80 FR 14297 - Airworthiness Directives; Agusta S.p.A. Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 53 (March 19, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 53 (March 19, 2015)
| Page Range | 14297-14299 | |
| FR Document | 2015-05715 |
[Federal Register Volume 80, Number 53 (Thursday, March 19, 2015)] [Rules and Regulations] [Pages 14297-14299] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-05715] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0579; Directorate Identifier 2014-SW-020-AD; Amendment 39-18115; AD 2015-05-05] RIN 2120-AA64 Airworthiness Directives; Agusta S.p.A. Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2014-04-14 for Agusta S.p.A. (Agusta) Model A109S, AW109SP, A119, and AW119 MKII helicopters. AD 2014-04-14 required removing certain rod end assemblies from service because of reports of fractures. This new AD retains the requirements of AD 2014-04-14 but expands the scope of applicable rod end assemblies. This AD was prompted by reports of additional fractured rod end assemblies. We are issuing this AD to prevent failure of a rod end assembly, which could result in damage to the main rotor assembly and loss of control of the helicopter. DATES: This AD is effective April 23, 2015. ADDRESSES: For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331- 664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may view this referenced service information at the FAA, Office of the Regional Counsel, [[Page 14298]] Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, 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, 2601 Meacham Blvd., Fort Worth, Texas 76137; 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 2014-04-14, Amendment 39-17773 (79 FR 11699, March 3, 2014) for Agusta Model A109S, AW109SP, A119, and AW119 MKII helicopters with a main rotor lag damper assembly (lag damper), part number (P/N) 109-0112-39-103, 109-0112-39-105, 109-0112-05-105, or 109- 0112-05-107, installed with a rod end assembly, P/N M004-01H007-041 or P/N M004-01H007-045, with a serial number from 84 through 132 or from 4964 through 5011, and add a new AD. The NPRM published in the Federal Register on August 18, 2014 (79 FR 48698). AD 2014-04-14 required removing the rod end assemblies from service. AD 2014-04-14 was prompted by AD No. 2012-0208, dated October 5, 2012, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Agusta Model A109LUH, A109S, AW109SP, A119, and AW119 MKII helicopters. EASA advises of cases of in- flight fractures of rod end assembly, P/N M004-01H007-045, installed on main rotor lag dampers on Model A109LUH and AW109SP helicopters. An investigation revealed that two batches of rod end assemblies, P/N M004-01H007-041 and M004-01H007-045, could have cracks, according to EASA. EASA states that this condition, if not corrected, could lead to main rotor damage, possibly resulting in loss of control of the helicopter. The actions of AD 2014-04-14 were intended to prevent such damage and loss of control of the helicopter. Actions Since AD 2014-04-14 Was Issued Between the time we published the NPRM for AD 2014-04-14 (78 FR 44042, July 23, 2013) and the Final Rule for AD 2014-04-14 (79 FR 11699, March 3, 2014), EASA issued AD No. 2013-0290, dated December 9, 2013. EASA advises in AD No. 2013-0290 that a new case of a fractured rod end assembly has been reported and that additional batches of rod end assembly, P/N M004-01H007-041 and P/N M004-01H007-045, as well as batches of P/N 109-0112-11-101 and P/N 109-0112-22-105 could also have cracks. EASA expanded the applicability of its AD to include the additional rod end assemblies. We consequently issued the NPRM (79 FR 48698, August 18, 2014) to amend 14 CFR part 39 to remove AD 2014-04-14 and add a new AD. The NPRM proposed to retain the requirements of AD 2014-04-14 but expand the scope of applicable rod end assemblies. The NPRM also proposed to add a provision requiring compliance with the AD if the rod end assembly is removed during maintenance before 25 hours time-in-service (TIS). Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (79 FR 48698, August 18, 2014). FAA's Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, 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, except we have correctly stated the design holder's name as Agusta S.p.A. instead of AgustaWestland S.p.A. as specified by the current FAA type certificate. This change is consistent with the intent of the proposals in the NPRM (79 FR 48698, August 18, 2014) and will not increase the economic burden on any operator nor increase the scope of the AD. Differences Between This AD and the EASA AD The EASA AD calls for replacing certain rod end assemblies with airworthy rod end assemblies within 25 hours TIS, 2 months, or the next time maintenance of the applicable helicopters involves removing the rod end assembly. This AD does not have a calendar time requirement. The EASA AD applies to Agusta Model A109LUH helicopters. This AD does not apply to Model A109LUH helicopters because that model does not have a U.S. type certificate. Related Service Information We reviewed AgustaWestland Bollettino Tecnico (BT) No. 109S-49 for Model A109S helicopters, BT No. 109SP-052 for Model AW109SP helicopters, and BT No. 119-50 for Model A119 and AW119 MKII helicopters. All of the BTs are revision A, and dated December 3, 2013. The BTs specify a one-time inspection of each rod end assembly to determine its serial number. The BTs then require removal from service of certain serial-numbered rod end assemblies because fractures had been reported on rod ends in these batches. According to the BTs, no one was injured in the helicopters, and no helicopters were damaged because of these fractures. Costs of Compliance We estimate that this AD affects 91 helicopters of U.S. Registry and that labor costs average $85 a work-hour. Based on these estimates, we expect the following costs:Replacing a rod end assembly requires 1.5 work-hours for a labor cost of $128. Parts cost $3,918 for a total cost of $4,046 per helicopter, $368,186 for the U.S. fleet. According to the manufacturer's service information, costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by manufacturers. Accordingly, we have included all costs in our cost estimate. 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. [[Page 14299]] 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), (3) Will not affect intrastate aviation in Alaska, 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) 2014-04-14, Amendment 39-17773 (79 FR 11699, March 3, 2014), and adding the following new AD: 2015-05-05 Agusta S.p.A.: Amendment 39-18115; Docket No. FAA-2014- 0579; Directorate Identifier 2014-SW-020-AD. (a) Applicability This AD applies to the following helicopters, certificated in any category: (1) Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters, with a main rotor lag damper assembly (lag damper), part number (P/ N) 109-0112-39-103 or 109-0112-39-105, installed on rod end assembly, P/N M004-01H007-041 with a serial number (S/N) 1 through 202; or rod end assembly, P/N M004-01H007-045 with a S/N 1RW through 202RW or 4964 through 5011. (2) Agusta Model A119 and AW119 MKII helicopters, with a lag damper, P/N 109-0112-05-105 or 109-0112-05-107, installed on rod end assembly, P/N 109-0112-11-101 with a S/N 1 through 78; or rod end assembly, P/N 109-0112-11-105 with a S/N 1RW through 78RW; or rod end assembly, P/N M004-01H007-045 with a S/N 1RW through 202RW or 4964 through 5011. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a rod end assembly, which could result in fracture of the rod end assembly, damage to the main rotor, and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014-04-14, amendment 39-17773 (79 FR 11699, March 3, 2014). (d) Effective Date This AD becomes effective April 23, 2015. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Within 25 hours time-in-service or the next time maintenance of the helicopter involves removing the rod end assembly, whichever occurs first, remove the rod end assembly from service. (2) Do not install a rod end assembly, P/N M004-01H007-041 with a S/N 1 through 202; P/N M004-01H007-045 with a S/N 1RW through 202RW or 4964 through 5011; P/N 109-0112-11-101 with a S/N 1 through 78; or P/N 109-0112-11-105 with a S/N 1RW through 78RW, on any helicopter. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) AgustaWestland S.p.A. Bollettino Tecnico (BT) No. 109S-49, BT No. 109SP-052, and BT No. 119-50, all Revision A, and all dated December 3, 2013, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39- 0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD No. 2013-0290, dated December 9, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0579. (i) Subject Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System. Issued in Fort Worth, Texas, on March 4, 2015. Bruce E. Cain, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-05715 Filed 3-18-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations 14297
We are issuing this rulemaking under (b) Affected ADs (i) Related Information
the authority described in ‘‘Subtitle VII, None. (1) Refer to MCAI European Aviation
Part A, Subpart III, Section 44701: Safety Agency (EASA) AD No.: 2015–0034–
(c) Applicability E, dated February 27, 2015, for related
General requirements.’’ Under that
section, Congress charges the FAA with This AD applies to Stemme AG TSA–M information. You may examine the MCAI on
Models S6 and S6–RT gliders, all serial the Internet at http://www.regulations.gov by
promoting safe flight of civil aircraft in numbers, certificated in any category. searching for and locating Docket No. FAA–
air commerce by prescribing regulations 2015–0633.
for practices, methods, and procedures (d) Subject
(2) For information concerning this action,
the Administrator finds necessary for Air Transport Association of America contact Stemme AG, Flugplatzstra+e F2, Nr.
safety in air commerce. This regulation (ATA) Code 27: Flight Controls. 6–7, D–15344 Strausberg, Germany; phone:
is within the scope of that authority (e) Reason +49 (0) 3341/3612 0; fax: none; email: info@
because it addresses an unsafe condition stemme.de; internet: www.stemme.info.
This AD was prompted by mandatory
that is likely to exist or develop on continuing airworthiness information (MCAI) Issued in Kansas City, Missouri, on March
products identified in this rulemaking originated by an aviation authority of another 12, 2015.
action. country to identify and correct an unsafe Robert Busto,
condition on an aviation product. The MCAI Acting Manager, Small Airplane Directorate,
Regulatory Findings describes the unsafe condition as a bending Aircraft Certification Service.
We determined that this AD will not defect of the fork head installed in the
[FR Doc. 2015–06296 Filed 3–18–15; 8:45 am]
have federalism implications under aileron, speed brake, and flap control
Executive Order 13132. This AD will systems. We are issuing this AD to detect and BILLING CODE 4910–13–P
not have a substantial direct effect on correct the bending defect of the fork head
that could result in failure of the flight
the States, on the relationship between control system, possibly resulting in loss of DEPARTMENT OF TRANSPORTATION
the national government and the States, control.
or on the distribution of power and Federal Aviation Administration
responsibilities among the various (f) Actions and Compliance
levels of government. Unless already done, before further flight, 14 CFR Part 39
For the reasons discussed above, I after March 24, 2015 (the effective date of
certify that this AD: this AD), modify the affected flight control [Docket No. FAA–2014–0579; Directorate
(1) Is not a ‘‘significant regulatory systems, or take other actions, following a Identifier 2014–SW–020–AD; Amendment
method approved specifically for this AD by 39–18115; AD 2015–05–05]
action’’ under Executive Order 12866,
the FAA, Small Airplane Directorate. Contact
(2) Is not a ‘‘significant rule’’ under Stemme AG to obtain FAA-approved repair RIN 2120–AA64
the DOT Regulatory Policies and instructions approved specifically for
Procedures (44 FR 11034, February 26, compliance with this AD and incorporate Airworthiness Directives; Agusta
1979), those instructions. You can find contact S.p.A. Helicopters
(3) Will not affect intrastate aviation information for Stemme AG in paragraph
AGENCY: Federal Aviation
in Alaska, and (i)(2) of this AD.
(4) Will not have a significant Note 1 to paragraph (f) of this AD: At the Administration (FAA), DOT.
economic impact, positive or negative, time of issuance of this AD, no design ACTION: Final rule.
on a substantial number of small entities solution is available to restore the
airworthiness of the respective type designs SUMMARY: We are superseding
under the criteria of the Regulatory Airworthiness Directive (AD) 2014–04–
to a level corresponding to their approved
Flexibility Act. type design specifications. 14 for Agusta S.p.A. (Agusta) Model
List of Subjects in 14 CFR Part 39 (g) Other FAA AD Provisions
A109S, AW109SP, A119, and AW119
Air transportation, Aircraft, Aviation MKII helicopters. AD 2014–04–14
The following provisions also apply to this
safety, Incorporation by reference, required removing certain rod end
AD:
Safety. (1) Alternative Methods of Compliance assemblies from service because of
(AMOCs): The Manager, Standards Office, reports of fractures. This new AD retains
Adoption of the Amendment FAA, has the authority to approve AMOCs the requirements of AD 2014–04–14 but
Accordingly, under the authority for this AD, if requested using the procedures expands the scope of applicable rod end
delegated to me by the Administrator, found in 14 CFR 39.19. Send information to assemblies. This AD was prompted by
ATTN: Jim Rutherford, Aerospace Engineer, reports of additional fractured rod end
the FAA amends 14 CFR part 39 as
FAA, Small Airplane Directorate, 901 Locust, assemblies. We are issuing this AD to
follows: Room 301, Kansas City, Missouri 64106; prevent failure of a rod end assembly,
telephone: (816) 329–4165; fax: (816) 329–
PART 39—AIRWORTHINESS 4090; email: jim.rutherford@faa.gov. Before which could result in damage to the
DIRECTIVES using any approved AMOC on any airplane main rotor assembly and loss of control
to which the AMOC applies, notify your of the helicopter.
■ 1. The authority citation for part 39 appropriate principal inspector (PI) in the DATES: This AD is effective April 23,
continues to read as follows: FAA Flight Standards District Office (FSDO), 2015.
Authority: 49 U.S.C. 106(g), 40113, 44701. or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement ADDRESSES: For service information
§ 39.13 [Amended] in this AD to obtain corrective actions from identified in this AD, contact
a manufacturer or other source, use these AgustaWestland, Product Support
■ 2. The FAA amends § 39.13 by adding
actions if they are FAA-approved. Corrective Engineering, Via del Gregge, 100, 21015
the following new AD:
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actions are considered FAA-approved if they Lonate Pozzolo (VA) Italy, ATTN:
2015–06–03 Stemme AG: Amendment 39– are approved by the State of Design Authority Maurizio D’Angelo; telephone 39–0331–
18121; Docket No. FAA–2015–0633; (or their delegated agent). You are required 664757; fax 39–0331–664680; or at
Directorate Identifier 2015–CE–005–AD. to assure the product is airworthy before it
is returned to service. http://www.agustawestland.com/
(a) Effective Date technical-bulletins. You may view this
This airworthiness directive (AD) becomes (h) Special Flight Permit referenced service information at the
effective March 24, 2015. Special flight permits are prohibited. FAA, Office of the Regional Counsel,
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![Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations 14299
We are issuing this rulemaking under (a) Applicability (h) Additional Information
the authority described in Subtitle VII, This AD applies to the following (1) AgustaWestland S.p.A. Bollettino
Part A, Subpart III, Section 44701, helicopters, certificated in any category: Tecnico (BT) No. 109S–49, BT No. 109SP–
‘‘General requirements.’’ Under that (1) Agusta S.p.A. (Agusta) Model A109S 052, and BT No. 119–50, all Revision A, and
section, Congress charges the FAA with and AW109SP helicopters, with a main rotor all dated December 3, 2013, which are not
promoting safe flight of civil aircraft in lag damper assembly (lag damper), part incorporated by reference, contain additional
number (P/N) 109–0112–39–103 or 109– information about the subject of this AD. For
air commerce by prescribing regulations service information identified in this AD,
for practices, methods, and procedures 0112–39–105, installed on rod end assembly,
P/N M004–01H007–041 with a serial number contact AgustaWestland, Product Support
the Administrator finds necessary for Engineering, Via del Gregge, 100, 21015
(S/N) 1 through 202; or rod end assembly, P/
safety in air commerce. This regulation N M004–01H007–045 with a S/N 1RW Lonate Pozzolo (VA) Italy, ATTN: Maurizio
is within the scope of that authority through 202RW or 4964 through 5011. D’Angelo; telephone 39–0331–664757; fax
because it addresses an unsafe condition (2) Agusta Model A119 and AW119 MKII 39–0331–664680; or at http://
that is likely to exist or develop on www.agustawestland.com/technical-
helicopters, with a lag damper, P/N 109–
products identified in this rulemaking bulletins. You may review a copy of the
0112–05–105 or 109–0112–05–107, installed
service information at the FAA, Office of the
action. on rod end assembly, P/N 109–0112–11–101
Regional Counsel, Southwest Region, 2601
with a S/N 1 through 78; or rod end Meacham Blvd., Room 663, Fort Worth,
Regulatory Findings assembly, P/N 109–0112–11–105 with a S/N Texas 76137.
We have determined that this AD will 1RW through 78RW; or rod end assembly, P/ (2) The subject of this AD is addressed in
not have federalism implications under N M004–01H007–045 with a S/N 1RW the European Aviation Safety Agency (EASA)
Executive Order 13132. This AD will through 202RW or 4964 through 5011. AD No. 2013–0290, dated December 9, 2013.
not have a substantial direct effect on (b) Unsafe Condition You may view the EASA AD on the Internet
the States, on the relationship between at http://www.regulations.gov in Docket No.
This AD defines the unsafe condition as a FAA–2014–0579.
the national government and the States, crack in a rod end assembly, which could
or on the distribution of power and result in fracture of the rod end assembly, (i) Subject
responsibilities among the various damage to the main rotor, and subsequent Joint Aircraft Service Component (JASC)
levels of government. loss of control of the helicopter. Code: 6200, Main Rotor System.
For the reasons discussed above, I (c) Affected ADs Issued in Fort Worth, Texas, on March 4,
certify that this AD: 2015.
This AD supersedes AD 2014–04–14,
(1) Is not a ‘‘significant regulatory Bruce E. Cain,
amendment 39–17773 (79 FR 11699, March
action’’ under Executive Order 12866, 3, 2014). Acting Directorate Manager, Rotorcraft
(2) Is not a ‘‘significant rule’’ under Directorate, Aircraft Certification Service.
DOT Regulatory Policies and Procedures (d) Effective Date
[FR Doc. 2015–05715 Filed 3–18–15; 8:45 am]
(44 FR 11034, February 26, 1979), This AD becomes effective April 23, 2015.
BILLING CODE 4910–13–P
(3) Will not affect intrastate aviation (e) Compliance
in Alaska, and
You are responsible for performing each
(4) Will not have a significant DEPARTMENT OF TRANSPORTATION
action required by this AD within the
economic impact, positive or negative, specified compliance time unless it has
on a substantial number of small entities already been accomplished prior to that time. Federal Aviation Administration
under the criteria of the Regulatory
Flexibility Act. (f) Required Actions 14 CFR Part 39
(1) Within 25 hours time-in-service or the
List of Subjects in 14 CFR Part 39 next time maintenance of the helicopter [Docket No. FAA–2014–1001; Directorate
involves removing the rod end assembly, Identifier 2014–CE–034–AD; Amendment
Air transportation, Aircraft, Aviation 39–18103; AD 2015–04–01]
safety, Incorporation by reference, whichever occurs first, remove the rod end
Safety. assembly from service. RIN 2120–AA64
(2) Do not install a rod end assembly, P/
Adoption of the Amendment N M004–01H007–041 with a S/N 1 through Airworthiness Directives; Short
202; P/N M004–01H007–045 with a S/N 1RW Brothers & Harland Ltd. Airplanes
Accordingly, under the authority through 202RW or 4964 through 5011; P/N
delegated to me by the Administrator, 109–0112–11–101 with a S/N 1 through 78; AGENCY: Federal Aviation
the FAA amends 14 CFR part 39 as or P/N 109–0112–11–105 with a S/N 1RW Administration (FAA), DOT.
follows: through 78RW, on any helicopter. ACTION: Final rule; correction.
PART 39—AIRWORTHINESS (g) Alternative Methods of Compliance
(AMOCs) SUMMARY: The FAA is correcting an
DIRECTIVES airworthiness directive (AD) that
(1) The Manager, Safety Management
published in the Federal Register. That
■ 1. The authority citation for part 39 Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
AD applies to all Short Brothers &
continues to read as follows: Harland Ltd. Model SC–7 Series 3
Aviation Safety Engineer, Safety Management
Authority: 49 U.S.C. 106(g), 40113, 44701. Group, FAA, 2601 Meacham Blvd., Fort airplanes. The amendment number in
Worth, Texas 76137; telephone (817) 222– the Agency Identification Numbers in
§ 39.13 [Amended] 5110; email robert.grant@faa.gov. the preamble section of the AD is
■ 2. The FAA amends § 39.13 by (2) For operations conducted under a 14 incorrect. Although no other part of the
CFR part 119 operating certificate or under preamble or regulatory information has
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removing Airworthiness Directive (AD)
2014–04–14, Amendment 39–17773 (79 14 CFR part 91, subpart K, we suggest that been corrected, we are publishing the
you notify your principal inspector, or entire rule in the Federal Register.
FR 11699, March 3, 2014), and adding lacking a principal inspector, the manager of
the following new AD: DATES: This final rule is effective March
the local flight standards district office or
2015–05–05 Agusta S.p.A.: Amendment 39– certificate holding district office, before 30, 2015.
18115; Docket No. FAA–2014–0579; operating any aircraft complying with this ADDRESSES: You may examine the AD
Directorate Identifier 2014–SW–020–AD. AD through an AMOC. docket on the Internet at http://
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Document Created: 2018-02-21 09:41:59
Document Modified: 2018-02-21 09:41:59
| 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 23, 2015. | |
| Contact | Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 14297 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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