Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Rules and Regulations]
[Pages 37790-37793]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15290]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0566; Directorate Identifier 2011-SW-008-AD; 
Amendment 39-17065; AD 2012-11-02]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) that 
supersedes an existing Emergency Airworthiness Directive (EAD) for 
certain Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters. The 
existing EAD, which was previously sent to all known U.S. owners and 
operators of ECD Model EC135 helicopters and not made generally 
effective by publication in the Federal Register, currently requires 
inspecting the ring frame between the rear structure tube (tailboom) 
and the tail rotor fenestron housing (fenestron housing) for a crack 
before the first flight of each day and replacing any cracked ring 
frame with an airworthy ring frame. Since we issued that EAD, we have 
determined that a pre-flight pilot check in conjunction with a 
recurring 25-hour inspection is sufficient for determining the 
airworthiness of the ring frame. Additionally, ECD has developed a 
modification that is terminating action for the requirements of that 
EAD. This superseding AD revises the inspection requirements of the EAD 
to allow an owner/operator to perform the pre-flight pilot check, adds 
a recurring inspection of the ring frame, and allows for installation 
of a ring frame reinforcement as an optional terminating action for the 
AD requirements. The actions are intended to detect a crack in the ring 
frame which could result in loss of the fenestron structure and 
subsequent loss of control of the helicopter.

DATES: This AD becomes effective July 10, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of July 10, 2012.
    We must receive comments on this AD by August 24, 2012.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 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 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 a copy of the 
referenced 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: Sharon Miles, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; phone (817) 222-5110; email: 
[email protected].

[[Page 37791]]


SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA EAD 
No.: 2008-0190-E, dated October 13, 2008 (EAD 2008-0190-E), to correct 
an unsafe condition for EC135 and EC635 model helicopters. EASA advises 
that, during a recent pre-flight check on an EC 135 helicopter, a crack 
was detected on the ring frame that connects the tail rotor fenestron 
housing to the rear structure tube (tailboom). EASA states that this 
condition, if not corrected, could lead to crack propagation remaining 
undetected, possibly resulting in loss of the fenestron structure and 
loss of control of the helicopter. EAD 2008-0190-E requires 
accomplishing a pilot pre-flight check of the rear structure tube for 
cracks before each first flight of the day; amending the flight manual 
to reflect the pilot pre-flight check; within 25 flight hours, having 
the rear structure tube inspected for cracks by a mechanic; and, if any 
cracks are detected contacting ECD for approved corrective actions.
    On October 16, 2008, we issued EAD No. 2008-22-51 (EAD 2008-22-51) 
for the ECD Model EC135 helicopter. That EAD requires, before further 
flight and thereafter before the first flight of each day, visually 
inspecting the ring frame between the tailboom and fenestron housing 
for a crack, and replacing the ring frame with an airworthy ring frame 
if there is a crack. That EAD resulted from two reports of cracks on 
the ring frame connecting the tail rotor fenestron housing to the 
tailboom. The first crack was discovered in Germany and is discussed in 
EAD 2008-0190-E. The second crack, which was 9 inches long, was 
discovered in the U.S. and was in the same area as the first reported 
crack. We issued EAD 2008-22-51 to detect a crack in the ring frame, 
which could result in loss of the fenestron structure and subsequent 
loss of control of the helicopter.

Actions Since Existing EAD Was Issued

    Since we issued EAD 2008-22-51, EASA issued AD No.: 2009-0065, 
dated March 13, 2009 (AD 2009-0065), which supersedes EAD 2008-0190-E. 
AD 2009-0065 retains the requirements of EAD 2008-0190-E, expands the 
applicability to EC 135 helicopters manufactured in Spain, and adds a 
repetitive 100-hour inspection of the rear fuselage structure area for 
cracks.
    EASA next issued AD No.: 2009-0065R1, dated September 8, 2009 (AD 
2009-0065R1), which revises AD 2009-0065. EASA advises that ECD has 
developed a modification (reinforcement) of the aft ring frame, 
including a part number (P/N) change, for both production and in-
service application. Consequently, AD 2009-0065R1 retains the 
inspection requirements of AD 2009-0065 but limits its applicability to 
helicopters without the reinforced aft ring frame installed, and allows 
installation of the reinforced aft ring frame as an optional 
terminating action for the repetitive checks and inspections.
    EASA then issued AD No.: 2010-0254, dated December 20, 2010 (AD 
2010-0254), which supersedes AD 2009-0065R1. AD 2010-0254 retains the 
repetitive inspection requirements of AD 2009-0065R1, but reduces the 
interval of the visual inspection from 100 hours to 25 hours and 
requires installation of the reinforced aft ring frame within 12 months 
as terminating action for the repetitive checks and inspections.
    Since we issued EAD 2008-22-51, we have determined that a pre-
flight pilot check in conjunction with a recurring 25-hour inspection 
is sufficient for determining the airworthiness of the ring frame. 
Therefore, we are issuing this AD to revise the inspection 
requirements, as well as allow for the optional terminating action 
developed by ECD.

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, their technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition is 
likely to exist or develop on other helicopters of these same type 
designs.

Related Service Information

    We reviewed ECD Emergency Alert Service Bulletin (ASB) EC135-53A-
022, Revision 02, dated November 30, 2010 (ASB EC135-53A-022). ASB 
EC135-53A-022 describes procedures for a pilot check of the ring frame 
during the preflight check. ASB EC135-53A-022 additionally prescribes a 
recurring inspection of the ring frame every 25 flight hours and 
accomplishment of ECD Service Bulletin EC135-53-023, as corrected 
November 13, 2009 (SB EC135-53-023), which describes procedures to 
attach a frame reinforcement to the ring frame. The correction 
coversheet attached to SB EC135-53-023 is dated November 13, 2009; it 
describes the correction on page 6 of the service bulletin. All pages 
of the corrected service bulletin show the original issue date of 
August 19, 2009; the date has been underlined on page 6 of the 
corrected service bulletin. Accomplishment of SB EC135-53-023 
constitutes terminating action for the visual inspection requirements 
of ASB EC135-53A-022.

AD Requirements

    This AD supersedes EAD 2008-22-51 and requires the following:
    <bullet> Before further flight, and thereafter at each preflight 
check, performing a visual check of the ring frame which connects the 
tail rotor Fenestron housing to the tailboom for a crack. An owner/
operator (pilot) may perform this check because it involves only a 
visual check for a crack in the ring frame and can be performed equally 
well by a pilot or a mechanic.
    <bullet> Within 25 hours time-in-service (TIS), and every 25 hours 
TIS thereafter, removing the tail rotor drive shaft paneling and 
inspecting the ring frame for a crack.
    <bullet> As an optional terminating action for the requirements of 
this AD, installing a frame reinforcement to the ring frame and re-
identifying the ring frame by following specified portions of the 
manufacturer's service bulletin.

[[Page 37792]]

Differences Between This AD and the EASA AD

    This AD differs from the EASA AD as follows:
    <bullet> The EASA AD requires amendment of the Flight Manual with a 
page from ASB EC135-53A-022. Following issuance of the EASA AD, a 
revision has been published for the Flight Manuals and the amended 
pages are no longer issued with ASB EC135-53A-022. Therefore, this AD 
does not require this.
    <bullet> The EASA AD requires modification of the aft ring frame 
within 12 months as terminating action; this AD provides it as an 
optional terminating action.
    <bullet> The EASA AD applies to the Model EC 635 helicopter, and 
this AD does not include this model because it does not have an FAA-
issued type certificate.
    <bullet> The EASA AD includes a ``tolerance'' range for 
accomplishment of the pilot check and visual inspections. This AD does 
not allow this.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring the installation of the ECD-developed ring frame modification 
as terminating action for the repetitive inspection requirements of 
this AD. However, the planned compliance time for the installation of 
the modification would allow enough time to provide notice and 
opportunity for prior public comment on the merits of the modification.

Costs of Compliance

    We estimate that this AD will affect 226 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. Inspecting the ring frame requires .5 
work-hour at an average labor rate of $85 per hour, for a cost per 
inspection cycle of $42.50 per helicopter, and a cost to the fleet of 
$9,605. Replacing a cracked ring frame will require about 8 work hours 
at an average labor rate of $85 per hour, and a parts cost of $7,425, 
for a total cost per helicopter of $8,105. Modifying and re-identifying 
the ring frame requires 17 work-hours and a parts cost of $1,320, for a 
total cost per helicopter of $2,765 and the cost to the fleet is 
$624,890.
    According to the manufacturer, they will cover all parts costs for 
a cracked ring frame, thereby reducing the cost impact on affected 
persons. However, as we do not control such coverage by the 
manufacturer, we have included all costs in our cost estimate.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because some of the required checks 
and inspections must be accomplished before further flight.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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 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, 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this 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.

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 adding the following new airworthiness 
directive (AD):

2012-11-02 Eurocopter Deutschland GmbH: Amendment 39-17065; Docket 
No. FAA-2012-0566; Directorate Identifier 2011-SW-008-AD.

(a) Applicability

    This AD applies to Model EC135 helicopters with a ring frame, 
part number (P/N) L535A3501230, installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the ring 
frame connecting the rear structure tube (tailboom) and the tail 
rotor fenestron housing. This condition could result in loss of the 
fenestron structure and subsequent loss of control of the 
helicopter.

(c) Other Affected ADs

    This AD supersedes Emergency AD 2008-22-51, dated October 16, 
2008.

(d) Effective Date

    This AD becomes effective July 10, 2012.

(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 before the first 
flight of the day, visually check the ring frame that connects the 
tail rotor fenestron housing to the tailboom for a crack. This 
action 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 91.173, 121.380, or 135.439.

[[Page 37793]]

    (2) Within 25 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 25 hours TIS, remove the tail rotor 
driveshaft paneling and visually inspect the ring frame for a crack.
    (3) While performing a check or an inspection as required in 
paragraph (f)(1) or (f)(2) of this AD, paint cracks around the rivet 
heads and in the transition area between the tailboom and ring frame 
or between the ring frame and fenestron housing may be present and 
do not create an unsafe condition. If you are unable to determine 
whether a crack is on the paint or on the ring frame, you must 
remove the paint to do an accurate inspection.
    (4) If there is a crack in the ring frame, before further 
flight, replace it with an airworthy ring frame.
    (5) As an optional terminating action for the requirements of 
this AD, you may install a frame reinforcement to the ring frame and 
re-identify the ring frame in accordance with the Accomplishment 
Instructions, paragraph 3.B. of Eurocopter EC135 Service Bulletin 
EC135-53-023, as corrected on November 13, 2009, except you are not 
required to contact ECD as noted under paragraphs 3.B.(3) Caution 
and 3.B.(8).

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Sharon Miles, Aerospace 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
2601 Meacham Blvd., Fort Worth, Texas 76137; phone (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 Emergency Alert Service Bulletin (ASB) EC135-53A-
022, Revision 02, dated November 30, 2010, which is not incorporated 
by reference, contains additional information about the subject of 
this AD. For service information identified in this 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 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 European Aviation 
Safety Agency AD No. 2010-0254, dated December 20, 2010.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft 
Tailboom.

(k) 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 EC135 Service Bulletin EC135-53-023, as corrected 
on November 13, 2009. The correction coversheet attached to this 
document is dated November 13, 2009; it describes the correction on 
page 6 of the service bulletin. All pages of the corrected service 
bulletin show the original issue date of August 19, 2009. On page 6 
of the corrected service bulletin the date has been underlined.
    (ii) Reserved.
    (3) For Eurocopter service information identified in this 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.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.
    (5) You may also view this service information 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on May 22, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-15290 Filed 6-22-12; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:01:41.290658+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

566247502ca7738181fe24ba4e316f41e9653fbcf0a009e3079b7464e54322ab

Text SHA-256

3adba881a78ce88abae53f922633537bf558452980bf4e6edd2a56ff60bccd7c