[Federal Register Volume 78, Number 187 (Thursday, September 26, 2013)]
[Proposed Rules]
[Pages 59298-59303]
From the Federal Register Online via the Government Publishing 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
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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 [email protected].
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
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$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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(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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(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
[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.
(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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