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[Federal Register Volume 78, Number 84 (Wednesday, May 1, 2013)]
[Rules and Regulations]
[Pages 25365-25367]
From the Federal Register Online via the Government Printing 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 
gary.b.roach@faa.gov.

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 gary.b.roach@faa.gov.
    (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]
BILLING CODE 4910-13-P
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