81 FR 15171 - Airworthiness Directives; Agusta S.p.A. Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 55 (March 22, 2016)

Page Range		15171-15173
FR Document		2016-06373

We propose to adopt a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, A109S and AW109SP helicopters. This proposed AD would require visually inspecting the tail rotor drive shaft assembly (drive shaft) for a crack. This proposed AD is prompted by the discovery of three cracks on the drive shaft of a Model A109S helicopter. The proposed actions are intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control.

Federal Register, Volume 81 Issue 55 (Tuesday, March 22, 2016)

[Federal Register Volume 81, Number 55 (Tuesday, March 22, 2016)]
[Proposed Rules]
[Pages 15171-15173]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-06373]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 55 / Tuesday, March 22, 2016 / 
Proposed Rules

[[Page 15171]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3781; Directorate Identifier 2015-SW-048-AD]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, 
A109S and AW109SP helicopters. This proposed AD would require visually 
inspecting the tail rotor drive shaft assembly (drive shaft) for a 
crack. This proposed AD is prompted by the discovery of three cracks on 
the drive shaft of a Model A109S helicopter. The proposed actions are 
intended to detect a crack on the drive shaft to prevent failure of the 
driveshaft, failure of the tail rotor, and subsequent loss of 
helicopter control.

DATES: We must receive comments on this proposed AD by May 23, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3781; or in person at the Docket Operations Office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the European Aviation Safety Agency (EASA) 
AD, the economic evaluation, any comments received, and other 
information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed rule, 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 the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Martin R. Crane, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA, which is the aviation authority for Italy, has issued AD No. 
2015-0054, dated March 27, 2015, to correct an unsafe condition for 
Model A109A with retrofit kit part number 109-0820-27-101 installed, 
and Model A109A II, A109C, A109E, A109K2, A109LUH, A109S, and AW109SP 
helicopters.
    EASA advises that during scheduled maintenance on a Model A109S 
helicopter, three cracks were found on the drive shaft. An 
investigation could not determine the cause of the cracking but 
concluded it could not have been caused by fatigue. This condition, if 
not detected and corrected, could lead to tail rotor failure, possibly 
resulting in loss of helicopter control, EASA advises. EASA AD No. 
2015-0054 consequently requires a one-time inspection of the drive 
shaft, and replacing the drive shaft if cracks are found.

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 its AD. We are 
proposing this AD because we evaluated all known relevant information 
and determined that an unsafe condition is likely to exist or develop 
on other products of the same type design.

Related Service Information Under 1 CFR Part 51

    We reviewed AgustaWestland Bollettino Tecnico (BT) No. 109-147 for 
Model A109A helicopters with retrofit kit P/N 109-0820-27-101 
installed, Model A109A II, and Model A109C helicopters; BT No. 109EP-
143 for Model A109E helicopters; BT No. 109K-68 for Model A109K2 
helicopters; BT No. 109S-067 for Model A109S

[[Page 15172]]

helicopters; and BT No. 109SP-094 for Model AW109SP helicopters. All of 
the BTs are dated March 25, 2015. AgustaWestland reports that during a 
scheduled servicing of an A109S helicopter, three cracks were found on 
drive shaft P/N 109-8412-02-1. The BTs prescribe a one-time drive shaft 
inspection for cracks.
    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.

Proposed AD Requirements

    This proposed AD would require, within 50 hours time-in-service, 
visually inspecting the drive shaft for a crack and replacing the drive 
shaft if it is cracked.

Differences Between This Proposed AD and the EASA AD

    The EASA AD applies to Agusta Model A109LUH helicopters. This 
proposed AD would not because that model does not have an FAA type 
certificate.

Interim Action

    We consider this proposed AD to be an interim action. The design 
approval holder has not determined the cause of the unsafe condition 
identified in this proposed AD. If a cause is determined and actions 
developed to address the cause, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this proposed AD would affect 142 helicopters of 
U.S. Registry and that labor costs average $85 per work-hour. Based on 
these estimates, we expect the following costs:
     Inspecting the drive shaft would require 9 work-hours and 
no parts. The estimated cost would be $765 per helicopter and $108,630 
for the U.S. fleet.
     Replacing the drive shaft would not require additional 
labor hours. Parts would cost $6,082 per helicopter.
    According to Agusta service information, some of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected individuals. We do not control warranty coverage by 
Agusta. 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.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Agusta S.p.A.: Docket No. FAA-2015-3781; Directorate Identifier 
2015-SW-048-AD.

(a) Applicability

    This AD applies to Agusta S.p.A. Model A109A, A109A II, A109C, 
A109E, A109K2, A109S, and AW109SP helicopters with a tail rotor 
drive shaft assembly (drive shaft), part number 109-8412-02-1 or 
109-8412-02-3, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a drive 
shaft. This condition could result in failure of a drive shaft, 
failure of the tail rotor, and subsequent loss of helicopter 
control.

(c) Comments Due Date

    We must receive comments by May 23, 2016.

(d) 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.

(e) Required Actions

    Within 50 hours time-in-service:
    (1) Visually inspect each drive shaft in accordance with the 
Compliance Instructions, paragraph 4, of AgustaWestland Bollettino 
Tecnico (BT) No. 109-147, dated March 25, 2015; BT No. 109EP-143, 
dated March 25, 2015; BT No. 109K-68, dated March 25, 2015; BT No. 
109S-067, dated March 25, 2015; or BT No. 109SP-094, dated March 25, 
2015, as applicable for your model helicopter.
    (2) If there is a crack, replace the drive shaft before further 
flight.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Martin R. Crane, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, 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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2015-0054, dated March 27, 2015. You may view 
the EASA AD on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2015-3781.

[[Page 15173]]

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor 
Drive Shaft.

    Issued in Fort Worth, Texas, on March 15, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-06373 Filed 3-21-16; 8:45 am]
BILLING CODE 4910-13-P

15171

Proposed Rules Federal Register
Vol. 81, No. 55

Tuesday, March 22, 2016

This section of the FEDERAL REGISTER Examining the AD Docket public contact with FAA personnel
contains notices to the public of the proposed
You may examine the AD docket on concerning this proposed rulemaking.
issuance of rules and regulations. The Before acting on this proposal, we will
purpose of these notices is to give interested the Internet at http://
www.regulations.gov by searching for consider all comments we receive on or
persons an opportunity to participate in the before the closing date for comments.
rule making prior to the adoption of the final and locating Docket No. FAA–2015–
3781; or in person at the Docket We will consider comments filed after
rules.
Operations Office between 9 a.m. and 5 the comment period has closed if it is
p.m., Monday through Friday, except possible to do so without incurring
DEPARTMENT OF TRANSPORTATION Federal holidays. The AD docket expense or delay. We may change this
contains this proposed AD, the proposal in light of the comments we
Federal Aviation Administration European Aviation Safety Agency receive.
(EASA) AD, the economic evaluation, Discussion
14 CFR Part 39 any comments received, and other
EASA, which is the aviation authority
information. The street address for the
for Italy, has issued AD No. 2015–0054,
[Docket No. FAA–2015–3781; Directorate Docket Operations Office (telephone
dated March 27, 2015, to correct an
Identifier 2015–SW–048–AD] 800–647–5527) is in the ADDRESSES
unsafe condition for Model A109A with
section. Comments will be available in
retrofit kit part number 109–0820–27–
RIN 2120–AA64 the AD docket shortly after receipt.
For service information identified in 101 installed, and Model A109A II,
this proposed rule, contact A109C, A109E, A109K2, A109LUH,
Airworthiness Directives; Agusta A109S, and AW109SP helicopters.
S.p.A. Helicopters AgustaWestland, Product Support
EASA advises that during scheduled
Engineering, Via del Gregge, 100, 21015
AGENCY: Federal Aviation maintenance on a Model A109S
Lonate Pozzolo (VA) Italy, ATTN:
Administration (FAA), DOT. helicopter, three cracks were found on
Maurizio D’Angelo; telephone 39–0331–
the drive shaft. An investigation could
ACTION: Notice of proposed rulemaking 664757; fax 39–0331–664680; or at
not determine the cause of the cracking
(NPRM). http://www.agustawestland.com/
but concluded it could not have been
technical-bulletins. You may review the
caused by fatigue. This condition, if not
SUMMARY: We propose to adopt a new referenced service information at the
detected and corrected, could lead to
airworthiness directive (AD) for Agusta FAA, Office of the Regional Counsel,
tail rotor failure, possibly resulting in
S.p.A. (Agusta) Model A109A, A109A II, Southwest Region, 10101 Hillwood
loss of helicopter control, EASA
A109C, A109E, A109K2, A109S and Pkwy., Room 6N–321, Fort Worth, TX
advises. EASA AD No. 2015–0054
AW109SP helicopters. This proposed 76177.
consequently requires a one-time
AD would require visually inspecting FOR FURTHER INFORMATION CONTACT: inspection of the drive shaft, and
the tail rotor drive shaft assembly (drive Martin R. Crane, Aviation Safety replacing the drive shaft if cracks are
shaft) for a crack. This proposed AD is Engineer, Safety Management Group, found.
prompted by the discovery of three Rotorcraft Directorate, FAA, 10101
cracks on the drive shaft of a Model Hillwood Pkwy., Fort Worth, TX 76177; FAA’s Determination
A109S helicopter. The proposed actions telephone (817) 222–5110; email These helicopters have been approved
are intended to detect a crack on the martin.r.crane@faa.gov. by the aviation authority of Italy and are
drive shaft to prevent failure of the SUPPLEMENTARY INFORMATION: approved for operation in the United
driveshaft, failure of the tail rotor, and States. Pursuant to our bilateral
subsequent loss of helicopter control. Comments Invited agreement with Italy, EASA, its
DATES: We must receive comments on We invite you to participate in this technical representative, has notified us
this proposed AD by May 23, 2016. rulemaking by submitting written of the unsafe condition described in its
comments, data, or views. We also AD. We are proposing this AD because
ADDRESSES: You may send comments by
invite comments relating to the we evaluated all known relevant
any of the following methods:
economic, environmental, energy, or information and determined that an
• Federal eRulemaking Docket: Go to federalism impacts that might result unsafe condition is likely to exist or
http://www.regulations.gov. Follow the from adopting the proposals in this develop on other products of the same
online instructions for sending your document. The most helpful comments type design.
comments electronically. reference a specific portion of the
• Fax: 202–493–2251. proposal, explain the reason for any Related Service Information Under 1
• Mail: Send comments to the U.S. recommended change, and include CFR Part 51
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS

Department of Transportation, Docket supporting data. To ensure the docket We reviewed AgustaWestland
Operations, M–30, West Building does not contain duplicate comments, Bollettino Tecnico (BT) No. 109–147 for
Ground Floor, Room W12–140, 1200 commenters should send only one copy Model A109A helicopters with retrofit
New Jersey Avenue SE., Washington, of written comments, or if comments are kit P/N 109–0820–27–101 installed,
DC 20590–0001. filed electronically, commenters should Model A109A II, and Model A109C
• Hand Delivery: Deliver to the submit only one time. helicopters; BT No. 109EP–143 for
‘‘Mail’’ address between 9 a.m. and 5 We will file in the docket all Model A109E helicopters; BT No. 109K–
p.m., Monday through Friday, except comments that we receive, as well as a 68 for Model A109K2 helicopters; BT
Federal holidays. report summarizing each substantive No. 109S–067 for Model A109S

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15172 Federal Register / Vol. 81, No. 55 / Tuesday, March 22, 2016 / Proposed Rules

helicopters; and BT No. 109SP–094 for Aviation Programs,’’ describes in more § 39.13 [Amended]
Model AW109SP helicopters. All of the detail the scope of the Agency’s ■ 2. The FAA amends § 39.13 by adding
BTs are dated March 25, 2015. authority. the following new airworthiness
AgustaWestland reports that during a We are issuing this rulemaking under directive (AD):
scheduled servicing of an A109S the authority described in ‘‘Subtitle VII,
helicopter, three cracks were found on Agusta S.p.A.: Docket No. FAA–2015–3781;
Part A, Subpart III, Section 44701:
drive shaft P/N 109–8412–02–1. The Directorate Identifier 2015–SW–048–AD.
General requirements.’’ Under that
BTs prescribe a one-time drive shaft section, Congress charges the FAA with (a) Applicability
inspection for cracks. promoting safe flight of civil aircraft in This AD applies to Agusta S.p.A. Model
This service information is reasonably air commerce by prescribing regulations A109A, A109A II, A109C, A109E, A109K2,
available because the interested parties for practices, methods, and procedures A109S, and AW109SP helicopters with a tail
have access to it through their normal the Administrator finds necessary for rotor drive shaft assembly (drive shaft), part
course of business or by the means safety in air commerce. This regulation number 109–8412–02–1 or 109–8412–02–3,
identified in the ADDRESSES section. is within the scope of that authority installed, certificated in any category.

Proposed AD Requirements because it addresses an unsafe condition (b) Unsafe Condition
that is likely to exist or develop on This AD defines the unsafe condition as a
This proposed AD would require, products identified in this rulemaking crack in a drive shaft. This condition could
within 50 hours time-in-service, action. result in failure of a drive shaft, failure of the
visually inspecting the drive shaft for a tail rotor, and subsequent loss of helicopter
crack and replacing the drive shaft if it Regulatory Findings control.
is cracked. We determined that this proposed AD (c) Comments Due Date
Differences Between This Proposed AD would not have federalism implications
We must receive comments by May 23,
and the EASA AD under Executive Order 13132. This 2016.
proposed AD would not have a
The EASA AD applies to Agusta (d) Compliance
substantial direct effect on the States, on
Model A109LUH helicopters. This
the relationship between the national You are responsible for performing each
proposed AD would not because that action required by this AD within the
Government and the States, or on the
model does not have an FAA type specified compliance time unless it has
distribution of power and
certificate. already been accomplished prior to that time.
responsibilities among the various
Interim Action levels of government. (e) Required Actions
We consider this proposed AD to be For the reasons discussed, I certify Within 50 hours time-in-service:
an interim action. The design approval this proposed regulation: (1) Visually inspect each drive shaft in
holder has not determined the cause of 1. Is not a ‘‘significant regulatory accordance with the Compliance
the unsafe condition identified in this action’’ under Executive Order 12866; Instructions, paragraph 4, of AgustaWestland
Bollettino Tecnico (BT) No. 109–147, dated
proposed AD. If a cause is determined 2. Is not a ‘‘significant rule’’ under the March 25, 2015; BT No. 109EP–143, dated
and actions developed to address the DOT Regulatory Policies and Procedures March 25, 2015; BT No. 109K–68, dated
cause, we might consider additional (44 FR 11034, February 26, 1979); March 25, 2015; BT No. 109S–067, dated
rulemaking. 3. Will not affect intrastate aviation in March 25, 2015; or BT No. 109SP–094, dated
Alaska to the extent that it justifies March 25, 2015, as applicable for your model
Costs of Compliance helicopter.
making a regulatory distinction; and
We estimate that this proposed AD (2) If there is a crack, replace the drive
4. Will not have a significant shaft before further flight.
would affect 142 helicopters of U.S.
economic impact, positive or negative,
Registry and that labor costs average $85 (f) Alternative Methods of Compliance
on a substantial number of small entities
per work-hour. Based on these (AMOCs)
under the criteria of the Regulatory
estimates, we expect the following costs: (1) The Manager, Safety Management
Flexibility Act.
• Inspecting the drive shaft would Group, FAA, may approve AMOCs for this
require 9 work-hours and no parts. The We prepared an economic evaluation
AD. Send your proposal to: Martin R. Crane,
estimated cost would be $765 per of the estimated costs to comply with Aviation Safety Engineer, Safety Management
helicopter and $108,630 for the U.S. this proposed AD and placed it in the Group, Rotorcraft Directorate, FAA, 10101
fleet. AD docket. Hillwood Pkwy, Fort Worth, TX 76177;
• Replacing the drive shaft would not List of Subjects in 14 CFR Part 39 telephone (817) 222–5110; email 9-ASW-
require additional labor hours. Parts FTW-AMOC-Requests@faa.gov.
would cost $6,082 per helicopter. Air transportation, Aircraft, Aviation (2) For operations conducted under a 14
safety, Incorporation by reference, CFR part 119 operating certificate or under
According to Agusta service
Safety. 14 CFR part 91, subpart K, we suggest that
information, some of the costs of this you notify your principal inspector, or
proposed AD may be covered under The Proposed Amendment lacking a principal inspector, the manager of
warranty, thereby reducing the cost the local flight standards district office or
impact on affected individuals. We do Accordingly, under the authority certificate holding district office before
not control warranty coverage by delegated to me by the Administrator, operating any aircraft complying with this
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS

Agusta. Accordingly, we have included the FAA proposes to amend 14 CFR part AD through an AMOC.
all costs in our cost estimate. 39 as follows: (g) Additional Information
Authority for This Rulemaking PART 39—AIRWORTHINESS The subject of this AD is addressed in
DIRECTIVES European Aviation Safety Agency (EASA) AD
Title 49 of the United States Code No. 2015–0054, dated March 27, 2015. You
specifies the FAA’s authority to issue may view the EASA AD on the Internet at
rules on aviation safety. Subtitle I, ■ 1. The authority citation for part 39
http://www.regulations.gov by searching for
section 106, describes the authority of continues to read as follows: and locating it in Docket No. FAA–2015–
the FAA Administrator. ‘‘Subtitle VII: Authority: 49 U.S.C. 106(g), 40113, 44701. 3781.

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Document Created: 2018-02-02 15:15:43
Document Modified: 2018-02-02 15:15:43

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		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by May 23, 2016.
Contact		Martin R. Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]
FR Citation		81 FR 15171
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

81 FR 15171 - Airworthiness Directives; Agusta S.p.A. Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 55 (March 22, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration