
(1) Is not a ‘‘significant regulatory action required by this AD within the
the spring-type engine suspension action’’ under Executive Order 12866, specified compliance time unless it has
modification specified in Eurocopter SB already been accomplished prior to that time.
(2) Is not a ‘‘significant rule’’ under
No. 71–005 and does not require the
DOT Regulatory Policies and Procedures (f) Required Actions
repetitive inspection of the coupling
(44 FR 11034, February 26, 1979), (1) For helicopters with a serial number up
tube and the engine mount base. This
AD also does not require you to contact (3) Will not affect intrastate aviation to and including 1169, not modified with an
sradovich on DSK3TPTVN1PROD with RULES

the manufacturer. in Alaska to the extent that a regulatory, improvement of the engine mount in
and accordance with Eurocopter Service Bulletin
Costs of Compliance (SB) No. 71–003, Revision 1, dated July 18,
(4) Will not have a significant 2002 (SB 71–003), or not modified by
We estimate that this AD will affect economic impact, positive or negative, installing a spring-type engine suspension
23 helicopters of the 115 helicopters of on a substantial number of small entities system in accordance with Eurocopter SB No.
U.S. Registry. At an average labor rate of under the criteria of the Regulatory 71–005, Revision 0, dated May 14, 2004 (SB
$85 per work-hour, we estimate that Flexibility Act. 71–005), before further flight:

VerDate Sep<11>2014 16:06 Jun 21, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\22JNR1.SGM 22JNR1
Document Created: 2016-06-22 01:06:04
Document Modified: 2016-06-22 01:06:04
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective July 27, 2016.
Contact		James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]
FR Citation		81 FR 40492
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 40492 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 120 (June 22, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
