Airworthiness Directives; Eurocopter France (Eurocopter) Model AS332C, AS332L, AS332L1, and AS332L2 Helicopters, 66606-66609 [2011-27673]
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66606
§ 917.143
Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations
[Amended]
21. In § 917.143, lift the suspension of
April 18, 2011 (76 FR 21618); remove
the words ‘‘and peaches’’ from the
introductory text of paragraph (b) and
from paragraphs (b)(1), (b)(2), and (b)(4);
remove the words ‘‘and 200 pounds of
peaches’’ from paragraph (b)(3); and
suspend the section indefinitely.
■
§ 917.150
■
[Removed]
22. Remove § 917.150.
Subpart—Assessment Rates
(§§ 917.258 through 917.259)
[Removed]
23. Remove Subpart—Assessment
Rates, consisting of §§ 917.258 through
917.259.
■
Subpart—Container and Pack
Regulation (§§ 917.442) [Removed]
24. Remove Subpart—Container and
Pack Regulation, consisting of § 917.442.
■
§ 917.459
■
[Removed]
25. Remove §§ 917.459.
Dated: October 14, 2011.
David R. Shipman,
Acting Administrator, Agricultural Marketing
Service.
[FR Doc. 2011–27286 Filed 10–26–11; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0939; Directorate
Identifier 2010–SW–067–AD; Amendment 39
16798; AD 2011–18–16]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France (Eurocopter) Model AS332C,
AS332L, AS332L1, and AS332L2
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
AGENCY:
This amendment adopts a
new airworthiness directive (AD) for the
specified Eurocopter model helicopters.
This action requires inspecting the
upper end fitting ball joints of the main
rotor servocontrols for lateral play, and
depending on the findings either
repetitively inspecting the ball joint or
replacing the servocontrol. This
amendment is prompted by reports of
noncompliant swaging of the end fitting
ball joints on main rotor servocontrols.
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
17:05 Oct 26, 2011
Jkt 226001
Investigation has shown that the
swaging load applied to the ball joints
was 1.3 metric tons instead of the
specified 13 metric tons. The actions
specified in this AD are intended to
prevent failure of the upper end fitting
ball joints of the main rotor
servocontrols, failure of the upper end
fittings, and loss of control of the
helicopter.
DATES: Effective November 14, 2011.
Comments for inclusion in the Rules
Docket must be received on or before
December 27, 2011.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• Federal eRulemaking Portal: Go to
https://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 Forum
Drive, Grand Prairie, TX 75053–4005,
telephone (800) 232–0323, fax (972)
641–3710, or at https://
www.eurocopter.com.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information on the Internet at https://
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.
FOR FURTHER INFORMATION CONTACT: Gary
Roach, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Regulations and
Guidance Group, 2601 Meacham Blvd.,
Fort Worth, Texas 76137, telephone
(817) 222–5130, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Discussion
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–
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
0117–E, dated June 16, 2010, to correct
an unsafe condition for the specified
Eurocopter model helicopters. EASA
advises that the equipment
manufacturer (Goodrich) has identified
two servocontrol production batches as
noncompliant with swaging of the end
fitting ball joints on main rotor
servocontrols. EASA states that
investigations have revealed that the
swaging load applied to the ball joints
in these two batches was 1.3 metric
tons, instead of the specified 13 metric
tons, which could lead the ball joints to
slip in service. The slipping of the ball
joint of the servocontrol lower end
fitting does not significantly affect the
service life of the end fitting. However,
the slipping of the ball joint of the
servocontrol upper end fitting can lead
to a significant reduction in the service
life of the end fitting. This condition, if
not corrected, could lead to failure of
the upper end fitting ball joint of a main
rotor servocontrol and result in loss of
control of the helicopter.
Differences Between This AD and the
EASA AD
We refer to flight hours as hours timein-service (TIS).
Related Service Information
Eurocopter has issued an Emergency
Alert Service Bulletin (EASB), dated
June 15, 2010, with two numbers: No.
67.00.40 for FAA type-certificated
Models AS332C, L, L1, and L2 and for
Models AS332C1, B, B1, F1, M, and M1
that are not FAA type certificated, and
No. 67.00.27 for Models AS532AC, AL,
SC, UC, UE, UL, A2, and U2 that are not
FAA type certificated. The EASB
specifies checking and restoring
conformity of the affected end fitting
ball joints of the servocontrols. The
EASB contains Appendix 1 and 2,
Goodrich Service Bulletins No. SC7203–
67–31–02 and No. SC7221–67–39–02,
both dated May 11, 2010, which specify
the process for comforming each
affected servocontrol. EASA classified
this EASB as mandatory and issued
Emergency AD No. 2010–0117–E, dated
June 16, 2010, to ensure the continued
airworthiness of these helicopters.
FAA’s Evaluation and Unsafe Condition
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, 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
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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs.
Eurocopter states that there are
currently no helicopters with the
affected part installed in the United
States. However, this rule is necessary
to ensure that the described unsafe
condition is addressed in the event this
part is installed on any helicopter in the
future.
Costs of Compliance
There are no costs of compliance
assuming that there are no helicopters
on the U.S. Registry with the affected
part installed as represented by the
manufacturer.
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FAA’s Determination of the Effective
Date
This unsafe condition is likely to exist
or develop on other helicopters of these
same type designs. Therefore, this AD is
being issued to prevent failure of the
upper end fitting ball joints of the main
rotor servocontrols, failure of the upper
end fittings, and loss of control of the
helicopter. Since there are currently no
U.S. registered helicopters with the
affected part installed, we have
determined that notice and opportunity
for prior public comment before issuing
this AD are unnecessary and that good
cause exists for making this amendment
effective in less than 30 days.
Requirements of This AD
This AD requires:
• Within 15 hours TIS, unless
accomplished previously, using a feeler
gage, measuring the lateral play between
the outer ring of the ball joint and each
of the two faces of the upper end fitting.
• If the lateral play is greater than or
equal to 1 millimeter (MM) (0.04 inch)
and the servocontrol has accumulated
825 or more hours TIS, replacing it with
an airworthy servocontrol before further
flight.
• If the lateral play is greater than or
equal to 1 mm (0.04 inch) and the
servocontrol has accumulated less than
825 hours TIS, on or before the
servocontrol accumulates 825 hours
TIS, replacing it with an airworthy
servocontrol.
• If the lateral play is less than 1 mm
(0.04 inch), thereafter, at intervals not to
exceed 300 hours TIS, repeating the
inspection. At each 300-hour TIS
inspection, if the lateral play is greater
than or equal to 1 mm (0.04 inch),
within 525 hours TIS, replacing the
servocontrol with an airworthy
servocontrol.
• Replacing the servocontrol with an
airworthy servocontrol that is not
included in the AD applicability or that
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17:05 Oct 26, 2011
Jkt 226001
is modified with a letter ‘‘R’’ after the S/
N constitutes terminating action for the
requirements of this AD.
Because these affected parts have an
unlimited operational fatigue life with
no previous fatigue inspections
required, the replacement criteria of this
AD assumes that the affected
servocontrols found to have greater than
or equal to 1 MM of lateral play have
already been operated for at least 825
hours TIS with this fatigue damage and
must be replaced at 825 hours TIS or if
they have already accumulated 825 or
more hours TIS, within 15 hours TIS of
the effective date of this AD. However,
if a subsequent 300-hour TIS repetitive
inspection required by this AD reveals
lateral play of 1 MM or greater, those
affected servocontrols may be operated
an additional 525 hours TIS because the
previous 300-hours TIS inspection
established the new baseline for the 825
hours TIS thereby allowing an
additional 525 hours TIS before
replacement.
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 FAA Docket No. ‘‘FAA–2011–
0939; Directorate Identifier 2010–SW–
067–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://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 19477 78).
Regulatory Findings
We have determined that notice and
prior public comment are unnecessary
in promulgating this regulation;
therefore, it can be issued immediately
to correct an unsafe condition in aircraft
because none of the model helicopters
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
66607
that are registered in the United States
have the affected part installed. We have
also determined that this regulation is
not a ‘‘significant regulatory action’’
under Executive Order 12866. It has
been determined further that this action
involves an emergency regulation under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979). If it
is determined that this emergency
regulation otherwise would be
significant under DOT Regulatory
Policies and Procedures, a final
regulatory evaluation will be prepared
and placed in the AD docket.
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, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration amends part 39 of the
Federal Aviation Regulations (14 CFR
part 39) as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive (AD) to
read as follows:
■
2011–18–16 Eurocopter France:
Amendment 39–16798; Docket No. FAA
2011–0939; Directorate Identifier 2010–
SW–067–AD.
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27OCR1
66608
Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations
1727, which are not marked with a letter ‘‘R’’
after the S/N, certificated in any category.
Compliance: Required as indicated.
To prevent failure of the upper end fitting
ball joints of the main rotor servocontrols,
failure of the upper end fittings, and loss of
control of the helicopter, do the following:
(a) Within 15 hours time-in-service (TIS),
unless accomplished previously, using a
feeler gage, measure the lateral play between
the outer ring of the ball joint and each of the
two faces of the upper end fitting as depicted
in Figure 1 of this AD.
(b) If the lateral play is greater than or
equal to 1 millimeter (MM) (0.04 inch) and
the servocontrol has accumulated 825 or
more hours TIS, before further flight, replace
it with an airworthy servocontrol.
(c) If the lateral play is greater than or
equal to 1 mm (0.04 inch) and the
servocontrol has accumulated less than 825
hours TIS, on or before the servocontrol
accumulates 825 hours TIS, replace it with
an airworthy servocontrol.
(d) If the lateral play is less than 1 mm
(0.04 inch), at intervals not to exceed 300
hours TIS, repeat the inspection required by
paragraph (a) of this AD. At each 300 hour
TIS interval inspection, if the lateral play is
greater than or equal to 1 mm (0.04 inch),
within 525 hours TIS, replace the
servocontrol with an airworthy servocontrol.
Note 1: An acceptable method of returning
the servocontrol to an airworthy condition
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17:05 Oct 26, 2011
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PO 00000
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Fmt 4700
Sfmt 4700
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27OCR1
ER27OC11.001</GPH>
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Applicability: Models AS332C, L, L1, and
L2 helicopters, with main rotor
servocontrols, part number (P/N) SC7203–1
with serial number (S/N) 633 through 643,
645 through 659, 664 or 665, or P/N SC7221–
1 with S/N 1693 through 1723 and 1726 or
Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations
for the purposes of this AD is by modifying
the servocontrol and marking an ‘‘R’’ after the
S/N by following Goodrich Service Bulletin
(SB) No. SC7203–67–31–02, dated May 11,
2010, for servocontrol, P/N SC7203–1, or
Goodrich SB No. SC72216739–02, dated May
11, 2010, for servocontrol, P/N SC7221 1. The
Goodrich SBs are attached to Eurocopter
Emergency Alert SB containing two numbers
(67.00.40 and 67–00.27), dated June 15, 2010
as Appendix 1 and Appendix 2, respectively.
None of these three SBs is incorporated by
reference in this AD.
(e) Replacing a servocontrol with an
airworthy servocontrol that is marked with a
letter ‘‘R’’ by the manufacturer after the S/N
constitutes terminating action for the
requirements of this AD.
(f) 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, Rotorcraft Directorate,
FAA, ATTN: Gary Roach, Aviation Safety
Engineer, FAA, Regulations and Guidance
Group, 2601 Meacham Blvd, Fort Worth,
Texas 76137, telephone (817) 222–5130, fax
(817) 222 5961, for information about
previously approved alternative methods of
compliance.
(g) The Joint Aircraft System/Component
(JASC) Code is 6730: Rotorcraft Servo
System.
(h) This amendment becomes effective on
November 14, 2011.
Note 2: The subject of this AD is addressed
in European Aviation Safety Agency
Emergency AD No. 2010–0117–E, dated June
16, 2010.
Issued in Fort Worth, Texas, on August 23,
2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2011–27673 Filed 10–26–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1035; Directorate
Identifier 2011–SW–038–AD; Amendment
39–16817; AD 2011–15–51]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (Bell) Model
407 and 427 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
mstockstill on DSK4VPTVN1PROD with RULES
AGENCY:
This document publishes in
the Federal Register an amendment
adopting Airworthiness Directive (AD)
2011–15–51, which was sent previously
to all known U.S. owners and operators
SUMMARY:
VerDate Mar<15>2010
17:05 Oct 26, 2011
Jkt 226001
of the specified Bell Model 407 and 427
helicopters by individual letters. This
AD requires inspecting certain
hydraulic servo actuators to determine
whether the shaft turns independently
of the nut or the clevis assembly. If the
shaft turns independently, this AD
requires replacing the servo with an
airworthy servo. If the shaft does not
turn independently, the AD requires
inspecting to determine the condition of
the lock washers. Based on the
condition of the lock washers, the AD
requires either replacing the servo with
an airworthy servo, or if any tab of the
lock washer is not flush against a flat
surface of the nut or clevis assembly,
bending it flush against a flat surface.
The AD also requires reidentifying the
servo by metal-impression stamping or
by vibro-etching ‘‘67.01’’ onto the
modification plate. Also, the AD
requires before installing a servo with a
part number or serial number identified
in this AD, not identified by ‘‘67–01’’ on
the modification plate, inspecting it by
following the requirements of this AD.
This AD is prompted by a report that a
quality escape by a supplier has
occurred and certain servos may have a
loose nut, shaft, and clevis assembly
due to improper lock-washer
installation. An investigation after an
accident revealed the clevis nut on the
servo was loose. The actions specified
by this AD are intended to prevent a
malfunction of a servo in the flight
control system and subsequent loss of
control of the helicopter.
DATES: Effective November 14, 2011, to
all persons except those persons to
whom it was made immediately
effective by Emergency AD 2011–15–51,
issued on July 8, 2011, which contained
the requirements of this amendment.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of November
14, 2011.
Comments for inclusion in the Rules
Docket must be received on or before
December 27, 2011.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• Federal eRulemaking Portal: Go to
https://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
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
66609
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 Bell
Helicopter Textron Canada Limited,
12,800 Rue de l’Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437–2862 or
(800) 363–8023, fax (450) 433–0272, or
at https://www.bellcustomer.com/files/.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information on the Internet at https://
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.
FOR FURTHER INFORMATION CONTACT: Matt
Wilbanks, Aviation Safety Engineer,
2601 Meacham Blvd, Fort Worth, Texas
76137, telephone (817) 222–5051, fax
(817) 222–5961.
SUPPLEMENTARY INFORMATION: On July 8,
2011, the FAA issued Emergency AD
2011–15–51 for the specified model
helicopters, which requires inspecting
certain servos to determine whether the
shaft turns independently of the nut or
the clevis assembly. If the shaft turns
independently, the AD requires
replacing the servo with an airworthy
servo. If the shaft does not turn
independently, the AD requires
inspecting to determine the condition of
the lock washers. If at least one lock
washer is not bent flush against a flat
surface of the nut and at least one tab
of the lock washer is not bent flush
against a flat surface of the clevis
assembly, the AD requires replacing the
servo with an airworthy servo. If any tab
of the lock washer is not bent flush
against either a flat surface of the nut or
clevis assembly, the AD requires
bending the tab flush against a flat
surface. The AD also requires
reidentifying the servo by metalimpression stamping or by vibro-etching
‘‘67.01’’ onto the modification plate.
Also, the AD requires before installing
a servo with a part number or serial
number identified in this AD, not
identified by ‘‘67–01’’ on the
modification plate, inspecting and
reidentifying it by following the
requirements of this AD. That action
was prompted by a report that a quality
escape by a supplier has occurred and
certain servos may have a loose nut,
E:\FR\FM\27OCR1.SGM
27OCR1
]]>Agencies
[Federal Register Volume 76, Number 208 (Thursday, October 27, 2011)]
[Rules and Regulations]
[Pages 66606-66609]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27673]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0939; Directorate Identifier 2010-SW-067-AD;
Amendment 39 16798; AD 2011-18-16]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France (Eurocopter) Model
AS332C, AS332L, AS332L1, and AS332L2 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Eurocopter model helicopters. This action requires
inspecting the upper end fitting ball joints of the main rotor
servocontrols for lateral play, and depending on the findings either
repetitively inspecting the ball joint or replacing the servocontrol.
This amendment is prompted by reports of noncompliant swaging of the
end fitting ball joints on main rotor servocontrols. Investigation has
shown that the swaging load applied to the ball joints was 1.3 metric
tons instead of the specified 13 metric tons. The actions specified in
this AD are intended to prevent failure of the upper end fitting ball
joints of the main rotor servocontrols, failure of the upper end
fittings, and loss of control of the helicopter.
DATES: Effective November 14, 2011.
Comments for inclusion in the Rules Docket must be received on or
before December 27, 2011.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
Federal eRulemaking Portal: Go to https://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 Forum Drive, Grand Prairie, TX
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at https://www.eurocopter.com.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information on the Internet at https://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.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Guidance Group, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5130, fax
(817) 222-5961.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
No. 2010-0117-E, dated June 16, 2010, to correct an unsafe condition
for the specified Eurocopter model helicopters. EASA advises that the
equipment manufacturer (Goodrich) has identified two servocontrol
production batches as noncompliant with swaging of the end fitting ball
joints on main rotor servocontrols. EASA states that investigations
have revealed that the swaging load applied to the ball joints in these
two batches was 1.3 metric tons, instead of the specified 13 metric
tons, which could lead the ball joints to slip in service. The slipping
of the ball joint of the servocontrol lower end fitting does not
significantly affect the service life of the end fitting. However, the
slipping of the ball joint of the servocontrol upper end fitting can
lead to a significant reduction in the service life of the end fitting.
This condition, if not corrected, could lead to failure of the upper
end fitting ball joint of a main rotor servocontrol and result in loss
of control of the helicopter.
Differences Between This AD and the EASA AD
We refer to flight hours as hours time-in-service (TIS).
Related Service Information
Eurocopter has issued an Emergency Alert Service Bulletin (EASB),
dated June 15, 2010, with two numbers: No. 67.00.40 for FAA type-
certificated Models AS332C, L, L1, and L2 and for Models AS332C1, B,
B1, F1, M, and M1 that are not FAA type certificated, and No. 67.00.27
for Models AS532AC, AL, SC, UC, UE, UL, A2, and U2 that are not FAA
type certificated. The EASB specifies checking and restoring conformity
of the affected end fitting ball joints of the servocontrols. The EASB
contains Appendix 1 and 2, Goodrich Service Bulletins No. SC7203-67-31-
02 and No. SC7221-67-39-02, both dated May 11, 2010, which specify the
process for comforming each affected servocontrol. EASA classified this
EASB as mandatory and issued Emergency AD No. 2010-0117-E, dated June
16, 2010, to ensure the continued airworthiness of these helicopters.
FAA's Evaluation and Unsafe Condition 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, 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
[[Page 66607]]
unsafe condition exists and is likely to exist or develop on other
helicopters of these same type designs.
Eurocopter states that there are currently no helicopters with the
affected part installed in the United States. However, this rule is
necessary to ensure that the described unsafe condition is addressed in
the event this part is installed on any helicopter in the future.
Costs of Compliance
There are no costs of compliance assuming that there are no
helicopters on the U.S. Registry with the affected part installed as
represented by the manufacturer.
FAA's Determination of the Effective Date
This unsafe condition is likely to exist or develop on other
helicopters of these same type designs. Therefore, this AD is being
issued to prevent failure of the upper end fitting ball joints of the
main rotor servocontrols, failure of the upper end fittings, and loss
of control of the helicopter. Since there are currently no U.S.
registered helicopters with the affected part installed, we have
determined that notice and opportunity for prior public comment before
issuing this AD are unnecessary and that good cause exists for making
this amendment effective in less than 30 days.
Requirements of This AD
This AD requires:
Within 15 hours TIS, unless accomplished previously, using
a feeler gage, measuring the lateral play between the outer ring of the
ball joint and each of the two faces of the upper end fitting.
If the lateral play is greater than or equal to 1
millimeter (MM) (0.04 inch) and the servocontrol has accumulated 825 or
more hours TIS, replacing it with an airworthy servocontrol before
further flight.
If the lateral play is greater than or equal to 1 mm (0.04
inch) and the servocontrol has accumulated less than 825 hours TIS, on
or before the servocontrol accumulates 825 hours TIS, replacing it with
an airworthy servocontrol.
If the lateral play is less than 1 mm (0.04 inch),
thereafter, at intervals not to exceed 300 hours TIS, repeating the
inspection. At each 300-hour TIS inspection, if the lateral play is
greater than or equal to 1 mm (0.04 inch), within 525 hours TIS,
replacing the servocontrol with an airworthy servocontrol.
Replacing the servocontrol with an airworthy servocontrol
that is not included in the AD applicability or that is modified with a
letter ``R'' after the S/N constitutes terminating action for the
requirements of this AD.
Because these affected parts have an unlimited operational fatigue
life with no previous fatigue inspections required, the replacement
criteria of this AD assumes that the affected servocontrols found to
have greater than or equal to 1 MM of lateral play have already been
operated for at least 825 hours TIS with this fatigue damage and must
be replaced at 825 hours TIS or if they have already accumulated 825 or
more hours TIS, within 15 hours TIS of the effective date of this AD.
However, if a subsequent 300-hour TIS repetitive inspection required by
this AD reveals lateral play of 1 MM or greater, those affected
servocontrols may be operated an additional 525 hours TIS because the
previous 300-hours TIS inspection established the new baseline for the
825 hours TIS thereby allowing an additional 525 hours TIS before
replacement.
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 FAA Docket No. ``FAA-2011-0939;
Directorate Identifier 2010-SW-067-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to https://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 19477 78).
Regulatory Findings
We have determined that notice and prior public comment are
unnecessary in promulgating this regulation; therefore, it can be
issued immediately to correct an unsafe condition in aircraft because
none of the model helicopters that are registered in the United States
have the affected part installed. We have also determined that this
regulation is not a ``significant regulatory action'' under Executive
Order 12866. It has been determined further that this action involves
an emergency regulation under DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979). If it is determined that this
emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the AD docket.
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, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
2011-18-16 Eurocopter France: Amendment 39-16798; Docket No. FAA
2011-0939; Directorate Identifier 2010-SW-067-AD.
[[Page 66608]]
Applicability: Models AS332C, L, L1, and L2 helicopters, with
main rotor servocontrols, part number (P/N) SC7203-1 with serial
number (S/N) 633 through 643, 645 through 659, 664 or 665, or P/N
SC7221-1 with S/N 1693 through 1723 and 1726 or 1727, which are not
marked with a letter ``R'' after the S/N, certificated in any
category.
Compliance: Required as indicated.
To prevent failure of the upper end fitting ball joints of the
main rotor servocontrols, failure of the upper end fittings, and
loss of control of the helicopter, do the following:
(a) Within 15 hours time-in-service (TIS), unless accomplished
previously, using a feeler gage, measure the lateral play between
the outer ring of the ball joint and each of the two faces of the
upper end fitting as depicted in Figure 1 of this AD.
[GRAPHIC] [TIFF OMITTED] TR27OC11.001
(b) If the lateral play is greater than or equal to 1 millimeter
(MM) (0.04 inch) and the servocontrol has accumulated 825 or more
hours TIS, before further flight, replace it with an airworthy
servocontrol.
(c) If the lateral play is greater than or equal to 1 mm (0.04
inch) and the servocontrol has accumulated less than 825 hours TIS,
on or before the servocontrol accumulates 825 hours TIS, replace it
with an airworthy servocontrol.
(d) If the lateral play is less than 1 mm (0.04 inch), at
intervals not to exceed 300 hours TIS, repeat the inspection
required by paragraph (a) of this AD. At each 300 hour TIS interval
inspection, if the lateral play is greater than or equal to 1 mm
(0.04 inch), within 525 hours TIS, replace the servocontrol with an
airworthy servocontrol.
Note 1: An acceptable method of returning the servocontrol to
an airworthy condition
[[Page 66609]]
for the purposes of this AD is by modifying the servocontrol and
marking an ``R'' after the S/N by following Goodrich Service
Bulletin (SB) No. SC7203-67-31-02, dated May 11, 2010, for
servocontrol, P/N SC7203-1, or Goodrich SB No. SC72216739-02, dated
May 11, 2010, for servocontrol, P/N SC7221 1. The Goodrich SBs are
attached to Eurocopter Emergency Alert SB containing two numbers
(67.00.40 and 67-00.27), dated June 15, 2010 as Appendix 1 and
Appendix 2, respectively. None of these three SBs is incorporated by
reference in this AD.
(e) Replacing a servocontrol with an airworthy servocontrol that
is marked with a letter ``R'' by the manufacturer after the S/N
constitutes terminating action for the requirements of this AD.
(f) 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, Rotorcraft
Directorate, FAA, ATTN: Gary Roach, Aviation Safety Engineer, FAA,
Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas
76137, telephone (817) 222-5130, fax (817) 222 5961, for information
about previously approved alternative methods of compliance.
(g) The Joint Aircraft System/Component (JASC) Code is 6730:
Rotorcraft Servo System.
(h) This amendment becomes effective on November 14, 2011.
Note 2: The subject of this AD is addressed in European
Aviation Safety Agency Emergency AD No. 2010-0117-E, dated June 16,
2010.
Issued in Fort Worth, Texas, on August 23, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27673 Filed 10-26-11; 8:45 am]
BILLING CODE 4910-13-P
