[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34335-34338]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14282]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0105; Directorate Identifier 2008-SW-58-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) (Airbus Helicopters) Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes superseding Airworthiness Directives 
(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 require 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 proposed AD 
would require 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. The proposed actions are intended to prevent 
coupling tube failure, loss of engine drive, and a subsequent forced 
landing of the helicopter.

DATES: We must receive comments on this proposed AD by August 17, 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 Direction 
Generale de L'Aviation Civile (DGAC) 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, Texas 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.airbushelicopters.com/techpub. You may review the 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: James Blyn, Aviation Safety Engineer, 
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas

[[Page 34336]]

76137; telephone (817) 222-5110; email [email protected].

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 March 6, 2000, we issued AD 2000-05-17, Amendment 39-11627 (65 
FR 13875, March 15, 2000) for Model EC120B helicopters with engine 
coupling tube, part number (P/N) C631A1002101, installed. AD 2000-05-17 
requires recurring inspections of each coupling tube for a crack and, 
if there is a crack, replacing any cracked coupling tube with an 
airworthy, reinforced coupling tube, P/N C631A1101101, and replacing 
certain engine support fitting parts. AD 2000-05-17 also requires 
replacing all affected coupling tubes with a reinforced coupling tube 
and replacing certain engine support fitting parts by March 31, 2000. 
AD 2000-05-17 was prompted by reports of cracks on the coupling tubes.
    On February 20, 2001, we issued AD 2001-04-12, Amendment 39-12131 
(66 FR 13232, March 5, 2001), for Model EC120B helicopters with engine 
coupling tube, P/N C631A1101101, installed. AD 2001-04-12 requires a 
visual check on each coupling tube for a crack at specified intervals. 
AD 2001-04-12 was prompted by several reports of cracks on the 
reinforced coupling tube.
    AD 2000-05-17 and AD 2001-04-12 were intended to prevent coupling 
tube failure, loss of engine drive, and a subsequent forced landing.

Actions Since AD 2000-05-17 and AD 2001-04-12 Were Issued

    Since we issued AD 2000-05-17 (65 FR 13875, March 15, 2000) and AD 
2001-04-12 (66 FR 13232, March 5, 2001), there have been reports of 
additional cracks in coupling tubes. Eurocopter France (now Airbus 
Helicopters) has conducted tests and determined that the washer-type 
engine mount may, in certain cases, induce excessive loading on the 
coupling tube since the design does not allow the operators to ensure 
that all of the parts are correctly assembled. Eurocopter France (now 
Airbus Helicopters) has also determined that excessive loading results 
in binding that increases component wear of the inner diameter of the 
mounting base.
    The DGAC, on behalf of the European Aviation Safety Agency, issued 
AD No. F-2003-325 R1, dated May 12, 2004, to correct an unsafe 
condition 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 certain 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 DGAC 
advises that a crack was detected on a reinforced coupling tube, which 
may lead to coupling tube failure and subsequent autorotation.
    This action is intended to prevent coupling tube failure, loss of 
engine drive, and a subsequent forced landing of the helicopter.

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 has kept the FAA informed 
of the situation described above. We are proposing 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.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Eurocopter service information:
     ASB No. 04A005, Revision 0, dated July 16, 2003, 
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-hand support bracket, P/N C714A1101103. SB 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.
     SB No. 71-005, Revision 0, dated May 14, 2004, 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 of this 
NPRM.
    The DGAC classified the service information contained in ASB No. 
04A005 and SB No. 71-005 as mandatory and issued AD No. F-2003-325 R1, 
dated May 12, 2004, to ensure the continued airworthiness of these 
helicopters.

Other Related Service Information

    We also reviewed the following Eurocopter service information:
     SB No. 71-003, Revision 1, dated July 18, 2002, contains 
procedures to improve the engine mount.
     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, 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

[[Page 34337]]

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.
    The DGAC also classified the service information contained in SB 
No. 71-003 and ASB No. 05A003 as mandatory and issued AD No. F-2003-325 
R1, dated May 12, 2004, to ensure the continued airworthiness of these 
helicopters.

Proposed AD Requirements

    This proposed AD would require:
     Before further flight, for certain helicopters, removing 
from service certain engine mount parts: support arm, P/N C714A1107201; 
swaged support arm, P/N C714A1106201; left-hand support bracket, P/N 
C714A1101102; and right-hand support bracket, P/N C714A1101103. 
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 affected parts.
     Within 25 hours time-in-service (TIS), for certain other 
helicopters that do not have the specified engine mount parts due to 
modifications, replacing the spring-type engine suspension system and 
dye-penetrant inspecting the flared coupling for a crack. If there is a 
crack in the flared coupling, before further flight, replacing the 
coupling with an airworthy coupling.
     Before further flight, removing coupling tube, P/N 
C631A1002101 from service. This proposed AD would prohibit installing 
coupling tube, P/N C631A1002101 on any helicopter.

Differences Between This Proposed AD and the DGAC AD

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

Costs of Compliance

    We estimate out of 115 helicopters on the U.S. registry about 23 
helicopters would be affected by this proposed AD. At an average labor 
rate of $85 per work hour, we estimate the following:
     Installing new mounting arms and brackets would require 
about 12 work hours and required parts would cost $9,194, for a total 
cost per helicopter of $10,214 and $234,922 for the fleet.
     Installing the mounting spring kit would require about 14 
work hours and required parts would cost $14,621, for a total cost per 
helicopter of $15,811 and $363,653 for the fleet.
     Dye-penetrant inspecting the coupling tube would require 
about 1 work hour for a cost per helicopter of $85 and $1,955 for the 
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 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:
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:

Airbus Helicopters (Previously Eurocopter France): 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) Comments Due Date

    We must receive comments by August 17, 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 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 34338]]

    (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, 
2601 Meacham Blvd., Fort Worth, Texas 76137; 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 AD. 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 review a copy 
of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.
    (2) The subject of this AD is addressed in Direction Generale de 
L'Aviation Civile (DGAC) AD No. F-2003-325 R1, Revision A, 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.

    Issued in Fort Worth, Texas, on May 29, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-14282 Filed 6-15-15; 8:45 am]
 BILLING CODE 4910-13-P