[Federal Register Volume 78, Number 84 (Wednesday, May 1, 2013)]
[Rules and Regulations]
[Pages 25365-25367]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-09436]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0951; Directorate Identifier 2007-SW-52-AD;
Amendment 39-17437; AD 2013-08-19]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and
AS355N helicopters. This AD requires visual and dye penetrant
inspections for cracks in the rear roller support shaft (shaft) and
rear fitting (fitting) of the sliding door, and replacing the shaft or
fitting if there is a crack. This AD's actions are prompted by reports
of cracks in the shaft and the fitting and are intended to prevent the
loss of the sliding door, which could come into contact with the rotor
system, leading to damage to the helicopter and loss of helicopter
control.
DATES: This AD is effective June 5, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of June 5, 2013.
ADDRESSES: 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 the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
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, 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 October 22, 2009, at 74 FR 54501, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to Eurocopter Model
AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1,
AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters, with sliding
door pre-modification (MOD) 073298 or pre-MOD 073308, installed. The
NPRM proposed to require visual and dye
[[Page 25366]]
penetrant inspections of the shaft and fitting. If a crack exists in
the shaft or fitting, the NPRM proposed replacing the cracked parts
with airworthy parts. The proposed requirements were intended to
prevent the loss of the sliding door, which could come into contact
with the rotor system and lead to damage to the helicopter and loss of
helicopter control.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
No. 2007-0236, dated August 31, 2007, to correct an unsafe condition
for specified Eurocopter model helicopters. EASA issued AD 2006-0251
and its revisions following a case of total failure and a case of a
crack discovered on the support shaft of the sliding door rear roller.
Metallurgical and metallographic analyses revealed a nonconformity
concerning the heat treatment of the material. Since then, other cases
of cracks and failures of the roller support shaft rear attach fitting
had been reported. EASA AD No. 2007-0236 supersedes EASA AD No. 2006-
0251R2 but retains the requirements for repetitive inspections until
replacement of current parts with improved parts. EASA AD No. 2007-0236
also prohibits installation of another roller support fitting part
number (P/N) 350A25-1270-22 on any AS350 or AS355 helicopter.
Comments
After our NPRM (74 FR 54501, October 22, 2009) was published, we
received comments from one commenter.
Request
One commenter requested that our AD apply to only pre-modified
aircraft as stated in the applicability paragraph. We agree.
The commenter also requested a paragraph on terminating action once
an aircraft is ``modified to a post-mod status'' to avoid confusing an
owner/operator. We disagree with this request. If an aircraft becomes
modified according to modifications 073298 and 073308, the AD is clear
that the applicability paragraph no longer applies.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are 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 and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed, except we have revised the
estimated costs of complying with this AD to reflect labor costs of $85
per hour instead of $80 per hour.
Differences Between This AD and the EASA AD
This AD differs from EASA AD No. 2007-0236 as follows:
We use the word ``inspect'' to describe the actions
required by a mechanic. EASA uses the word ``check,'' which is how we
describe the actions we allow a pilot to complete.
We do not require an operator to tell the manufacturer if
a crack is found in the shaft.
We are not including the Model AS 350 BB, because that
model is not type certificated in the U.S. We are including Models
AS350C and AS350D1 helicopters.
Related Service Information
On July 18, 2006, Eurocopter issued Alert Service Bulletin (ASB)
No. 52.00.30 for modifying the AS350 series helicopters and ASB No.
52.00.23 for modifying the AS355 series helicopters. These ASBs
contained modifications 073298 and 073308. The following day,
Eurocopter issued ASB No. 05.00.45 for the AS355 model helicopters and
ASB No. 05.00.47 for the AS350 helicopters. On June 29, 2007,
Eurocopter issued Revision 1 to ASB No. 52.00.30 for the AS350 model
helicopters and ASB No. 52.00.23 for the AS355 model helicopters to
modify the sliding door medium roller pin and the fitting.
Costs of Compliance
We estimate that this AD will affect 725 helicopters of U.S.
Registry and that labor costs average $85 a work-hour. Based on these
estimates, we expect the following costs:
Inspecting and modifying the sliding doors will require about 4
work-hours for a labor cost of $340. Parts will cost about $7,000 for a
total cost of $7,340 per helicopter, and $5,321,500 for the U.S. fleet.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.
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):
[[Page 25367]]
2013-08-19 Eurocopter France Helicopters: Amendment 39-17437; Docket
No. FAA-2009-0951; Directorate Identifier 2007-SW-52-AD.
(a) Applicability
This AD applies to Eurocopter France (Eurocopter) Model AS350B,
BA, B1, B2, B3, C, D, D1, AS355E, F, F1, F2, and N helicopters, with
sliding door pre-modification (MOD) 073298 or pre-MOD 073308,
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the rear
roller support shaft (shaft) or the rear fitting (fitting) of the
sliding door. This condition could result in loss of the sliding
door, which could come into contact with the rotor system, leading
to damage to the helicopter and loss of helicopter control.
(c) Effective Date
This AD becomes effective June 5, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless accomplished
previously.
(e) Required Actions
(1) For a sliding door with less than 90 hours time-in-service
(TIS), on or before accumulating a total of 110 hours TIS, conduct
the visual and dye penetrant inspections of the shaft and the
fitting of the sliding door for a crack by reference to Figure 1 and
by following the Operational Procedure, paragraph 2.B.1 and 2.B.2,
of Eurocopter Alert Service Bulletin (ASB) No. 05.00.47 dated July
19, 2006, for the Model AS350 helicopters (ASB 05.00.47) or ASB No.
05.00.45 dated July 19, 2006, for the Model AS355 helicopters (ASB
05.00.45), except you are not required to contact the manufacturer.
(i) If no crack is found in the shaft or fitting, reinstall the
shaft on the fitting, fit the spring pins, and plug the pin holes by
following the Operational Procedure, paragraph 2.B.2. of ASB
05.00.47 or 05.00.45, whichever is appropriate for your model
helicopter.
(ii) If you find a crack in the fitting, replace the fitting
with an airworthy fitting before further flight.
(iii) If you find a crack in the shaft, replace the shaft with
an airworthy shaft before further flight by reference to Figure 1
and by following paragraph 2.B.3. of ASB 05.00.47 or 05.00.45,
whichever is appropriate for your model helicopter.
(2) For a sliding door with 90 or more hours TIS, within the
next 20 hours TIS, and thereafter at intervals not to exceed 110
hours TIS, conduct the visual and dye penetrant inspections of the
shaft and the fitting of the sliding door for a crack by reference
to Figure 1 and by following the Operational Procedure, paragraph
2.B.1 and 2.B.2, of ASB 05.00.47 or ASB 05.00.45, whichever is
appropriate for your model helicopter, except you are not required
to contact the manufacturer.
(i) If no crack is found in the shaft and fitting, reinstall the
shaft or fitting, fit the spring pins, and plug the pin holes by
following the Operational Procedure, paragraph 2.B.2. of ASB
05.00.47 or 05.00.45, whichever is appropriate for your model
helicopter.
(ii) If you find a crack in the fitting, replace the fitting
with an airworthy fitting before further flight.
(iii) If you find a crack in the shaft, replace the shaft with
an airworthy shaft before further flight by reference to Figure 1
and by following paragraph 2.B.3. of ASB 05.00.47 or 05.45,
whichever is appropriate for your model helicopter.
(3) After the effective date of this AD, do not install any of
the following parts on any helicopter:
(i) Left-hand sliding door, part number (P/N) 350A25-0030-00XX,
350A25-0120-00XX, and 350AMR-0227-0052;
(ii) Right-hand sliding door, P/N 350A25-0030-01XX, 350A25-0120-
01XX, 350A25-0120-03XX, and 350AMR-0227-0051;
(iii) Rail roller pin, P/N 350A25-1275-20; and
(iv) Cast roller support fittings, P/N 350A25-1270-20 and P/N
350A25-1270-22.
(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 AD No. 2007-0236, dated August 31, 2007.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 5344, Fuselage
Door Hinges.
(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 France Alert Service Bulletin No. 05.00.47,
Revision 0, dated July 19, 2006.
(ii) Eurocopter France Alert Service Bulletin No. 05.00.45,
Revision 0, dated July 19, 2006.
(3) For Eurocopter France 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 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 12, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-09436 Filed 4-30-13; 8:45 am]
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