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[Federal Register Volume 76, Number 218 (Thursday, November 10, 2011)]
[Rules and Regulations]
[Pages 70046-70051]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27774]

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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 39-16847; AD 2011-22-05]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Model AS350B, B1, B2, 
B3, BA, C, D, and D1; and AS355E, F, F1, F2, N, and NP Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the Eurocopter France (Eurocopter) Model AS350B, B1, B2, B3, 
BA, C, D, and D1 helicopters; and Model AS355E, F, F1, F2, and N 
helicopters with certain tail rotor pitch control rods installed. That 
AD requires a daily check of the tail rotor (T/R) pitch control rod 
(control rod) outboard spherical bearing (bearing) for play. If play 
exists, that AD requires measuring the bearing's radial and axial play. 
Since that AD was issued, an incident occurred where the pilot of a 
Model AS350 helicopter felt vibrations in the anti-torque pedal in 
flight, resulting in a precautionary landing. An investigation 
determined that the control rod showed extensive wear on the ball-
joint. This superseding AD maintains the requirements of the existing 
AD, and expands the applicability to include the Model AS355NP 
helicopter and additional part-numbered control rods. The actions 
specified by this AD are intended to prevent failure of a control rod, 
loss of T/R control, and subsequent loss of control of the helicopter.

DATES: Effective November 25, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before January 9, 2012.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from 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.
    Examining the Docket: You may examine the docket that contains the 
AD, any comments, and other information 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 Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

[[Page 70047]]

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Manager, FAA, Rotorcraft 
Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, 
TX 76137, telephone (817) 222-5126, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    On October 22, 2003, the FAA issued AD 2003-22-06, Amendment 39-
13354 (68 FR 61608, October 29, 2003), Docket 2000-SW-12-AD (AD 2003-
22-06), for Eurocopter Model AS350B, B1, B2, B3, BA, C, D, and D1; and 
Model AS355E, F, F1, F2, and N helicopters with control rods, part-
number (P/N) 350A33-2145-00 or 350A33-2145-01, which superseded AD 98-
24-35, Amendment 39-10921 (63 FR 66418, December 2, 1998), Docket 98-
SW-41-AD, issued November 19, 1998 (AD 98-24-35). AD 98-24-35 required 
a recurring inspection to measure the control rod bearing for radial 
and axial play. That action was prompted by an accident and separate 
incident involving Model AS350B2 helicopters, and investigations 
revealed a broken control rod on the helicopter that was involved in 
the accident, and a severely worn control rod on the helicopter 
involved in the incident. There were two other unconfirmed incidents 
cited by the National Transportation Safety Board (based on the 
manufacturer's reports) involving the same control rod, P/N 350A33-
2145-01. AD 2003-22-06 superseded AD 98-24-35, and requires a daily 
check of the control rod bearing, allows a larger axial play limit, and 
requires a more frequent inspection interval once play is found in the 
control rod bearing during a daily check. AD 2003-22-06 also added the 
Eurocopter Model AS350B3 helicopter and another part-numbered control 
rod to the applicability. AD 2003-22-06 was prompted by a review of 
additional service information and public comments regarding the 
requirements of AD 98-24-35. The actions specified by AD 2003-22-06 are 
intended to prevent separation of the bearing ball from its outer race, 
rubbing of the body of the control rod against the tail rotor blade 
pitch horn clevis, failure of a control rod, loss of T/R control, and 
subsequent loss of control of the helicopter.

Actions Since Issuing Previous AD

    Since issuing AD 2003-22-06 (68 FR 61608, October 29, 2003), the 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Union, has issued EASA AD No. 
2010-0006, dated January 7, 2010, to correct an unsafe condition for 
the Eurocopter Model AS350B, B1, B2, B3, BA, BB, and D helicopters; and 
Model AS355E, F, F1, F2, and N, and NP helicopters with control rods, 
P/N 350A33-2100-00, -01, -02, -03, or -04; P/N 350A33-2121-00, -01, or 
-02; P/N 350A33-2143-00; or P/N 350A33-2145-00 or -01. EASA advises 
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 advises 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.
    In addition, after further review of the language used to describe 
the unsafe condition addressed in AD 2003-22-06 (68 FR 61608, October 
29, 2003), it has been determined that changes are needed in 
terminology to more accurately describe the unsafe condition that this 
AD is intending to correct.

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. The EASA classified these ASBs as 
mandatory and issued EASA AD No. 2010-0006 to ensure the continued 
airworthiness of these helicopters.

FAA's Determination and Requirements of This AD

    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, their 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. Therefore, this AD is being issued to prevent failure of 
a control rod, loss of tail rotor control, and subsequent loss of 
control of the helicopter. This AD requires the following actions:
     Before the first flight of each day, check 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. This action may be performed by an owner/operator 
(pilot) holding at least a private pilot certificate, and must be 
entered into the helicopter maintenance records in accordance with 14 
CFR 43.9(a)(1)-(4) and 91.417(a)(2)(v). A pilot may perform this check 
because it involves only a visual and physical check of the control rod 
for play, and can be performed equally well by a pilot or a mechanic. 
If play is detected, a mechanic must remove the control rod from the 
helicopter, and using a dial indicator, measure the control rod bearing 
wear. If the radial play exceeds 0.008 inch or axial play exceeds 0.016 
inch, the control rod must be replaced with an airworthy control rod 
before further flight.
     Thereafter, at recurring intervals not to exceed 30 hours 
time-in-service (TIS), remove the control rod and measure the bearing 
wear using a dial indicator. 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.
    The short compliance time involved, before the first flight of each 
day, is required because the previously described critical unsafe 
condition can adversely affect the controllability of the helicopter. 
Therefore, this AD must be issued immediately. Since a situation exists 
that requires the immediate adoption of this regulation, it is found 
that notice and opportunity for prior public comment hereon are 
impracticable, and that good cause exists for making this amendment 
effective in less than 30 days.

Differences Between This AD and the EASA AD

    This AD differs from the EASA AD as follows:
     This AD includes the Model AS350C and AS350D1 helicopters, 
as they may have the same control rod; this AD does not include the 
Model AS350BB because it does not have an FAA-issued type certificate.
     This AD uses the term ``T/R pitch control rod'' and the 
EASA AD uses the term ``T/R pitch change link'' to describe the same 
part.
     This AD uses the term ``loss of T/R control'' to describe 
the unsafe condition, and the EASA AD uses the term ``loss of anti-
torque control.''

[[Page 70048]]

     This AD uses the term ``hours TIS'' to describe compliance 
times, and the EASA AD uses the term ``flight hours.''
     This AD requires either a pilot/operator or mechanic, 
before the first flight of each day, to perform a check or inspection 
of the bearing for play. If play is found, a mechanic must, before 
further flight, measure the bearing play, and thereafter measure the 
bearing play at intervals not to exceed 30 hours TIS. The EASA AD 
requires a mechanic, within 30 flight hours, to perform an initial 
inspection to measure the bearing play, and thereafter, at intervals 
not to exceed 30 flight hours. The EASA AD does not require a daily 
check.

Costs of Compliance

    We estimate that this AD will affect about 733 helicopters of U.S. 
registry. We estimate, per helicopter, it will take minimal work-hours 
to do the daily check, 1 work-hour to do the recurring inspection, and 
1 work-hour to replace 1 control rod. The average labor rate is $85 per 
work-hour. Required parts will 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 $1,949,047 per year, assuming 10 recurring 
inspections per year per helicopter, and assuming 1 control rod is 
replaced per year per helicopter.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2011-1158; Directorate 
Identifier 2010-SW-018-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
docket Web site, you can find and read the comments to any of our 
dockets, including the name of the individual who sent the comment. You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19476).

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 the 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 AD. See the AD docket to examine the economic evaluation.

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.

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 Amendment 39-13354 (68 FR 
61608; October 29, 2003), and adding the following new Airworthiness 
Directive (AD):

2011-22-05 EUROCOPTER FRANCE (EUROCOPTER): Amendment 39-16847; 
Docket No. FAA-2011-1158; Directorate Identifier 2010-SW-018-AD; 
supersedes AD 2003-22-06, issued October 22, 2003 (68 FR 61608; 
October 29, 2003), Amendment 39-13354, Docket No. 2000-SW-12-AD.

    Applicability: 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.
    Compliance: Required as indicated.
    To prevent failure of a T/R control rod, loss of T/R control, 
and subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before the first flight of each day, 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 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 91.173, 121.380, or 135.439.
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[[Page 70049]]

[GRAPHIC] [TIFF OMITTED] TR10NO11.019

    (b) If the Teflon cloth is coming out of its normal position 
within the bearing, totally or partially, or if there is 
discoloration or scoring on the bearing, before further flight, 
replace the control rod with an airworthy control rod.
    (c) If a pilot or mechanic detects play, 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 of this AD:

[[Page 70050]]

[GRAPHIC] [TIFF OMITTED] TR10NO11.020

[[Page 70051]]

[GRAPHIC] [TIFF OMITTED] TR10NO11.021

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    (1) Remove the control rod from the helicopter.
    (2) Mount the control rod in a vise as shown in Figure 2 of this 
AD.
    (3) 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 of this AD.
    (4) 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.
    (5) Mount the control rod and bearing in a vise as shown in 
Figure 3 of this AD.
    (6) Using a dial indicator, take radial play measurements by 
moving the control rod in the direction F as shown in Figure 3 of 
this AD.
    (7) Record the hours of operation on each control rod.
    (8) 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.
    (9) If the radial and axial play are within limits, reinstall 
the control rod.
    (10) Thereafter, at intervals not to exceed 30 hours time-in-
service, remove the control rod and measure the bearing play with a 
dial indicator in accordance with paragraph (c) of this AD.
    (d) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, DOT/FAA, ATTN: Jim 
Grigg, Manager, Rotorcraft Directorate, 2601 Meacham Blvd., Fort 
Worth, TX 76137, telephone (817) 222-5126, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (e) The Joint Aircraft System/Component Code is 6720: Tail rotor 
control system.
    (f) This amendment becomes effective on November 25, 2011.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency (France) AD No. 2010-0006, dated January 7, 2010.

    Issued in Fort Worth, Texas, on October 12, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27774 Filed 11-9-11; 8:45 am]
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