Document ID: FAA-2011-1158-0007
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Eurocopter France Helicopters
Posted Date: 2013-09-26T04:00Z

[Federal Register Volume 78, Number 187 (Thursday, September 26, 2013)]
[Proposed Rules]
[Pages 59298-59303]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23434]

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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]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to revise 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 
pitch control rods installed. AD 2011-22-05 currently requires, before 
the first flight of each day, checking the tail rotor (T/R) pitch 
control rod (control rod) outboard spherical bearing (bearing) for 
play. If play exists, AD 2011-22-05 requires measuring the bearing's 
radial and axial play. Since we issued AD 2011-22-05, we have 
determined that we can safely extend the compliance time to perform the 
initial and recurring checks for bearing play. The proposed actions are 
intended to prevent failure of a control rod, loss of T/R control, and 
subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by November 25, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     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.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5

[[Page 59299]]

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 proposed AD, the foreign 
authority's 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 proposed 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 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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On October 12, 2011, we issued AD 2011-22-05, Amendment 39-16847 
(76 FR 70046, November 10, 2011) for Eurocopter Model AS350B, B1, B2, 
B3, BA, C, D, D1, AS355E, F, F1, F2, N, and NP helicopters with certain 
T/R control rods installed. AD 2011-22-05 requires the following 
actions:
     Before the first flight of each day, checking the control 
rod bearing for play on the helicopter, by observation and feel, by 
slightly moving the TR blade in the flapping axis while monitoring the 
bearing for movement.
     If the Teflon cloth is coming out of its position within 
the bearing or if there is discoloration or scoring, replacing the 
control rod assembly before further flight.
     If play is detected, having a mechanic remove the control 
rod from the helicopter, and using a dial indicator, measuring the 
control rod bearing wear. If the radial play exceeds 0.008 inch or 
axial play exceeds 0.016 inch, replacing the control rod with an 
airworthy control rod before further flight.
     Thereafter, at intervals not to exceed 30 hours time-in-
service (TIS), repeating the requirement to remove the control rod and 
measuring the bearing for wear using a dial indicator.
    AD 2011-22-05 was prompted by the issuance of AD No. 2010-0006, 
dated January 7, 2010, by the European Aviation Safety Agency (EASA), 
which is the Technical Agent for the Member States of the European 
Union. The EASA AD was issued to correct an unsafe condition for 
certain Eurocopter helicopters. EASA advised that a pilot of a 
Eurocopter Model AS350 helicopter felt slight vibrations in the pedal 
unit in flight. A few minutes later, the vibration level increased and 
the pilot carried out a precautionary autorotation landing. After 
landing, it was discovered that one TR pitch-change link was damaged, 
the tailboom cone was missing, and there was an impact mark on the 
tailboom. Further investigation revealed the affected TR pitch-change 
link showed extensive wear on the ball-joint. EASA advised that this 
condition, if not detected and corrected, could lead to loss of the 
anti-torque function and possible loss of control of the helicopter.

Actions Since AD 2011-22-05 Was Issued

    Since we issued AD 2011-22-05 (76 FR 70046, November 10, 2011), we 
have determined that we can safely extend the compliance time for the 
initial bearing play check and the interval for recurring checks to 30 
hours TIS. We also received several requests for alternative methods of 
compliance regarding the bearing play check, and as a result this 
proposed AD would clarify the requirements of that check. We 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.

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 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    Eurocopter has 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 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 to ensure the continued airworthiness 
of these helicopters.

Proposed AD Requirements

    This proposed AD would clarify the requirements of AD 2011-22-05, 
extend the compliance time for the bearing play checks to 30 hours TIS, 
and remove the requirement to replace the control rod if the Teflon 
cloth is out of position or if there is discoloration or scoring on the 
bearing.

Costs of Compliance

    We estimate that this proposed AD would affect 936 helicopters of 
U.S. Registry and that labor costs will average $85 a work-hour. 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 will cost about

[[Page 59300]]

$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, would cost $85 per 
helicopter, and replacing 1 control rod would cost $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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Eurocopter France: Docket No. FAA-2011-1158; Directorate Identifier 
2010-SW-018-AD.

(a) Applicability

    This AD applies to Eurocopter France (Eurocopter) 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 (76 FR 70046, November 10, 2011), 
Amendment 39-16847, Docket No. FAA-2011-1158, Directorate Identifier 
2010-SW-018-AD.

(d) Comments Due Date

    We must receive comments by November 25, 2013.

(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 of 
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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[GRAPHIC] [TIFF OMITTED] TP26SE13.009

    (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:

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[GRAPHIC] [TIFF OMITTED] TP26SE13.010

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[GRAPHIC] [TIFF OMITTED] TP26SE13.011

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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 
robert.grant@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.
    (3) An AMOC approved previously in accordance with Airworthiness 
Directive No. 2011-22-05, Amendment 39-16847 (76 FR 70046, November 
10, 2011), is approved as an AMOC for the corresponding requirements 
in paragraph (f)(2) of this AD.

(h) Additional Information

    (1) Eurocopter Alert Service Bulletin (ASB) No. 05.00.60 and ASB 
No. 05.00.56, 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 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 the European Aviation 
Safety Agency (EASA) AD No. 2010-0006, dated January 7, 2010. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2011-1158.

(i) Subject

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

    Issued in Fort Worth, Texas, on September 17, 2013.
Gwendolynne O'Connell,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-23434 Filed 9-25-13; 8:45 am]
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