[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Proposed Rules]
[Pages 5325-5329]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-01954]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0034; Directorate Identifier 2013-SW-006-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter Deutschland GmbH 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) 2012-10-
53 for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2,
EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2012-10-53
currently requires, 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 proposed AD would continue to require
checking and inspecting the upper and lower MRH shaft flanges for a
crack. The proposed 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: We must receive comments on this proposed AD by April 1, 2014.
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
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.eurocopter.com/techpub. You may review 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: Gary Roach, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 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
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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 15, 2012, we issued Emergency AD (EAD) No. 2012-10-51 for
ECD Model EC135 series helicopters to detect a crack on the MRH shaft
flange. EAD No. 2012-10-51 required a pilot check of the lower MRH
shaft flange for a crack or deformed blade attachment bolt safety pins
before the first flight of each day, inspecting the upper and lower MRH
shaft flanges for a crack within 5 hours TIS, and replacing the MRH
shaft if there is a crack. EAD No. 2012-10-51 was prompted by AD No.
2012-0041-E, dated March 12, 2012, issued by EASA, which is the
Technical Agent for the Member States of the European Union, to correct
an unsafe condition for the ECD Model EC 135 series helicopters. EASA
revised AD No. 2012-0041-E with EASA AD No. 2012-0041R1, dated March
15, 2012.
After we issued EAD No. 2012-10-51, EASA issued AD No. 2012-0085-E,
dated May 17, 2012, which superseded EASA AD No. 2012-0041R1. EASA
advised that since issuing EASA AD No. 2012-0041R1, further cracks had
been detected on two other helicopters during the pre-flight checks.
These are the same two cracks that prompted our EAD No. 2012-10-51.
However, EASA also stated that identification of deformed safety pins
may not be sufficient to detect a crack on the MRH shaft flange. ECD
investigated the cause of the cracks and developed new inspection
procedures with further corrective actions. Therefore, we issued EAD
No. 2012-10-53 on May 18, 2012, which superseded EAD No. 2012-10-51.
EAD No. 2012-10-53 was published in the Federal Register as a Final
rule; request for comments on November 20, 2012, at 77 FR 69558.
In issuing AD No. 2012-10-53, we included additional part-numbered
MRH shafts that should have been included in EAD No. 2012-10-51,
changed the daily checks to recurring checks at intervals not to exceed
6 hours TIS, added a 10 hour-TIS recurring inspection on MRH shafts
with 400 or more hours TIS, and removed the check of the blade
attachment bolt safety pins for deformation.
Actions Since AD 2012-10-53 Was Issued
Since we issued EAD No. 2012-10-53 on May 18, 2012, which was
published as a Final Rule; Request for Comments on November 20, 2012 at
77 FR 69558, Eurocopter revised Alert Service Bulletin (ASB) No. EC135-
62A-029, now at Revision 7, dated October 22, 2012. 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 No. 2012-0085R5, dated
October 30, 2012, to correct the unsafe condition. EASA advised 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 No. 2012-0085R5 to be interim AD action and further AD
action may follow.
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
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
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.
Proposed AD Requirements
This proposed AD would retain the repetitive visual check and
inspection of the upper and lower MRH shaft flanges, as well as the
replacement requirements of AD No. 2012-10-53 (77 FR 69558, November
20, 2012). 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
Sec. Sec. 43.9(a)(1)-(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. That check is an exception to our standard maintenance
regulations. Further, this proposed AD would 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 No. 2012-10-53 (77 FR 69558, November 20, 2012),
would continue to be considered approved as an AMOC for the
corresponding requirements in this proposed AD.
Differences Between This Proposed AD and the EASA AD
EASA considers its AD action to be an interim action; we do not
consider this proposed AD to be interim AD action because the proposed
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, while this proposed AD would not. The EASA
AD requires the initial visual check within 3 days, while this proposed
AD would require the initial visual check before further flight. The
EASA AD does not specify affected MRH shaft part numbers; this proposed
AD would because the FAA anticipates that ECD will produce new part-
numbered MRH shafts without the same unsafe condition.
Costs of Compliance
We estimate that this proposed AD would affect 244 helicopters of
U.S. Registry. We estimate inspecting the MRH shaft flanges would
require 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 would
require about 8 work-hours at an
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average labor rate of $85 per work-hour, and required parts would 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 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)
2012-10-53 (77 FR 69558, November 20, 2012), and adding the following
new AD:
Eurocopter Deutschland GmbH (ECD): 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) Comments Due Date
We must receive comments by April 1, 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)-(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.
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[GRAPHIC] [TIFF OMITTED] TP31JA14.001
(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 the applicability 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,
[[Page 5329]]
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.
(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 in Docket No. FAA-2014-0034 on the Internet at
http://www.regulations.gov.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.
Issued in Fort Worth, Texas, on January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-01954 Filed 1-30-14; 8:45 am]
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