81 FR 21234 - Airworthiness Directives; Airbus Helicopters (previously Eurocopter France)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 69 (April 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 69 (April 11, 2016)
| Page Range | 21234-21236 | |
| FR Document | 2016-07981 |
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)] [Rules and Regulations] [Pages 21234-21236] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07981] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4112; Directorate Identifier 2014-SW-043-AD; Amendment 39-18471; AD 2016-07-26] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (previously Eurocopter France) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2010-23-02 for Eurocopter France (now Airbus Helicopters) Model SA-365N, SA-365N1, AS- 365N2, and AS 365 N3 helicopters. AD 2010-23-02 required amending the Limitations section of the Rotorcraft Flight Manual (RFM) to limit the never-exceed velocity (VNE) to 150 Knots Indicated Air Speed (KIAS) and to add a 1,500 ft/minute rate of descent (R/D) limitation beyond 140 KIAS. Since we issued AD 2010-23-02, a design change designated as modification (MOD) 0755B28 improved the dynamic behavior of the horizontal stabilizer such that AD actions are not required. This new AD retains the requirements of AD 2010-23-01 and revises the applicability to exclude helicopters with MOD 0755B28. We are issuing this AD to exclude certain helicopters from the applicability and restrict the VNE on other helicopters to prevent failure of the horizontal stabilizer and subsequent loss of control of the helicopter. DATES: This AD is effective May 16, 2016. [[Page 21235]] ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641- 3775; or at http://www.airbushelicopters.com/techpub. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, Texas 76177. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov in Docket No. FAA-2015-4112; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2010-23-02, Amendment 39-16491 (75 FR 68169, November 5, 2010) and add a new AD. AD 2010-23-02 applied to Eurocopter France (now Airbus Helicopters) Model SA 365N, SA-365N1, AS 365N2, and AS 365 N3 helicopters. AD 2010-23-02 required amending the Limitations section of the RFM to limit the VNE to 150 KIAS and to add a 1,500 ft/ minute R/D limitation beyond 140 KIAS and installing one or more placards on the cockpit instrument panel in full view of the pilot and copilot. AD 2010-23-01 was prompted by AD No. 2008-0204R1, Revision 1, dated May 21, 2014, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advises that Airbus Helicopters developed MOD 07 55B28 to improve the dynamic behavior of the horizontal stabilizer and thus reduce the vibration levels during high speed descent. EASA issued AD No. 2008-0204R1 to retain the requirements of its previous AD but to exclude helicopters with MOD 07 55B28 from the applicability. The NPRM published in the Federal Register on October 19, 2015 (80 FR 63145). The NPRM proposed to retain the requirements to amend the Limitations section of the RFM and install one or more placards on the cockpit instrument panel. The NPRM also proposed to revise the applicability to exclude helicopters with MOD 0755B28 installed. The proposed requirements were intended to exclude certain helicopters from the applicability and restrict the VNE on other helicopters to prevent failure of the horizontal stabilizer and subsequent loss of control of the helicopter. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (80 FR 63145, October 19, 2015). 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 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 the same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Eurocopter has issued an Emergency Alert Service Bulletin (EASB) with three numbers (01.00.60, 01.00.16, and 01.28), Revision 1, dated December 2, 2008. EASB No. 01.00.60 applies to U.S. type-certificated Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters and also to military Model AS365F, Fs, Fi, and K helicopters that are not type certificated in the United States. EASB 01.00.16 applies to military Model AS565AA, MA, MB, SA, SB, and UB helicopters that are not type certificated in the United States. EASB 01.28 applies to the Model SA- 366G1 helicopter. The EASB specifies bonding one or more locally- produced labels to the instrument panel stating that the VNE is limited to 150 KIAS and the R/D must not exceed 1,500 ft/min beyond 140 KIAS. Eurocopter states in the EASB that it is working on an enhanced definition that will be proposed as soon as possible. EASA classified this EASB as mandatory and issued AD No. 2008-0204-E, dated December 4, 2008, and revised with Revision 1, dated May 21, 2014, to ensure the continued airworthiness of these helicopters. Airbus Helicopters has issued Service Bulletin (SB) No. AS365- 55.00.06, Revision 0, dated November 14, 2014, which Airbus Helicopters identifies as MOD 0755B28. The SB specifies repairing the stabilizer for suppression of the flutter phenomenon. Costs of Compliance We estimate that this AD will affect 33 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour. We estimate about \l/2\ work-hour per helicopter to make copies to include in the RFM and to make and install the placards. The parts costs are minimal. Based on these figures, we estimate the cost of this AD on U.S. operators will be $1,403 for the fleet. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866; (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); [[Page 21236]] (3) Will not affect intrastate aviation in Alaska to the extent that a regulatory; and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2010-23-02, Amendment 39-16491 (75 FR 68169, November 5, 2010), and adding the following new AD: 2016-07-26 Airbus Helicopters (previously Eurocopter France): Amendment 39-18471; Docket No. FAA-2015-4112; Directorate Identifier 2014-SW-043-AD. (a) Applicability This AD applies to Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters, with a horizontal stabilizer, part number 365A13- 3030-1901, -1902, -1903, -1904, -1905, -1906, -1908, -1909; 365A13- 3036-00, -0001, -0002, -0003; or 365A13-3038-00, installed, except those with modification 0755B28 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as vibration during descent at high speed. This condition could result in failure of the horizontal stabilizer and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces AD 2010-23-02, Amendment 39-16491 (75 FR 68169, November 5, 2010). (d) Effective Date This AD becomes effective May 16, 2016. (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 Before further flight: (1) Revise the airspeed operating limitation in the Limitations section of the Rotorcraft Flight Manual (RFM) by making pen and ink changes or by inserting a copy of this AD into the RFM stating: ``The never-exceed speed (VNE) is limited to 150 knots indicated airspeed (KIAS)'' and ``The rate-of-descent (R/D) must not exceed 1,500 ft/min when the airspeed is beyond 140 KIAS.'' (2) Install one or more self-adhesive placards, with 6 millimeter red letters on white background, on the cockpit instrument panel in full view of the pilot and co-pilot to read as follows: ``VNE LIMITED TO 150 KIAS'' and ``R/D MUST NOT EXCEED 1,500 ft/min when airspeed is beyond 140 KIAS'' (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, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; 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. (h) Additional Information (1) Eurocopter Emergency Alert Service Bulletin (EASB) No. 01.00.60, 01.00.16, and 01.28, Revision 1, dated December 2, 2008, and Airbus Helicopters Service Bulletin No. AS365-55.00.06, Revision 0, dated November 14, 2014, which are not incorporated by reference, contain additional information about the subject of this final rule. For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641- 3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008-0204R1, dated May 21, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-4112. (i) Subject Joint Aircraft Service Component (JASC) Code 5310: Horizontal Stabilizer Structure. Issued in Fort Worth, Texas, on March 31, 2016. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-07981 Filed 4-8-16; 8:45 am] BILLING CODE 4910-13-P
![21234 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
detail the scope of the Agency’s 2016–08–07 Rolls-Royce plc: Amendment Propeller Directorate, 1200 District Avenue,
authority. 39–18483; Docket No. FAA–2015–4076; Burlington, MA 01803; phone: 781–238–
Directorate Identifier 2015–NE–30–AD. 7772; fax: 781–238–7199; email:
We are issuing this rulemaking under brian.kierstead@faa.gov.
the authority described in ‘‘Subtitle VII, (a) Effective Date (2) Refer to MCAI European Aviation
Part A, Subpart III, Section 44701: This AD becomes effective May 16, 2016. Safety Agency AD 2015–0187, dated
General requirements.’’ Under that September 9, 2015, for more information.
(b) Affected ADs
section, Congress charges the FAA with You may examine the MCAI in the AD
promoting safe flight of civil aircraft in None. docket on the Internet at http://
air commerce by prescribing regulations www.regulations.gov by searching for and
(c) Applicability
locating it in Docket No. FAA–2015–4076.
for practices, methods, and procedures This AD applies to Rolls-Royce plc RB211–
the Administrator finds necessary for 22B–02, RB211–22B (MOD 72–8700), RB211– (j) Material Incorporated by Reference
safety in air commerce. This regulation 524B–02, RB211–524B–B–02, RB211–524B2– None.
is within the scope of that authority 19, RB211–524B2–B–19, RB211–524B3–02, Issued in Burlington, Massachusetts, on
because it addresses an unsafe condition RB211–524B4–02, RB211–524B4–D–02, April 4, 2016.
that is likely to exist or develop on RB211–524C2–19, RB211–524C2–B–19,
Colleen M. D’Alessandro,
products identified in this rulemaking RB211–524D4–19, RB211–524D4–B–19,
RB211–524D4X–19, RB211–524D4X–B–19, Manager, Engine & Propeller Directorate,
action. RB211–524D4–39, RB211–524D4–B–39, Aircraft Certification Service.
Regulatory Findings RB211–524G2–19, RB211–524G3–19,
RB211–524–G2–T–19, RB211–524G3–T–19, [FR Doc. 2016–08092 Filed 4–8–16; 8:45 am]
We determined that this AD will not RB211–524H–36, RB211–524H2–19, RB211– BILLING CODE 4910–13–P
have federalism implications under 524H–T–36, and RB211–524H2–T–19
Executive Order 13132. This AD will turbofan engines, all serial numbers, with
not have a substantial direct effect on low-pressure turbine (LPT) support roller DEPARTMENT OF TRANSPORTATION
bearing, part number (P/N) LK30313 or P/N
the States, on the relationship between Federal Aviation Administration
UL29651, installed.
the national government and the States,
or on the distribution of power and (d) Reason
14 CFR Part 39
responsibilities among the various This AD was prompted by a report of a
levels of government. breach of the turbine casing and release of [Docket No. FAA–2015–4112; Directorate
engine debris through a hole in the engine Identifier 2014–SW–043–AD; Amendment
For the reasons discussed above, I
nacelle. We are issuing this AD to prevent 39–18471; AD 2016–07–26]
certify this AD:
failure of the LPT support roller bearing, loss RIN 2120–AA64
(1) Is not a ‘‘significant regulatory of radial position following LPT blade
action’’ under Executive Order 12866, failure, uncontained part release, damage to Airworthiness Directives; Airbus
(2) Is not a ‘‘significant rule’’ under the engine, and damage to the airplane.
Helicopters (previously Eurocopter
the DOT Regulatory Policies and (e) Actions and Compliance France)
Procedures (44 FR 11034, February 26,
Comply with this AD within the AGENCY: Federal Aviation
1979), compliance times specified, unless already
(3) Will not affect intrastate aviation Administration (FAA), DOT.
done. At the next shop visit or within 24
in Alaska to the extent that it justifies months after the effective date of this AD, ACTION: Final rule.
making a regulatory distinction, and whichever occurs first, remove from service
LPT support roller bearing, P/N LK30313 or
SUMMARY: We are superseding
(4) Will not have a significant Airworthiness Directive (AD) 2010–23–
economic impact, positive or negative, P/N UL29651, and replace with a part
eligible for installation. 02 for Eurocopter France (now Airbus
on a substantial number of small entities Helicopters) Model SA–365N, SA–
under the criteria of the Regulatory (f) Installation Prohibition 365N1, AS–365N2, and AS 365 N3
Flexibility Act. After the effective date of this AD, do not helicopters. AD 2010–23–02 required
install an LPT support roller bearing, P/N amending the Limitations section of the
List of Subjects in 14 CFR Part 39
LK30313 or P/N UL29651, onto any engine. Rotorcraft Flight Manual (RFM) to limit
Air transportation, Aircraft, Aviation (g) Definition the never-exceed velocity (VNE) to 150
safety, Incorporation by reference, Knots Indicated Air Speed (KIAS) and
For the purpose of this AD, a ‘‘shop visit’’
Safety. is defined as induction of an engine into the to add a 1,500 ft/minute rate of descent
Adoption of the Amendment shop for maintenance involving the (R/D) limitation beyond 140 KIAS.
separation of pairs of major mating engine Since we issued AD 2010–23–02, a
Accordingly, under the authority flanges, except that the separation of engine design change designated as
delegated to me by the Administrator, flanges solely for the purposes of modification (MOD) 0755B28 improved
the FAA amends 14 CFR part 39 as transportation without subsequent engine the dynamic behavior of the horizontal
follows: maintenance does not constitute an engine stabilizer such that AD actions are not
shop visit.
required. This new AD retains the
PART 39—AIRWORTHINESS (h) Alternative Methods of Compliance requirements of AD 2010–23–01 and
DIRECTIVES (AMOCs) revises the applicability to exclude
The Manager, Engine Certification Office, helicopters with MOD 0755B28. We are
■ 1. The authority citation for part 39 FAA, may approve AMOCs for this AD. Use issuing this AD to exclude certain
continues to read as follows:
jstallworth on DSK7TPTVN1PROD with RULES
the procedures found in 14 CFR 39.19 to helicopters from the applicability and
Authority: 49 U.S.C. 106(g), 40113, 44701. make your request. You may email your restrict the VNE on other helicopters to
request to: ANE-AD-AMOC@faa.gov. prevent failure of the horizontal
§ 39.13 [Amended]
(i) Related Information stabilizer and subsequent loss of control
■ 2. The FAA amends § 39.13 by adding (1) For more information about this AD, of the helicopter.
the following new airworthiness contact Brian Kierstead, Aerospace Engineer, DATES: This AD is effective May 16,
directive (AD): Engine Certification Office, FAA, Engine & 2016.
VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1](https://thefederalregister.org/doc/81_FR_21303/page/1.svg)
![21236 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
(3) Will not affect intrastate aviation Flight Manual (RFM) by making pen and ink DEPARTMENT OF TRANSPORTATION
in Alaska to the extent that a regulatory; changes or by inserting a copy of this AD into
and the RFM stating: ‘‘The never-exceed speed Federal Aviation Administration
(4) Will not have a significant (VNE) is limited to 150 knots indicated
economic impact, positive or negative, airspeed (KIAS)’’ and ‘‘The rate-of-descent 14 CFR Part 39
on a substantial number of small entities (R/D) must not exceed 1,500 ft/min when the
airspeed is beyond 140 KIAS.’’ [Docket No. FAA-2014-0775; Directorate
under the criteria of the Regulatory Identifier 2014–NM–046–AD; Amendment
Flexibility Act. (2) Install one or more self-adhesive
39–18467; AD 2016–07–22]
placards, with 6 millimeter red letters on
List of Subjects in 14 CFR Part 39 white background, on the cockpit instrument RIN 2120–AA64
Air transportation, Aircraft, Aviation panel in full view of the pilot and co-pilot
safety, Incorporation by reference, to read as follows: ‘‘VNE LIMITED TO 150 Airworthiness Directives; Airbus
Safety. KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 Airplanes
ft/min when airspeed is beyond 140 KIAS’’
Adoption of the Amendment AGENCY: Federal Aviation
(g) Alternative Methods of Compliance Administration (FAA), Department of
Accordingly, under the authority (AMOCs) Transportation (DOT).
delegated to me by the Administrator,
(1) The Manager, Safety Management ACTION: Final rule.
the FAA amends 14 CFR part 39 as Group, FAA, may approve AMOCs for this
follows: AD. Send your proposal to: Robert Grant, SUMMARY: We are adopting a new
PART 39—AIRWORTHINESS Aviation Safety Engineer, Safety Management airworthiness directive (AD) for all
DIRECTIVES
Group, Rotorcraft Directorate, FAA, 10101 Airbus Model A300 B4–600, B4–600R,
Hillwood Pkwy., Fort Worth, Texas 76177; and F4–600R series airplanes, Model
■ 1. The authority citation for part 39 telephone (817) 222–5110; email 9-asw-ftw- A300 C4–605R Variant F airplanes
continues to read as follows: amoc-requests@faa.gov. (collectively called Model A300–600
(2) For operations conducted under a 14 series airplanes), and Model A310 series
Authority: 49 U.S.C. 106(g), 40113, 44701. CFR part 119 operating certificate or under airplanes. This AD was prompted by
§ 39.13 [Amended] 14 CFR part 91, subpart K, we suggest that reports of insufficient clearance for the
you notify your principal inspector, or electrical wiring bundles in the leading
■ 2. The FAA amends § 39.13 by lacking a principal inspector, the manager of
removing Airworthiness Directive (AD) and trailing edges of the right-hand (RH)
the local flight standards district office or
2010–23–02, Amendment 39–16491 (75 and left-hand (LH) wings. This AD
certificate holding district office, before
FR 68169, November 5, 2010), and operating any aircraft complying with this
requires modifying the electrical routing
adding the following new AD: AD through an AMOC. installation at the RH and LH wings. We
are issuing this AD to prevent
2016–07–26 Airbus Helicopters (previously (h) Additional Information insufficient clearance of electrical
Eurocopter France): Amendment 39–
18471; Docket No. FAA–2015–4112; (1) Eurocopter Emergency Alert Service wiring bundles located in the leading
Directorate Identifier 2014–SW–043–AD. Bulletin (EASB) No. 01.00.60, 01.00.16, and and trailing edges of the RH and LH
01.28, Revision 1, dated December 2, 2008, wings, which could lead to chafing
(a) Applicability and Airbus Helicopters Service Bulletin No. damage and arcing, possibly resulting in
This AD applies to Model SA–365N, SA– AS365–55.00.06, Revision 0, dated November an on-board fire.
365N1, AS–365N2, and AS 365 N3 14, 2014, which are not incorporated by DATES: This AD becomes effective May
helicopters, with a horizontal stabilizer, part reference, contain additional information
number 365A13–3030–1901, –1902, –1903, 16, 2016.
about the subject of this final rule. For
–1904, –1905, –1906, –1908, –1909; 365A13– The Director of the Federal Register
service information identified in this final
3036–00, –0001, –0002, –0003; or 365A13– approved the incorporation by reference
rule, contact Airbus Helicopters, Inc., 2701
3038–00, installed, except those with
N. Forum Drive, Grand Prairie, TX 75052;
of certain publications listed in this AD
modification 0755B28 installed, certificated as of May 16, 2016.
in any category. telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at http:// ADDRESSES: You may examine the AD
(b) Unsafe Condition www.airbushelicopters.com/techpub. You docket on the Internet at http://
This AD defines the unsafe condition as may review a copy of the service information www.regulations.gov/
vibration during descent at high speed. This at the FAA, Office of the Regional Counsel, #!docketDetail;D=FAA-2014-0775; or in
condition could result in failure of the Southwest Region, 10101 Hillwood Pkwy., person at the Docket Management
horizontal stabilizer and subsequent loss of Room 6N–321, Fort Worth, TX 76177. Facility, U.S. Department of
control of the helicopter. (2) The subject of this AD is addressed in Transportation, Docket Operations, M–
(c) Affected ADs European Aviation Safety Agency (EASA) AD 30, West Building Ground Floor, Room
No. 2008–0204R1, dated May 21, 2014. You W12–140, 1200 New Jersey Avenue SE.,
This AD replaces AD 2010–23–02,
Amendment 39–16491 (75 FR 68169, may view the EASA AD on the Internet at Washington, DC.
November 5, 2010). http://www.regulations.gov in Docket No. For service information identified in
FAA–2015–4112.
(d) Effective Date this final rule, contact Airbus SAS,
(i) Subject Airworthiness Office—EAW, 1 Rond
This AD becomes effective May 16, 2016.
Joint Aircraft Service Component (JASC) Point Maurice Bellonte, 31707 Blagnac
(e) Compliance Code 5310: Horizontal Stabilizer Structure. Cedex, France; telephone +33 5 61 93 36
You are responsible for performing each 96; fax +33 5 61 93 44 51; email
jstallworth on DSK7TPTVN1PROD with RULES
action required by this AD within the Issued in Fort Worth, Texas, on March 31,
account.airworth-eas@airbus.com;
specified compliance time unless it has 2016.
Internet http://www.airbus.com. You
already been accomplished prior to that time. James A. Grigg, may view this referenced service
(f) Required Actions Acting Manager, Rotorcraft Directorate, information at the FAA, Transport
Aircraft Certification Service. Airplane Directorate, 1601 Lind Avenue
Before further flight:
(1) Revise the airspeed operating limitation [FR Doc. 2016–07981 Filed 4–8–16; 8:45 am] SW., Renton, WA. For information on
in the Limitations section of the Rotorcraft BILLING CODE 4910–13–P the availability of this material at the
VerDate Sep<11>2014 14:13 Apr 08, 2016 Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\11APR1.SGM 11APR1](https://thefederalregister.org/doc/81_FR_21303/page/3.svg)
Document Created: 2016-04-09 00:11:21
Document Modified: 2016-04-09 00:11:21
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective May 16, 2016. | |
| Contact | Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 81 FR 21234 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR