81 FR 11407 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 43 (March 4, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 43 (March 4, 2016)
| Page Range | 11407-11409 | |
| FR Document | 2016-04678 |
[Federal Register Volume 81, Number 43 (Friday, March 4, 2016)] [Rules and Regulations] [Pages 11407-11409] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-04678] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 81, No. 43 / Friday, March 4, 2016 / Rules and Regulations [[Page 11407]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2568; Directorate Identifier 2014-SW-026-AD; Amendment 39-18424; AD 2016-05-06] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2014-07-52 for certain Airbus Helicopters (previously Eurocopter France) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2014-07- 52 required repetitively inspecting certain reinforcement angles of the rear structure to tailboom junction frame (reinforcement angles) for a crack at 10 hour time-in-service (TIS) intervals, repairing any cracked reinforcement angle, and allowed an optional repetitive inspection with a 165 hour TIS inspection interval as a terminating action for the 10 hour TIS inspections. This AD retains the inspection requirements of AD 2014-07-52 and requires the inspection of the area around each reinforcement angle screw hole as terminating action to the 10 hour TIS inspections. We are issuing this AD to detect a crack in the reinforcement angle, which if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter. DATES: This AD is effective April 8, 2016. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of June 25, 2014 (79 FR 33054, June 10, 2014). 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 review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 2568; 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 AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, 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, TX 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 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014) and add a new AD. AD 2014-07-52 applied to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with Modification (MOD) 07 3215 or with a reinforcement angle part number (P/N) 350A08.2493.21 or P/N 350A08.2493.23 installed. AD 2014-07-52 required, for helicopters with 640 or more hours TIS, repetitively inspecting each reinforcement angle for a crack every 10 hours TIS. As an optional action, AD 2014-07-52 allowed a repetitive 165 hour TIS inspection of the reinforcement angle under each attaching screw for a crack. AD 2014-07-52 was prompted by Emergency AD No. 2014- 0076-E, dated March 25, 2014, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advises that during the inspection of several AS355 helicopters, cracks found in the reinforcement angles had initiated on the non-visible surface of the angle, and that this condition, if not corrected, could lead to further crack propagation and subsequent loss of the tailboom, resulting in loss of control of the helicopter. The EASA AD requires repetitive inspections of the reinforcement angles, and states that a terminating action is under investigation. The NPRM published in the Federal Register on July 23, 2015 (80 FR 43645). The NPRM proposed to retain the 10 hour TIS repetitive inspections of the reinforcement angle and require (instead of allow as an option) the 165 hour TIS inspection of the junction frame bores as terminating action for the 10 hour TIS inspections. The NPRM also proposed to revise the applicability to only include helicopters with reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23, and not include helicopters with MOD 07 3215. Since MOD 07 3215 installed reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23, AD 2014- 07-52 was written to apply to helicopters with either the reinforcement angle P/Ns or with MOD 07 3215, so that operators could more easily determine whether AD 2014-07-52 applied to their aircraft. Airbus Helicopters then developed MOD 07 3232, which removes reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23. We removed MOD 07 3215 from the applicability because we did not want the AD to apply to a helicopter with both MOD 07 3215 and MOD 07 3232 in its aircraft records, as it would not have reinforcement angle P/N 350A08.2493.21 or P/N 350A08.2493.23 installed. The proposed requirements were intended to detect a [[Page 11408]] crack in the reinforcement angle, which if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter. Since the NPRM was issued, a group email address has been established for requesting an FAA alternative method of compliance for a helicopter of foreign design. We have revised this contact information in this final rule to reflect the new email address. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (79 FR 33054, June 10, 2014). 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 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 and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Differences Between This AD and the EASA AD This AD is not applicable to the AS350BB as that model is not type certificated in the U.S. This AD applies to Airbus Helicopters Model AS350C and AS350D1 helicopters because these helicopters have a similar design. Finally, the EASA AD requires operators to contact Airbus Helicopters if there is a crack, and this AD does not, however it does require repairing the crack before further flight. Related Service Information Under 1 CFR Part 51 Airbus Helicopters issued Emergency Alert Service Bulletin (EASB) No. 05.00.70 for Model AS350B, BA, BB, Bl, B2, B3, and D helicopters, and EASB No. 05.00.62 for Model AS355E, F, F1, F2, N, and NP helicopters, both Revision 0 and dated March 24, 2014. EASB No. 05.00.70 and EASB No. 05.00.62 describe procedures for inspecting the angle reinforcements for a crack. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 822 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per work-hour, inspecting the reinforcement angles for a crack without removing the screws requires 1.0 work-hour, for a cost per helicopter of $85 and a total cost of $69,870 for the U.S. fleet, per inspection cycle. Removing the screws and inspecting the reinforcement angle requires 2 work-hours, for a cost per helicopter of $170 and a total cost of $139,740 for the U.S. fleet, per inspection cycle. If required, repairing a cracked reinforcement angle requires about 10 work-hours, and required parts cost about $300, for a total cost per helicopter of $1,150. 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 helicopters identified in this rulemaking action. Regulatory Findings 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); (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 and placed it in the AD docket. 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) 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014), and adding the following new AD: 2016-05-06 Airbus Helicopters (previously Eurocopter France): Amendment 39-18424; Docket No. FAA-2015-2568; Directorate Identifier 2014-SW-026-AD. (a) Applicability This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, with a reinforcement angle part number (P/N) 350A08.2493.21 or P/N 350A08.2493.23 installed, certificated in any category. Note 1 to paragraph (a) of this AD: Helicopters with Modification (MOD) 073232 do not have P/N 350A08.2493.21 or P/N 350A08.2493.23 installed. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a rear structure to tailboom junction frame reinforcement angle (reinforcement angle), which if not detected could result in loss of the tail boom and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014). [[Page 11409]] (d) Effective Date This AD becomes effective April 8, 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 (1) For helicopters with 640 or more hours time-in-service (TIS) since installation of MOD 073215 or since installation of an applicable reinforcement angle, within 10 hours TIS, and thereafter at intervals not exceeding 10 hours TIS, inspect each reinforcement angle for a crack as depicted in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.70 for Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters and Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.62 for AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, both Revision 0 and dated March 24, 2014. (2) If there is a crack, before further flight, repair the reinforcement angle in a manner approved by the manager listed in paragraph (h)(1) of this AD. (3) Within 165 hours TIS after the first inspection required by paragraph (f)(1) of this AD, and thereafter at intervals not exceeding 165 hours TIS, remove screw No. 5 from the reinforcement angle, thoroughly clean the area around the hole and inspect the reinforcement angle for a crack. If there is not a crack, reinstall the screw. Sequentially repeat the steps required by this paragraph for screws No. 6 through No. 12. If there is a crack, comply with paragraph (f)(2) of this AD. Accomplishment of the inspection required by this paragraph terminates the repetitive inspections required by paragraph (f)(1) of this AD. (g) Special Flight Permits Special flight permits are prohibited. (h) 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, 10101 Hillwood Pkwy, Fort Worth, TX 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. (3) AMOCs approved previously in accordance with AD 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014) are approved as AMOCs for the corresponding requirements of paragraph (f)(2) of this AD. (i) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD 2014-0076-E, dated March 25, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-2568. (j) Subject Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tailboom. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on June 25, 2014 (79 FR 33054, June 10, 2014). (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.62, Revision 0, dated March 24, 2014. (ii) Airbus Helicopters EASB No. 05.00.70, Revision 0, dated March 24, 2014. Note 2 to paragraph (k)(3): Airbus Helicopters EASB No. 05.00.62 and EASB No. 05.00.70, both Revision 0 and dated March 24, 2014, are co-published as one document along with Airbus Helicopters EASB No. 05.00.45 and EASB No. 05.00.41, both Revision 0 and dated March 24, 2014, which are not incorporated by reference in this AD. (4) For Airbus Helicopters 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. (5) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on February 25, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-04678 Filed 3-3-16; 8:45 am] BILLING CODE 4910-13-P
![11407
Rules and Regulations Federal Register
Vol. 81, No. 43
Friday, March 4, 2016
This section of the FEDERAL REGISTER The Director of the Federal Register installed. AD 2014–07–52 required, for
contains regulatory documents having general approved the incorporation by reference helicopters with 640 or more hours TIS,
applicability and legal effect, most of which of certain documents listed in this AD repetitively inspecting each
are keyed to and codified in the Code of as of June 25, 2014 (79 FR 33054, June reinforcement angle for a crack every 10
Federal Regulations, which is published under 10, 2014). hours TIS. As an optional action, AD
50 titles pursuant to 44 U.S.C. 1510.
ADDRESSES: For service information 2014–07–52 allowed a repetitive 165
The Code of Federal Regulations is sold by identified in this final rule, contact hour TIS inspection of the
the Superintendent of Documents. Prices of Airbus Helicopters, Inc., 2701 N. Forum reinforcement angle under each
new books are listed in the first FEDERAL Drive, Grand Prairie, TX 75052; attaching screw for a crack. AD 2014–
REGISTER issue of each week. telephone (972) 641–0000 or (800) 232– 07–52 was prompted by Emergency AD
0323; fax (972) 641–3775; or at http:// No. 2014–0076–E, dated March 25,
www.airbushelicopters.com/techpub. 2014, issued by EASA, which is the
DEPARTMENT OF TRANSPORTATION You may review the referenced service Technical Agent for the Member States
information at the FAA, Office of the of the European Union. EASA advises
Federal Aviation Administration that during the inspection of several
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321, AS355 helicopters, cracks found in the
14 CFR Part 39 reinforcement angles had initiated on
Fort Worth, TX 76177.
[Docket No. FAA–2015–2568; Directorate the non-visible surface of the angle, and
Identifier 2014–SW–026–AD; Amendment Examining the AD Docket that this condition, if not corrected,
39–18424; AD 2016–05–06] You may examine the AD docket on could lead to further crack propagation
RIN 2120–AA64 the Internet at http:// and subsequent loss of the tailboom,
www.regulations.gov by searching for resulting in loss of control of the
Airworthiness Directives; Airbus and locating Docket No. FAA–2015– helicopter. The EASA AD requires
Helicopters (Previously Eurocopter 2568; or in person at the Docket repetitive inspections of the
France) Helicopters Operations Office between 9 a.m. and 5 reinforcement angles, and states that a
p.m., Monday through Friday, except terminating action is under
AGENCY: Federal Aviation Federal holidays. The AD docket investigation.
Administration (FAA), DOT. contains this AD, the European Aviation The NPRM published in the Federal
ACTION: Final rule. Safety Agency (EASA) AD, any Register on July 23, 2015 (80 FR 43645).
incorporated-by-reference service The NPRM proposed to retain the 10
SUMMARY: We are superseding information, the economic evaluation, hour TIS repetitive inspections of the
Airworthiness Directive (AD) 2014–07– any comments received, and other reinforcement angle and require (instead
52 for certain Airbus Helicopters information. The street address for the of allow as an option) the 165 hour TIS
(previously Eurocopter France) Model Docket Operations Office (phone: 800– inspection of the junction frame bores as
AS350B, AS350BA, AS350B1, 647–5527) is U.S. Department of terminating action for the 10 hour TIS
AS350B2, AS350B3, AS350C, AS350D, Transportation, Docket Operations inspections. The NPRM also proposed
AS350D1, AS355E, AS355F, AS355F1, Office, M–30, West Building Ground to revise the applicability to only
AS355F2, AS355N, and AS355NP Floor, Room W12–140, 1200 New Jersey include helicopters with reinforcement
helicopters. AD 2014–07–52 required Avenue SE., Washington, DC 20590. angle P/N 350A08.2493.21 and P/N
repetitively inspecting certain 350A08.2493.23, and not include
FOR FURTHER INFORMATION CONTACT:
reinforcement angles of the rear helicopters with MOD 07 3215. Since
Robert Grant, Aviation Safety Engineer,
structure to tailboom junction frame MOD 07 3215 installed reinforcement
Safety Management Group, FAA, 10101
(reinforcement angles) for a crack at 10 angle P/N 350A08.2493.21 and P/N
Hillwood Pkwy., Fort Worth, TX 76177;
hour time-in-service (TIS) intervals, 350A08.2493.23, AD 2014–07–52 was
telephone (817) 222–5110; email
repairing any cracked reinforcement written to apply to helicopters with
robert.grant@faa.gov.
angle, and allowed an optional either the reinforcement angle P/Ns or
SUPPLEMENTARY INFORMATION:
repetitive inspection with a 165 hour with MOD 07 3215, so that operators
TIS inspection interval as a terminating Discussion could more easily determine whether
action for the 10 hour TIS inspections. We issued a notice of proposed AD 2014–07–52 applied to their aircraft.
This AD retains the inspection rulemaking (NPRM) to amend 14 CFR Airbus Helicopters then developed
requirements of AD 2014–07–52 and part 39 to remove AD 2014–07–52, MOD 07 3232, which removes
requires the inspection of the area Amendment 39–17858 (79 FR 33054, reinforcement angle P/N
around each reinforcement angle screw June 10, 2014) and add a new AD. AD 350A08.2493.21 and P/N
hole as terminating action to the 10 hour 2014–07–52 applied to Airbus 350A08.2493.23. We removed MOD 07
TIS inspections. We are issuing this AD Helicopters Model AS350B, AS350BA, 3215 from the applicability because we
to detect a crack in the reinforcement
jstallworth on DSK7TPTVN1PROD with RULES
AS350B1, AS350B2, AS350B3, AS350C, did not want the AD to apply to a
angle, which if not corrected, could AS350D, AS350D1, AS355E, AS355F, helicopter with both MOD 07 3215 and
result in loss of the tailboom and AS355F1, AS355F2, AS355N, and MOD 07 3232 in its aircraft records, as
subsequent loss of control of the AS355NP helicopters with Modification it would not have reinforcement angle
helicopter. (MOD) 07 3215 or with a reinforcement P/N 350A08.2493.21 or P/N
DATES: This AD is effective April 8, angle part number (P/N) 350A08.2493.23 installed. The proposed
2016. 350A08.2493.21 or P/N 350A08.2493.23 requirements were intended to detect a
VerDate Sep<11>2014 13:44 Mar 03, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\04MRR1.SGM 04MRR1](https://thefederalregister.org/doc/81_FR_11450/page/1.svg)
![11408 Federal Register / Vol. 81, No. 43 / Friday, March 4, 2016 / Rules and Regulations
crack in the reinforcement angle, which reasonably available because the (2) Is not a ‘‘significant rule’’ under
if not corrected, could result in loss of interested parties have access to it DOT Regulatory Policies and Procedures
the tailboom and subsequent loss of through their normal course of business (44 FR 11034, February 26, 1979);
control of the helicopter. or by the means identified in the (3) Will not affect intrastate aviation
Since the NPRM was issued, a group ADDRESSES section. in Alaska to the extent that it justifies
email address has been established for making a regulatory distinction; and
requesting an FAA alternative method Costs of Compliance
(4) Will not have a significant
of compliance for a helicopter of foreign We estimate that this AD affects 822 economic impact, positive or negative,
design. We have revised this contact helicopters of U.S. Registry. We estimate on a substantial number of small entities
information in this final rule to reflect that operators may incur the following under the criteria of the Regulatory
the new email address. costs in order to comply with this AD. Flexibility Act.
Comments At an average labor rate of $85 per work- We prepared an economic evaluation
hour, inspecting the reinforcement of the estimated costs to comply with
We gave the public the opportunity to angles for a crack without removing the this AD and placed it in the AD docket.
participate in developing this AD, but screws requires 1.0 work-hour, for a cost
we did not receive any comments on the List of Subjects in 14 CFR Part 39
per helicopter of $85 and a total cost of
NPRM (79 FR 33054, June 10, 2014). $69,870 for the U.S. fleet, per inspection Air transportation, Aircraft, Aviation
FAA’s Determination cycle. Removing the screws and safety, Incorporation by reference,
inspecting the reinforcement angle Safety.
These helicopters have been approved
requires 2 work-hours, for a cost per Adoption of the Amendment
by the aviation authority of France and
helicopter of $170 and a total cost of
are approved for operation in the United Accordingly, under the authority
$139,740 for the U.S. fleet, per
States. Pursuant to our bilateral delegated to me by the Administrator,
inspection cycle. If required, repairing a
agreement with France, EASA, its the FAA amends 14 CFR part 39 as
cracked reinforcement angle requires
technical representative, has notified us follows:
about 10 work-hours, and required parts
of the unsafe condition described in the
cost about $300, for a total cost per
EASA AD. We are issuing this AD PART 39—AIRWORTHINESS
helicopter of $1,150.
because we evaluated all information DIRECTIVES
provided by EASA and determined the Authority for This Rulemaking
unsafe condition exists and is likely to ■ 1. The authority citation for part 39
exist or develop on other helicopters of Title 49 of the United States Code continues to read as follows:
these same type designs and that air specifies the FAA’s authority to issue
Authority: 49 U.S.C. 106(g), 40113, 44701.
safety and the public interest require rules on aviation safety. Subtitle I,
adopting the AD requirements as section 106, describes the authority of § 39.13 [Amended]
proposed. the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more ■ 2. The FAA amends § 39.13 by
Interim Action detail the scope of the Agency’s removing Airworthiness Directive (AD)
authority. 2014–07–52, Amendment 39–17858 (79
We consider this AD to be an interim FR 33054, June 10, 2014), and adding
action. If final action is later identified, We are issuing this rulemaking under the following new AD:
we might consider further rulemaking the authority described in Subtitle VII,
then. Part A, Subpart III, Section 44701: 2016–05–06 Airbus Helicopters (previously
Eurocopter France): Amendment 39–
‘‘General requirements.’’ Under that
Differences Between This AD and the 18424; Docket No. FAA–2015–2568;
section, Congress charges the FAA with Directorate Identifier 2014–SW–026–AD.
EASA AD
promoting safe flight of civil aircraft in
This AD is not applicable to the air commerce by prescribing regulations (a) Applicability
AS350BB as that model is not type for practices, methods, and procedures This AD applies to Airbus Helicopters
certificated in the U.S. This AD applies the Administrator finds necessary for Model AS350B, AS350BA, AS350B1,
to Airbus Helicopters Model AS350C safety in air commerce. This regulation AS350B2, AS350B3, AS350C, AS350D,
and AS350D1 helicopters because these is within the scope of that authority AS350D1, AS355E, AS355F, AS355F1,
helicopters have a similar design. AS355F2, AS355N, and AS355NP
because it addresses an unsafe condition
Finally, the EASA AD requires operators helicopters, with a reinforcement angle part
that is likely to exist or develop on number (P/N) 350A08.2493.21 or P/N
to contact Airbus Helicopters if there is helicopters identified in this rulemaking 350A08.2493.23 installed, certificated in any
a crack, and this AD does not, however action. category.
it does require repairing the crack before
Regulatory Findings Note 1 to paragraph (a) of this AD:
further flight. Helicopters with Modification (MOD) 073232
Related Service Information Under 1 This AD will not have federalism do not have P/N 350A08.2493.21 or P/N
CFR Part 51 implications under Executive Order 350A08.2493.23 installed.
13132. This AD will not have a (b) Unsafe Condition
Airbus Helicopters issued Emergency
substantial direct effect on the States, on
Alert Service Bulletin (EASB) No. This AD defines the unsafe condition as a
the relationship between the national
05.00.70 for Model AS350B, BA, BB, Bl, crack in a rear structure to tailboom junction
government and the States, or on the frame reinforcement angle (reinforcement
B2, B3, and D helicopters, and EASB
distribution of power and
jstallworth on DSK7TPTVN1PROD with RULES
No. 05.00.62 for Model AS355E, F, F1, angle), which if not detected could result in
responsibilities among the various loss of the tail boom and subsequent loss of
F2, N, and NP helicopters, both
levels of government. control of the helicopter.
Revision 0 and dated March 24, 2014.
EASB No. 05.00.70 and EASB No. For the reasons discussed above, I (c) Affected ADs
05.00.62 describe procedures for certify that this AD:
This AD supersedes AD 2014–07–52,
inspecting the angle reinforcements for (1) Is not a ‘‘significant regulatory Amendment 39–17858 (79 FR 33054, June
a crack. This service information is action’’ under Executive Order 12866; 10, 2014).
VerDate Sep<11>2014 13:44 Mar 03, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\04MRR1.SGM 04MRR1](https://thefederalregister.org/doc/81_FR_11450/page/2.svg)
![Federal Register / Vol. 81, No. 43 / Friday, March 4, 2016 / Rules and Regulations 11409
(d) Effective Date (i) Additional Information DEPARTMENT OF TRANSPORTATION
This AD becomes effective April 8, 2016. The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD Federal Aviation Administration
(e) Compliance
2014–0076–E, dated March 25, 2014. You
You are responsible for performing each may view the EASA AD on the Internet at 14 CFR Part 39
action required by this AD within the http://www.regulations.gov in Docket No.
specified compliance time unless it has
FAA–2015–2568. [Docket No. FAA–2015–3607; Directorate
already been accomplished prior to that time.
Identifier 2015–CE–010–AD; Amendment
(j) Subject 39–18398; AD 2016–04–04]
(f) Required Actions
(1) For helicopters with 640 or more hours Joint Aircraft Service Component (JASC)
time-in-service (TIS) since installation of Code: 5302: Rotorcraft Tailboom. RIN 2120–AA64
MOD 073215 or since installation of an (k) Material Incorporated by Reference
applicable reinforcement angle, within 10 Airworthiness Directives; M7
hours TIS, and thereafter at intervals not (1) The Director of the Federal Register Aerospace LLC Airplanes
exceeding 10 hours TIS, inspect each approved the incorporation by reference
reinforcement angle for a crack as depicted (IBR) of the service information listed in this AGENCY: Federal Aviation
in Figure 1 of Airbus Helicopters Emergency paragraph under 5 U.S.C. 552(a) and 1 CFR Administration (FAA), DOT.
Alert Service Bulletin No. 05.00.70 for Model part 51. ACTION: Final rule.
AS350B, AS350BA, AS350B1, AS350B2, (2) You must use this service information
AS350B3, AS350C, AS350D, and AS350D1 as applicable to do the actions required by SUMMARY: We are adopting a new
helicopters and Airbus Helicopters this AD, unless the AD specifies otherwise. airworthiness directive (AD) for all M7
Emergency Alert Service Bulletin No. (3) The following service information was Aerospace LLC Models SA26–AT,
05.00.62 for AS355E, AS355F, AS355F1, approved for IBR on June 25, 2014 (79 FR SA226–T(B), SA226–AT, SA226–T,
AS355F2, AS355N, and AS355NP 33054, June 10, 2014). SA226–TC, SA227–AC (C–26A),
helicopters, both Revision 0 and dated March (i) Airbus Helicopters Emergency Alert SA227–AT, SA227–BC (C–26A),
24, 2014. Service Bulletin (EASB) No. 05.00.62, SA227–CC, SA227–DC (C–26B), and
(2) If there is a crack, before further flight, Revision 0, dated March 24, 2014.
repair the reinforcement angle in a manner
SA227–TT airplanes. This AD was
(ii) Airbus Helicopters EASB No. 05.00.70, prompted by information that the
approved by the manager listed in paragraph Revision 0, dated March 24, 2014.
(h)(1) of this AD. airplane flight manual (AFM) does not
(3) Within 165 hours TIS after the first Note 2 to paragraph (k)(3): Airbus provide adequate guidance in the
inspection required by paragraph (f)(1) of this Helicopters EASB No. 05.00.62 and EASB handling of engine failures, which may
AD, and thereafter at intervals not exceeding No. 05.00.70, both Revision 0 and dated lead to reliance on the negative torque
165 hours TIS, remove screw No. 5 from the March 24, 2014, are co-published as one system (NTS) for reducing drag. This
reinforcement angle, thoroughly clean the document along with Airbus Helicopters condition could lead the pilot to not
area around the hole and inspect the EASB No. 05.00.45 and EASB No. 05.00.41, fully feather the propeller with
reinforcement angle for a crack. If there is not both Revision 0 and dated March 24, 2014, consequent loss of control. This AD
a crack, reinstall the screw. Sequentially which are not incorporated by reference in requires inserting updates into the
repeat the steps required by this paragraph this AD. airplane flight manual (AFM) and/or the
for screws No. 6 through No. 12. If there is (4) For Airbus Helicopters service pilot operating handbook (POH) that
a crack, comply with paragraph (f)(2) of this
information identified in this final rule, will clearly establish that the NTS is not
AD. Accomplishment of the inspection
contact Airbus Helicopters, Inc., 2701 N. designed to automatically feather the
required by this paragraph terminates the
repetitive inspections required by paragraph Forum Drive, Grand Prairie, TX 75052; propeller but only to provide drag
(f)(1) of this AD. telephone (972) 641–0000 or (800) 232–0323; protection. We are issuing this AD to
fax (972) 641–3775; or at http:// correct the unsafe condition on these
(g) Special Flight Permits www.airbushelicopters.com/techpub. products.
Special flight permits are prohibited. (5) You may view this service information
at FAA, Office of the Regional Counsel, DATES: This AD is effective April 8,
(h) Alternative Methods of Compliance 2016.
(AMOCs) Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For The Director of the Federal Register
(1) The Manager, Safety Management information on the availability of this approved the incorporation by reference
Group, FAA, may approve AMOCs for this of certain publications listed in this AD
material at the FAA, call (817) 222–5110.
AD. Send your proposal to: Robert Grant, as of April 8, 2016.
(6) You may view this service information
Aviation Safety Engineer, Safety Management
that is incorporated by reference at the ADDRESSES: For service information
Group, FAA, 10101 Hillwood Pkwy, Fort
Worth, TX 76177; telephone (817) 222–5110; National Archives and Records identified in this AD, contact M7
email 9-ASW-FTW-AMOC-Requests@faa.gov. Administration (NARA). For information on Aerospace LLC, 10823 NE Entrance
(2) For operations conducted under a 14 the availability of this material at NARA, call Road, San Antonio, Texas 78216; phone:
CFR part 119 operating certificate or under (202) 741–6030, or go to: http:// (210) 824–9421; fax: (210) 804–7766;
14 CFR part 91, subpart K, we suggest that www.archives.gov/federal-register/cfr/ibr- Internet: http://www.elbitsystems-
you notify your principal inspector, or locations.html. us.com; email: MetroTech@
lacking a principal inspector, the manager of M7Aerospace.com. You may view this
Issued in Fort Worth, Texas, on February
the local flight standards district office or referenced service information at the
certificate holding district office, before 25, 2016.
Scott A. Horn,
FAA, Small Airplane Directorate, 901
jstallworth on DSK7TPTVN1PROD with RULES
operating any aircraft complying with this
Locust, Kansas City, Missouri 64106.
AD through an AMOC. Acting Manager, Rotorcraft Directorate,
(3) AMOCs approved previously in
For information on the availability of
Aircraft Certification Service.
accordance with AD 2014–07–52, this material at the FAA, call 816–329–
[FR Doc. 2016–04678 Filed 3–3–16; 8:45 am]
Amendment 39–17858 (79 FR 33054, June 4148. It is also available on the Internet
10, 2014) are approved as AMOCs for the BILLING CODE 4910–13–P at http://www.regulations.gov by
corresponding requirements of paragraph searching for and locating Docket No.
(f)(2) of this AD. FAA–2015–3607.
VerDate Sep<11>2014 13:44 Mar 03, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\04MRR1.SGM 04MRR1](https://thefederalregister.org/doc/81_FR_11450/page/3.svg)
Document Created: 2018-02-02 15:05:57
Document Modified: 2018-02-02 15:05:57
| 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 April 8, 2016. | |
| Contact | Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 81 FR 11407 | |
| 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