AD 2014-04282

[Federal Register Volume 79, Number 49 (Thursday, March 13, 2014)]
[Rules and Regulations]
[Pages 14169-14174]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-04282]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1158; Directorate Identifier 2010-SW-018-AD; 
Amendment 39-17765; AD 2011-22-05 R1]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held By Eurocopter France) (Airbus Helicopters)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are revising Airworthiness Directive (AD) 2011-22-05 for 
Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, BA, C, D, D1, 
AS355E, F, F1, F2, N, and NP helicopters with certain tail rotor (T/R) 
pitch control rods (control rods) installed. AD 2011-22-05 required 
checking the control rod for play before the first flight of each day. 
This new AD requires checking the control rod for play within 30 hours 
time-in-service (TIS) and, if no bearing play is detected, thereafter 
at intervals not to exceed 30 hours TIS. The actions in this AD are 
intended to prevent failure of a T/R control rod, loss of T/R control, 
and subsequent loss of control of the helicopter.

DATES: This AD is effective April 17, 2014.

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 
<a href="http://www.airbushelicopters.com/techpub">http://www.airbushelicopters.com/techpub</a>. You may view this 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> in Docket No. FAA-2011-1158 or in person at the 
Docket Management Facility 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 information, the economic evaluation, any comments received, 
and other information. The address for the Docket Office (phone: 800-
647-5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#1e6c717c7b6c6a30796c7f706a5e787f7f30797168"><span class="__cf_email__" data-cfemail="25574a474057510b4257444b51654344440b424a53">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to revise AD 2011-22-05, Amendment 39-16847 (76 FR 70046, 
November 10, 2011). AD 2011-22-05 applied to Eurocopter Model AS350B, 
B1, B2, B3, BA, C, D, D1; and Model AS355E, F, F1, F2, N, and NP 
helicopters with T/R control rod, part number (P/N) 350A33-2100-00, -
01, -02, -03, -04; P/N 350A33-2121-00, -01, -02; P/N 350A33-2143-00; or 
P/N 350A33-2145-00 or -01, installed. AD 2011-22-05 required checking 
the control rod for play before the first flight of each day. The NPRM, 
published in the Federal Register on September 26, 2013 (78 FR 59298), 
proposed to extend the required time to check control rod play to 
within 30 hours TIS and, if no bearing play is detected, thereafter at 
intervals not to exceed 30 hours TIS.
    The NPRM was based on our determination that we can safely extend 
the compliance time for the initial bearing play check and the interval 
for recurring checks. We also clarified the requirements of that check 
and removed a previous requirement that if the Teflon cloth is coming 
out of its normal position within the bearing, or if there is 
discoloration or scoring on the bearing, that the control rod be 
replaced with an airworthy rod before further flight. These actions are 
intended to prevent failure of a control rod, loss of T/R control, and 
subsequent loss of control of the helicopter.
    Since we issued the NPRM, Eurocopter France has changed its name to 
Airbus Helicopters. This AD reflects that change and updates the 
contact information to obtain service documentation.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (78 FR 59298, 
September 26, 2013).

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

[[Page 14170]]

proposed except for the minor change previously described. This change 
is consistent with the intent of the proposals in the NPRM (78 FR 
59298, September 26, 2013) and will not increase the economic burden on 
any operator nor increase the scope of the AD.

Related Service Information

    Eurocopter issued Alert Service Bulletin (ASB) No. 05.00.60 for the 
Model AS350 series helicopters, and ASB No. 05.00.56 for the Model 
AS355 series helicopters, both Revision 0, and both dated December 9, 
2009. These ASBs specify performing an initial and recurring check for 
play in the pitch-change links. If axial play in the ball-joint is 
detectable, the ASBs specify removing the pitch-change link and 
measuring the bearing wear using a dial indicator. EASA classified 
these ASBs as mandatory and issued EASA AD No. 2010-0006, dated January 
7, 2010, to ensure the continued airworthiness of these helicopters.

Costs of Compliance

    We estimate that this AD affects 936 helicopters of U.S. Registry. 
We estimate, per helicopter, it will take minimal work-hours to do the 
check, 1 work-hour to measure the bearing play, and 1 work-hour to 
replace 1 control rod. The average labor rate is $85 per work-hour. 
Required parts cost about $1,724 to replace a control rod per 
helicopter. Based on these figures, we estimate the cost of this AD on 
U.S. operators is minimal for the check. Measuring the bearing play, if 
needed, costs $85 per helicopter, and replacing 1 control rod costs 
$1,809 per helicopter.

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 have 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 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, 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.

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 removing Airworthiness Directive (AD) 
2011-22-05, Amendment 39-16847 (76 FR 70046, November 10, 2011), and 
adding the following new AD:

2011-22-05 R1 Airbus Helicopters (Type Certificate Previously Held 
by Eurocopter France) (Airbus Helicopters): Amendment 39-17765; 
Docket No. FAA-2011-1158; Directorate Identifier 2010-SW-018-AD.

(a) Applicability

    This AD applies to Airbus Model AS350B, B1, B2, B3, BA, C, D, 
D1; and Model AS355E, F, F1, F2, N, and NP helicopters; with tail 
rotor (T/R) pitch control rod (control rod), part number (P/N) 
350A33-2100-00, -01, -02, -03, -04; P/N 350A33-2121-00, -01, -02; P/
N 350A33-2143-00; or P/N 350A33-2145-00 or -01, installed; 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as excessive play in the 
control rod. This condition could result in failure of a T/R control 
rod, loss of T/R control, and subsequent loss of control of the 
helicopter.

(c) Affected ADs

    This AD revises AD 2011-22-05, Amendment 39-16847 (76 FR 70046, 
November 10, 2011).

(d) Effective Date

    This AD becomes effective April 17, 2014.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Within 30 hours time-in-service (TIS) and, if no bearing 
play is detected, thereafter at intervals not to exceed 30 hours 
TIS, place the T/R pedals in the neutral position. If the helicopter 
is fitted with a T/R load compensator, discharge the accumulator as 
described in the rotorcraft flight manual. Check the control rod 
bearing (bearing) for play on the helicopter, by observation and 
feel, by slightly moving the T/R blade in the flapping axis while 
monitoring the bearing for movement. See the following Figure 1 to 
Paragraph (f) of this AD. The actions required by this paragraph may 
be performed by the owner/operator (pilot) holding at least a 
private pilot certificate, and must be entered into the helicopter 
maintenance records showing compliance with this AD in accordance 
with 14 CFR 43.9(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record 
must be maintained as required by 14 CFR 91.417, 121.380, or 
135.439.
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[[Page 14171]]

[GRAPHIC] [TIFF OMITTED] TR13MR14.000

    (2) If a pilot or mechanic detects play in the bearing, before 
the next flight, a mechanic must remove the control rod from the 
helicopter, and using a dial indicator, measure the bearing wear 
according to the following and as shown in Figures 2 and 3 to 
Paragraph (f) of this AD:

[[Page 14172]]

[GRAPHIC] [TIFF OMITTED] TR13MR14.001


[[Page 14173]]


[GRAPHIC] [TIFF OMITTED] TR13MR14.002

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    (i) Remove the control rod from the helicopter.
    (ii) Mount the control rod in a vise as shown in Figure 2 to 
Paragraph (f) of this AD.
    (iii) Using a dial indicator, take axial play readings by moving 
the spherical bearing in the direction F (up and down) as shown in 
Figure 2 to Paragraph (f) of this AD.
    (iv) Install a bolt through the bearing and secure it with a 
washer and nut to provide a clamping surface when the bearing is 
clamped in a vise.
    (v) Mount the control rod and bearing in a vise as shown in 
Figure 3 to Paragraph (f) of this AD.
    (vi) Using a dial indicator, take radial play measurements by 
moving the control rod in the direction F as shown in Figure 3 to 
Paragraph (f) of this AD.
    (vii) Record the hours of operation on each control rod.
    (viii) If the radial play exceeds 0.008 inch or axial play 
exceeds 0.016 inch, replace the control rod with an airworthy 
control rod before further flight.
    (ix) If the radial and axial play are within limits, reinstall 
the control rod.
    (x) Thereafter, at intervals not to exceed 30 hours TIS, remove 
the control rod and measure the bearing play with a dial indicator 
in accordance with paragraph (f)(2) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5110; email 
<a href="/cdn-cgi/l/email-protection#cebca1acabbcbae0a9bcafa0ba8ea8afafe0a9a1b8"><span class="__cf_email__" data-cfemail="f88a979a9d8a8cd69f8a99968cb89e9999d69f978e">[email&#160;protected]</span></a>.
    (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.

(h) Additional Information

    (1) Eurocopter Alert Service Bulletin (ASB) No. 05.00.60 and ASB 
No. 05.00.56, both Revision 0, and both dated December 9, 2009, 
which are not incorporated by reference, contain additional 
information about the subject of this AD. 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 <a href="http://www.airbushelicopters.com/techpub">http://www.airbushelicopters.com/techpub</a>. 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 the European Aviation 
Safety Agency (EASA) AD No. 2010-0006, dated January 7, 2010. You 
may view the EASA AD on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 
in Docket No. FAA-2011-1158.

[[Page 14174]]

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6720, Tail rotor 
control system.

    Issued in Fort Worth, Texas, on January 31, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-04282 Filed 3-12-14; 8:45 am]
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