```

[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)]
[Proposed Rules]
[Pages 32072-32074]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13354]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1935; Directorate Identifier 2014-SW-008-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 AB139 and AW139 helicopters. This proposed 
AD would require visually inspecting certain subfloor frames for a 
crack. This proposed AD is prompted by reports of cracks on in-service 
helicopters. The proposed actions are intended to detect or prevent a 
crack in the subfloor frame, which could result in failure of the pilot 
and co-pilot pedal support frame and subsequent loss of control of the 
helicopter.

DATES: We must receive comments on this proposed AD by August 4, 2015.

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 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 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 the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth, Texas 76137.

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 robert.grant@faa.gov.

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 Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2014-0048, dated March 4, 2014, 
to correct an unsafe condition for Agusta Model AB139 and AW139 
helicopters with a serial number (S/N) 31005 through 31517 (except S/N 
31007, 31415, 31431, 31491, 31500, 31508, and 31516) and S/N 41001 
through 41356 (except S/N 41355). EASA advises that cracks have been 
reported in the subfloor frame at station (STA) 2105 on in-service 
helicopters. This condition, if not detected and corrected, could lead 
to failure of the pedals supporting the frame, which in turn could lead 
to the pedals being inoperative and subsequent loss of control of the 
helicopter, EASA advises.
    The EASA AD requires repetitive inspections of the subfloor frame 
at STA 2105 for a crack. The EASA AD also requires installation of 
frame reinforcements before further flight if there is a crack or 
within 1,200 flight hours if there is no crack. The EASA AD provides 
that installation of the frame reinforcements constitutes terminating 
action for the repetitive inspections required by the AD.

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 Bolletino Tecnico No. 139-311, Revision 
B, dated June 4, 2014 (BT), for certain serial-numbered Agusta Model

[[Page 32073]]

AB139 and AW139 helicopters. The BT calls for visual inspections of the 
subfloor frames within 30 flight hours or two months, whichever occurs 
first, and thereafter at intervals of 300 flight hours or 6 months, 
whichever comes first, until frame reinforcements are installed to 
prevent future failures. The BT also specifies installing the frame 
reinforcements immediately if a crack is found and within 1,200 flight 
hours if a crack is not found. 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 of this NPRM.

Proposed AD Requirements

    This proposed AD would require:
     Within 30 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 300 hours TIS, using a light, inspecting all 
visible surfaces of the subfloor frames at station (STA) 2105 for a 
crack.
     If there is a crack, before further flight, and if there 
are no cracks, within 1200 hours TIS, installing frame STA 2105 
retromod part number (P/N) 3G5306P47211. This terminates the repetitive 
inspection requirements of this AD.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires conducting the initial inspection within 30 
flight hours or 2 months, whichever occurs first, and thereafter, at 
intervals not to exceed 300 flight hours or 6 months, whichever occurs 
first. The proposed AD would require conducting the initial inspection 
within 30 TIS, and thereafter, at intervals not to exceed 300 hours 
TIS.

Costs of Compliance

    We estimate that this proposed AD would affect 102 U.S.-registered 
helicopters and that labor costs average $85 a work hour. Based on 
these estimates, we expect the following costs:
     The visual inspection would require 2 work-hours for a 
labor cost of $170 per helicopter. No parts would be needed, so the 
cost would total $170 per helicopter, $17,340 for the U.S. fleet.
     If there are no cracks, installing the frame 
reinforcements would require 240 work-hours for a labor cost of $20,400 
and parts would cost $2,274. The total cost would be $22,674 per 
helicopter.
     If there is a crack, installing the frame reinforcements 
would require 240 work-hours for a labor cost of $20,400 and parts 
would cost $3,401. The total cost would be $23,801 per helicopter.

 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-2015-1935; Directorate Identifier 
2014-SW-008-AD.

(a) Applicability

    This AD applies to Agusta S.p.A. Model AB139 and AW139 
helicopters, serial number (S/N) 31005 through 31517 (except S/N 
31007, 31415, 31431, 31491, 31500, 31508, and 31516) and S/N 41001 
through 41356 (except S/N 41355), certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a subfloor 
frame. This condition could result in failure of the pilot and co-
pilot pedal support frame and subsequent loss of control of the 
helicopter.

(c) Comments Due Date

    We must receive comments by August 4, 2015.

(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

    (1) Within 30 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 300 hours TIS, using a light, inspect all 
visible surfaces of the left hand subfloor frame, right hand 
subfloor frame, and middle subfloor frame at station (STA) 2105 for 
a crack as shown in Figures 10 through 13 of AgustaWestland 
Bollettino Tecnico No. 139-311, Revision B, dated June 4, 2014 (BT 
139-311).
    (2) If there is a crack, before further flight, install frame 
STA 2105 retromod part number (P/N) 3G5306P47211 by following the 
Compliance Instructions, Part II, paragraphs 7 through 7.10. of BT 
139-311.
    (3) If there are no cracks, within 1200 hours TIS, install frame 
STA 2105 retromod P/N 3G5306P47211 by following the Compliance 
Instructions, Part II, paragraphs 7 through 7.10. of BT 139-311.
    (4) Installing frame STA 2105 retromod P/N 3G5306P47211 
terminates the repetitive inspection requirements in paragraph 
(e)(1) of this AD.

(f) Special Flight Permit

    Special Flight Permits are prohibited.

(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

[[Page 32074]]

Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone 
(817) 222-5110; email robert.grant@faa.gov.
    (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

    The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) No. 2014-0048, March 4, 2014. You may view the 
EASA AD on the Internet at http://www.regulations.gov in the AD 
Docket.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 5300, Fuselage 
Structure (General).

    Issued in Fort Worth, Texas, on May 26, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-13354 Filed 6-4-15; 8:45 am]
 BILLING CODE 4910-13-P
```