80 FR 25589 - Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 86 (May 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 86 (May 5, 2015)
| Page Range | 25589-25591 | |
| FR Document | 2015-09548 |
[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)] [Rules and Regulations] [Pages 25589-25591] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-09548] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0038; Directorate Identifier 2013-SW-023-AD; Amendment 39-18146; AD 2015-09-01] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This AD requires repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD requires, before further flight, repairing or replacing the blade with an airworthy part. This AD was prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The actions of this AD are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter. DATES: This AD is effective June 9, 2015. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of June 9, 2015. ADDRESSES: For service information identified in this AD, contact Airbus Helicopters, Inc., 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 the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is also available on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0038. 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 European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647- 5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion On January 31, 2014, at 79 FR 5321, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters. The NPRM proposed to require repetitive visual and tap test inspections of each blade strip for a crack, cut, or debonding. If there is a crack or if there is debonding beyond acceptable limits or located outside a specific area, the NPRM proposed to require, before further flight, repairing or replacing the blade with an airworthy part. If there is a cut in the blade root polyurethane protective strip, the NPRM proposed to require tap test inspecting the blade for debonding. The proposed requirements were intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2013-0103, dated May 2, 2013, issued [[Page 25590]] by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Eurocopter (now Airbus Helicopters) Model EC225LP helicopters with certain blades installed. EASA advises that an investigation of significant debonding of a blade strip revealed rapidly progressing debonding caused by water seepage through a crack in the blade strip. EASA issued AD 2013-0103 requiring repetitive inspections of the blade strip to correct this condition. Comments After our NPRM (79 FR 5321, January 31, 2014) was published, we received comments from 2 commenters. Request Two commenters requested that a helicopter be allowed to operate with a crack in the leading edge blade strip as long as the crack is within the limits prescribed by the manufacturer. The commenters stated that EASA and the manufacturer allow for a helicopter to fly if the blade strip has a crack that is within limits because the blade strip is sacrificial and nonstructural. The commenters state that requiring repairing or replacing the blade strip if there is a crack results in a higher cost and greater out-of-service time for operators without a justifiable or measured increase in safety. We agree with allowing a crack in the blade strip that is within limits and has been properly sealed. Therefore, we have changed paragraph (e)(5) of the AD to require sealing the crack instead of repairing or replacing the blade if there is a crack within acceptable limits. 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, EASA, its 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, 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 with the change described previously. This change is consistent with the intent of the proposals in the NPRM (79 FR 5321, January 31, 2014) and will not increase the economic burden on any operator nor increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Eurocopter issued Emergency Alert Service Bulletin No. 05A010, Revision 2, dated April 22, 2013 (EASB), for the Model EC225LP helicopter and for the non-FAA typed certificated Model EC725AP military helicopter. The EASB specifies a visual check and tapping test of the bonding of the strip on the leading edge of the blades for cracks, cuts, and debonding and taking corrective actions as applicable. Revision 1 to the EASB changed the visual check and the tapping test so that they can be performed without removing the blades. Revision 2 extended the applicability to additional part-numbered blades with a modified blade strip installed. This information is reasonably available at http://www.regulations.gov in Docket No. FAA- 2014-0038. Or see ADDRESSES for other ways to access this service information. Costs of Compliance We estimate that this AD affects 4 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work hour. We estimate 4 work hours to inspect the helicopter for a total of $340 per helicopter and $1,360 for the U.S. operator fleet per inspection cycle. If necessary, it will take 4 work hours to repair the blade and $600 for required parts for a total of $940 per helicopter. It will take about 5 work hours to replace a blade at a cost of $425 for labor. Parts will cost $315,495 to replace part number (P/N) 332A11-0050-01 and $403,650 to replace P/N 332A11-0055-00, for a total cost of $315,920 and $404,075, respectively. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866; (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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): 2015-09-01 Airbus Helicopters (Type Certificate previously held by Eurocopter France): Amendment 39-18146, Docket No. FAA-2014-0038, Directorate Identifier 2013-SW-023-AD. (a) Applicability This AD applies to Model EC225LP helicopters with a main rotor blade (blade), part number 332A11.0050.00, 332A11.0055.00, 332A11.0050.02, or 332A11.0055.02, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as loss of a blade stainless steel protective strip (strip), which could result in excessive vibrations induced by blade weight imbalance and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective June 9, 2015. (d) 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. (e) Required Actions Within 15 hours time-in-service (TIS) and thereafter at intervals not to exceed 85 hours TIS, visually and tap test inspect each blade strip for a crack, a cut, or open and blind debonding. For purposes of this AD, open debonding, also known as edge bond separation, occurs when a bonded part becomes unattached (debonded) leaving the surface under it exposed to open air around the periphery of the part. Blind debonding occurs when a bonded part becomes unattached internally yet remains bonded around its entire periphery. [[Page 25591]] (1) If there is open or blind debonding within acceptable limits and the debonded area is located inside Area D of Figure 1 of Eurocopter Emergency Alert Service Bulletin No. 05A010, Revision 2, dated April 22, 2013 (EASB), no further action is required until the next inspection. (2) If there is open or blind debonding and the debonded area is located outside Area D of Figure 1 of the EASB, before further flight, repair or replace the blade. (3) If there is open or blind debonding beyond acceptable limits, before further flight, repair or replace the blade. (4) If there is a cut in the blade root polyurethane protective strip as depicted in Area A of Figure 2 of the EASB, tap test inspect the area. (i) If there is no open and blind debonding, at intervals not to exceed 15 hours TIS, tap test inspect the blade strip in the blade root area, in the stainless steel leading edge/neoprene junction area for open or blind debonding. (ii) If there is open or blind debonding within acceptable limits and the debonded area is located inside Area D of Figure 1 of the EASB, no further action is required until the next inspection. (iii) If there is open or blind and the debonded area is located outside Area D of Figure 1 of the EASB, before further flight, repair or replace the blade. (iv) If there is open or blind debonding beyond acceptable limits, before further flight, repair or replace the blade. (5) If there is a crack within acceptable limits, before further flight, seal the crack. If there is a crack beyond the acceptable limits, before further flight, repair or replace the blade. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222- 5110; email [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. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013-0103, dated May 2, 2013. You may view the EASA AD on the Internet at www.regulations.gov in Docket No. FAA- 2014-0038. (h) Subject Joint Aircraft Service Component (JASC) Code: 6210 Main Rotor Blades. (i) 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 Emergency Alert Service Bulletin No. 05A010, Revision 2, dated April 22, 2013. (ii) Reserved. (3) For service information identified in this AD, contact Airbus Helicopters, Inc., 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, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on April 16, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-09548 Filed 5-4-15; 8:45 am] BILLING CODE 4910-13-P
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statements, and documents at such the Recipient with written notice of the Helicopters, Inc., 2701 N. Forum Drive,
times, in such forms, and accompanied proposed sanction and an opportunity Grand Prairie, TX 75052; telephone
by such supporting data, as required by to comment. Nothing in this section, (972) 641–0000 or (800) 232–0323; fax
the CDFI Fund and the U.S. Department however, shall provide a Recipient to (972) 641–3775; or at http://
of the Treasury to ensure compliance any formal or informal hearing or www.airbushelicopters.com/techpub.
with the requirements of this part. The comparable proceeding not otherwise You may review the referenced service
United States Government, including required by law. information at the FAA, Office of the
the U.S. Department of the Treasury, the Regional Counsel, Southwest Region,
Comptroller General, and its duly § 1806.504 Retention of records. 2601 Meacham Blvd., Room 663, Fort
authorized representatives, shall have A Recipient must comply with all Worth, Texas 76137. It is also available
full and free access to the Recipient’s record retention requirements as set on the Internet at http://
offices and facilities, and all books, forth in the Uniform Administrative www.regulations.gov in Docket No.
documents, records, and financial Requirements. FAA–2014–0038.
statements relevant to the award of the Dated: April 30, 2015. Examining the AD Docket
Federal funds and may copy such Mary Ann Donovan,
documents as they deem appropriate. You may examine the AD docket on
Director, Community Development Financial
(b) The Award Agreement provides the Internet at http://
Institutions Fund.
that the provisions of the Act, this part, www.regulations.gov or in person at the
[FR Doc. 2015–10433 Filed 5–4–15; 8:45 am]
and the Award Agreement are Docket Operations Office between 9
BILLING CODE 4810–70–P
enforceable under 12 U.S.C. 1818 of the a.m. and 5 p.m., Monday through
Federal Deposit Insurance Act by the Friday, except Federal holidays. The AD
Appropriate Federal Banking Agency, as docket contains this AD, the European
DEPARTMENT OF TRANSPORTATION Aviation Safety Agency (EASA) AD, any
applicable, and that any violation of
such provisions shall be treated as a incorporated-by-reference service
Federal Aviation Administration information, the economic evaluation,
violation of the Federal Deposit
Insurance Act. Nothing in this any comments received, and other
14 CFR Part 39 information. The street address for the
paragraph (b) precludes the CDFI Fund
from directly enforcing the Award [Docket No. FAA–2014–0038; Directorate Docket Operations Office (phone: 800–
Agreement as provided for under the Identifier 2013–SW–023–AD; Amendment 647–5527) is U.S. Department of
terms of the Act.
39–18146; AD 2015–09–01] Transportation, Docket Operations
(c) The CDFI Fund will notify the RIN 2120–AA64 Office, M–30, West Building Ground
Appropriate Federal Banking Agency Floor, Room W12–140, 1200 New Jersey
before imposing any sanctions on a Airworthiness Directives; Airbus Avenue SE., Washington, DC 20590.
Recipient that is examined by or subject Helicopters (Type Certificate FOR FURTHER INFORMATION CONTACT: Gary
to the reporting requirements of that Previously Held by Eurocopter France) Roach, Aviation Safety Engineer,
agency. The CDFI Fund will not impose Regulations and Policy Group,
AGENCY: Federal Aviation Rotorcraft Directorate, FAA, 2601
a sanction described in section Administration (FAA), DOT.
1806.500(b) if the Appropriate Federal Meacham Blvd., Fort Worth, Texas
ACTION: Final rule. 76137; telephone (817) 222–5110; email
Banking Agency, in writing, not later
than 30 calendar days after receiving SUMMARY: We are adopting a new gary.b.roach@faa.gov.
notice from the CDFI Fund: airworthiness directive (AD) for Airbus SUPPLEMENTARY INFORMATION:
(1) Objects to the proposed sanction; Model EC225LP helicopters. This AD Discussion
(2) Determines that the sanction requires repetitive visual and tap test
would: On January 31, 2014, at 79 FR 5321,
inspections of each main rotor blade
(i) Have a material adverse effect on the Federal Register published our
(blade) leading edge stainless steel
the safety and soundness of the notice of proposed rulemaking (NPRM),
protective strip (strip) for a crack, cut,
Recipient; or which proposed to amend 14 CFR part
or blind or open debonding 39 by adding an AD that would apply
(ii) Impede or interfere with an
(debonding), and taking approved to Airbus Helicopters. The NPRM
enforcement action against that
corrective measures. If there is a crack proposed to require repetitive visual
Recipient by the Appropriate Federal
or if there is debonding that exceeds and tap test inspections of each blade
Banking Agency;
acceptable limits, this AD requires, strip for a crack, cut, or debonding. If
(3) Proposes a comparable alternative
before further flight, repairing or there is a crack or if there is debonding
action; and
(4) Specifically explains: replacing the blade with an airworthy beyond acceptable limits or located
(i) The basis for the determination part. This AD was prompted by outside a specific area, the NPRM
under paragraph (c)(2) of this section suspected water seepage through a crack proposed to require, before further
and, if appropriate, provides in the blade strip resulting in significant flight, repairing or replacing the blade
documentation to support the debonding. The actions of this AD are with an airworthy part. If there is a cut
determination; and intended to prevent loss of the blade in the blade root polyurethane
(ii) How the alternative action strip, excessive vibrations induced by protective strip, the NPRM proposed to
suggested pursuant to paragraph (c)(3) blade weight imbalance, and subsequent require tap test inspecting the blade for
of this section would be as effective as loss of control of the helicopter. debonding. The proposed requirements
rljohnson on DSK3VPTVN1PROD with RULES
the sanction proposed by the CDFI Fund DATES: This AD is effective June 9, 2015. were intended to prevent loss of the
in securing compliance and deterring The Director of the Federal Register blade strip, excessive vibrations
future noncompliance. approved the incorporation by reference induced by blade weight imbalance, and
(d) Prior to imposing any sanctions of a certain document listed in this AD subsequent loss of control of the
pursuant to this section or an Award as of June 9, 2015. helicopter.
Agreement, the CDFI Fund shall, to the ADDRESSES: For service information The NPRM was prompted by AD No.
maximum extent practicable, provide identified in this AD, contact Airbus 2013–0103, dated May 2, 2013, issued
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by EASA, which is the Technical Agent Related Service Information Under 1 on a substantial number of small entities
for the Member States of the European CFR Part 51 under the criteria of the Regulatory
Union, to correct an unsafe condition Eurocopter issued Emergency Alert Flexibility Act.
for Eurocopter (now Airbus Helicopters) Service Bulletin No. 05A010, Revision We prepared an economic evaluation
Model EC225LP helicopters with certain 2, dated April 22, 2013 (EASB), for the of the estimated costs to comply with
blades installed. EASA advises that an Model EC225LP helicopter and for the this AD and placed it in the AD docket.
investigation of significant debonding of non-FAA typed certificated Model List of Subjects in 14 CFR Part 39
a blade strip revealed rapidly EC725AP military helicopter. The EASB
progressing debonding caused by water Air transportation, Aircraft, Aviation
specifies a visual check and tapping test
seepage through a crack in the blade safety, Incorporation by reference,
of the bonding of the strip on the
strip. EASA issued AD 2013–0103 Safety.
leading edge of the blades for cracks,
requiring repetitive inspections of the cuts, and debonding and taking Adoption of the Amendment
blade strip to correct this condition. corrective actions as applicable. Accordingly, under the authority
Comments Revision 1 to the EASB changed the delegated to me by the Administrator,
visual check and the tapping test so that the FAA amends 14 CFR part 39 as
After our NPRM (79 FR 5321, January they can be performed without follows:
31, 2014) was published, we received removing the blades. Revision 2
comments from 2 commenters. extended the applicability to additional PART 39—AIRWORTHINESS
Request part-numbered blades with a modified DIRECTIVES
blade strip installed. This information is
Two commenters requested that a reasonably available at http:// ■ 1. The authority citation for part 39
helicopter be allowed to operate with a www.regulations.gov in Docket No. continues to read as follows:
crack in the leading edge blade strip as FAA–2014–0038. Or see ADDRESSES for Authority: 49 U.S.C. 106(g), 40113, 44701.
long as the crack is within the limits other ways to access this service
prescribed by the manufacturer. The information. § 39.13 [Amended]
commenters stated that EASA and the ■ 2. The FAA amends § 39.13 by adding
Costs of Compliance
manufacturer allow for a helicopter to the following new airworthiness
fly if the blade strip has a crack that is We estimate that this AD affects 4 directive (AD):
within limits because the blade strip is helicopters of U.S. Registry. We estimate
that operators may incur the following 2015–09–01 Airbus Helicopters (Type
sacrificial and nonstructural. The Certificate previously held by
commenters state that requiring costs in order to comply with this AD. Eurocopter France): Amendment 39–
repairing or replacing the blade strip if Labor costs are estimated at $85 per 18146, Docket No. FAA–2014–0038,
there is a crack results in a higher cost work hour. We estimate 4 work hours to Directorate Identifier 2013–SW–023–AD.
and greater out-of-service time for inspect the helicopter for a total of $340
per helicopter and $1,360 for the U.S. (a) Applicability
operators without a justifiable or
operator fleet per inspection cycle. If This AD applies to Model EC225LP
measured increase in safety.
necessary, it will take 4 work hours to helicopters with a main rotor blade (blade),
We agree with allowing a crack in the part number 332A11.0050.00,
blade strip that is within limits and has repair the blade and $600 for required
332A11.0055.00, 332A11.0050.02, or
been properly sealed. Therefore, we parts for a total of $940 per helicopter. 332A11.0055.02, installed, certificated in any
have changed paragraph (e)(5) of the AD It will take about 5 work hours to category.
to require sealing the crack instead of replace a blade at a cost of $425 for
labor. Parts will cost $315,495 to replace (b) Unsafe Condition
repairing or replacing the blade if there
part number (P/N) 332A11–0050–01 and This AD defines the unsafe condition as
is a crack within acceptable limits. loss of a blade stainless steel protective strip
$403,650 to replace P/N 332A11–0055–
FAA’s Determination 00, for a total cost of $315,920 and (strip), which could result in excessive
vibrations induced by blade weight
This helicopter has been approved by $404,075, respectively. imbalance and subsequent loss of control of
the aviation authority of France and is Regulatory Findings the helicopter.
approved for operation in the United This AD will not have federalism (c) Effective Date
States. Pursuant to our bilateral implications under Executive Order This AD becomes effective June 9, 2015.
agreement with France, EASA, its 13132. This AD will not have a
technical representative, has notified us (d) Compliance
substantial direct effect on the States, on
of the unsafe condition described in the the relationship between the national You are responsible for performing each
EASA AD. We are issuing this AD government and the States, or on the action required by this AD within the
because we evaluated all information specified compliance time unless it has
distribution of power and already been accomplished prior to that time.
provided by EASA, reviewed the responsibilities among the various
relevant information, considered the levels of government. (e) Required Actions
comments received, and determined the For the reasons discussed above, I Within 15 hours time-in-service (TIS) and
unsafe condition exists and is likely to certify that this AD: thereafter at intervals not to exceed 85 hours
exist or develop on other helicopters of (1) Is not a ‘‘significant regulatory TIS, visually and tap test inspect each blade
this same type design and that air safety action’’ under Executive Order 12866; strip for a crack, a cut, or open and blind
and the public interest require adopting (2) Is not a ‘‘significant rule’’ under debonding. For purposes of this AD, open
rljohnson on DSK3VPTVN1PROD with RULES
the AD requirements as proposed with debonding, also known as edge bond
DOT Regulatory Policies and Procedures
the change described previously. This separation, occurs when a bonded part
(44 FR 11034, February 26, 1979); becomes unattached (debonded) leaving the
change is consistent with the intent of (3) Will not affect intrastate aviation surface under it exposed to open air around
the proposals in the NPRM (79 FR 5321, in Alaska to the extent that it justifies the periphery of the part. Blind debonding
January 31, 2014) and will not increase making a regulatory distinction; and occurs when a bonded part becomes
the economic burden on any operator (4) Will not have a significant unattached internally yet remains bonded
nor increase the scope of this AD. economic impact, positive or negative, around its entire periphery.
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(1) If there is open or blind debonding (IBR) of the service information listed in this address the unsafe condition on these
within acceptable limits and the debonded paragraph under 5 U.S.C. 552(a) and 1 CFR products.
area is located inside Area D of Figure 1 of part 51.
Eurocopter Emergency Alert Service Bulletin (2) You must use this service information DATES: This AD is effective May 26,
No. 05A010, Revision 2, dated April 22, 2013 as applicable to do the actions required by 2015.
(EASB), no further action is required until this AD, unless the AD specifies otherwise. The Director of the Federal Register
the next inspection. (i) Eurocopter Emergency Alert Service approved the incorporation by reference
(2) If there is open or blind debonding and Bulletin No. 05A010, Revision 2, dated April of a certain publication listed in the AD
the debonded area is located outside Area D 22, 2013. as of May 26, 2015.
of Figure 1 of the EASB, before further flight, (ii) Reserved. We must receive comments on this
repair or replace the blade. (3) For service information identified in
(3) If there is open or blind debonding
AD by June 19, 2015.
this AD, contact Airbus Helicopters, Inc.,
beyond acceptable limits, before further 2701 N. Forum Drive, Grand Prairie, TX ADDRESSES: You may send comments by
flight, repair or replace the blade. 75052; telephone (972) 641–0000 or (800) any of the following methods:
(4) If there is a cut in the blade root 232–0323; fax (972) 641–3775; or at http:// • Federal eRulemaking Portal: Go to
polyurethane protective strip as depicted in www.airbushelicopters.com/techpub. http://www.regulations.gov. Follow the
Area A of Figure 2 of the EASB, tap test (4) You may view this service information instructions for submitting comments.
inspect the area. at FAA, Office of the Regional Counsel, • Fax: (202) 493–2251.
(i) If there is no open and blind debonding, Southwest Region, 2601 Meacham Blvd., • Mail: U.S. Department of
at intervals not to exceed 15 hours TIS, tap Room 663, Fort Worth, Texas 76137. For
test inspect the blade strip in the blade root
Transportation, Docket Operations, M–
information on the availability of this 30, West Building Ground Floor, Room
area, in the stainless steel leading edge/ material at the FAA, call (817) 222–5110.
neoprene junction area for open or blind (5) You may view this service information
W12–140, 1200 New Jersey Avenue SE.,
debonding. that is incorporated by reference at the Washington, DC 20590.
(ii) If there is open or blind debonding National Archives and Records • Hand Delivery: U.S. Department of
within acceptable limits and the debonded Administration (NARA). For information on Transportation, Docket Operations, M–
area is located inside Area D of Figure 1 of the availability of this material at NARA, call 30, West Building Ground Floor, Room
the EASB, no further action is required until (202) 741–6030, or go to: http:// W12–140, 1200 New Jersey Avenue SE.,
the next inspection. www.archives.gov/federal-register/cfr/ibr- Washington, DC 20590, between 9 a.m.
(iii) If there is open or blind and the locations.html.
debonded area is located outside Area D of and 5 p.m., Monday through Friday,
Figure 1 of the EASB, before further flight, Issued in Fort Worth, Texas, on April 16, except Federal holidays.
repair or replace the blade. 2015. For service information identified in
(iv) If there is open or blind debonding Lance T. Gant, this AD, contact Solo Kleinmotoren
beyond acceptable limits, before further Acting Directorate Manager, Rotorcraft GmbH, Postfach 600152, 71050
flight, repair or replace the blade. Directorate, Aircraft Certification Service. Sindelfingen, Germany; telephone: +49
(5) If there is a crack within acceptable 7031 301–0; fax: +49 7031 301–136;
[FR Doc. 2015–09548 Filed 5–4–15; 8:45 am]
limits, before further flight, seal the crack. If email: aircraft@solo-germany.com;
there is a crack beyond the acceptable limits, BILLING CODE 4910–13–P
before further flight, repair or replace the
Internet: http://aircraft.solo-online.com/
blade. com. You may review copies of the
DEPARTMENT OF TRANSPORTATION referenced service information at the
(f) Alternative Methods of Compliance FAA, Small Airplane Directorate, 901
(AMOCs) Federal Aviation Administration Locust, Kansas City, Missouri 64106.
(1) The Manager, Safety Management For information on the availability of
Group, FAA, may approve AMOCs for this 14 CFR Part 39 this material at the FAA, call (816) 329–
AD. Send your proposal to: Gary Roach,
[Docket No. FAA–2015–1130; Directorate
4148. It is also available on the Internet
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA, Identifier 2015–CE–008–AD; Amendment at http://www.regulations.gov by
2601 Meacham Blvd., Fort Worth, Texas 39–18150; AD 2015–09–04] searching for locating Docket No. FAA–
76137; telephone (817) 222–5110; email 2015–1130.
gary.b.roach@faa.gov. RIN 2120–AA64
(2) For operations conducted under a 14
Examining the AD Docket
CFR part 119 operating certificate or under Airworthiness Directives; DG You may examine the AD docket on
14 CFR part 91, subpart K, we suggest that Flugzeugbau GmbH Gliders the Internet at http://
you notify your principal inspector, or www.regulations.gov by searching for
lacking a principal inspector, the manager of AGENCY: Federal Aviation
Administration (FAA), DOT. and locating Docket No. FAA–2015–
the local flight standards district office or
certificate holding district office, before ACTION: Final rule; request for comments
1130 or in person at the Docket
operating any aircraft complying with this Management Facility between 9 a.m.
AD through an AMOC. SUMMARY: We are adopting a new and 5 p.m., Monday through Friday,
airworthiness directive (AD) for DG except Federal holidays. The AD docket
(g) Additional Information
Flugzeugbau GmbH Model DG–1000T contains this AD, the regulatory
The subject of this AD is addressed in evaluation, any comments received, and
gliders equipped with a Solo
European Aviation Safety Agency (EASA) AD other information. The street address for
No. 2013–0103, dated May 2, 2013. You may Kleinmotoren Model 2350 C engine that
view the EASA AD on the Internet at supersedes AD 2013–22–14 R1. This AD the Docket Office (telephone (800) 647–
www.regulations.gov in Docket No. FAA– results from mandatory continuing 5527) is in the ADDRESSES section.
2014–0038. airworthiness information (MCAI) Comments will be available in the AD
rljohnson on DSK3VPTVN1PROD with RULES
issued by the aviation authority of docket shortly after receipt.
(h) Subject
another country to identify and correct FOR FURTHER INFORMATION CONTACT: Jim
Joint Aircraft Service Component (JASC) an unsafe condition on an aviation Rutherford, Aerospace Engineer, 901
Code: 6210 Main Rotor Blades.
product. The MCAI describes the unsafe Locust, Room 301, Kansas City,
(i) Material Incorporated by Reference condition as engine shaft failure with Missouri 64106; telephone: (816) 329–
(1) The Director of the Federal Register consequent propeller detachment. We 4165; fax: 98160 329–4090; email:
approved the incorporation by reference are issuing this AD to require actions to jim.rutherford@faa.gov.
VerDate Sep<11>2014 15:13 May 04, 2015 Jkt 235001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\05MYR1.SGM 05MYR1](https://thefederalregister.org/doc/80_FR_25675/page/3.svg)
Document Created: 2015-12-16 07:53:34
Document Modified: 2015-12-16 07:53:34
| 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 June 9, 2015. | |
| 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] | |
| FR Citation | 80 FR 25589 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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