Airworthiness Directives; Agusta S.p.A. Helicopters

[Federal Register Volume 79, Number 46 (Monday, March 10, 2014)]
[Rules and Regulations]
[Pages 13199-13201]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-04274]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0109; Directorate Identifier 2013-SW-049-AD; 
Amendment 39-17772; AD 2014-04-13]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta 
S.p.A. (Agusta) Model AB412 and AB412 EP helicopters. This AD requires 
inspecting the tail rotor (T/R) blade for a crack, corrosion, nick, 
scratch, dent, or other damage and replacing or repairing the blade, 
depending on the damage. This AD is prompted by reports of T/R blade 
failures caused by fatigue cracking that originated from surface 
damage. These actions are intended to prevent failure of the T/R blade 
and subsequent loss of control of the helicopter.

DATES: This AD becomes effective March 25, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 25, 2014.
    We must receive comments on this AD by May 9, 2014.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 AD, the European Aviation Safety 
Agency (EASA) AD, any incorporated by reference service information, 
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 AD, contact Agusta 
Westland, 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 [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    On April 22, 2008, we issued AD 2008-10-03, Amendment 39-15509 (73 
FR 24858, May 6, 2008) for Bell Helicopter Textron Helicopters (Bell) 
Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP 
helicopters. AD 2008-10-03 required certain checks and inspections of 
each T/R blade at specified intervals and repairing or replacing, as 
applicable, any unairworthy T/R blade. AD 2008-10-03 was prompted by 
eight reports of fatigue cracking of T/R blades installed on Bell Model 
212 and 412 helicopters (three failures on Bell Model 212 and five 
failures on Bell Model 412) with a T/R blade, part number (P/N) 212-
010-750-009, -105, and -107. Three of the Model 412 failures occurred 
during flight.
    After we issued AD 2008-10-03, an accident attributed to a T/R 
failure occurred. Because of this accident, we determined that a 
second, more detailed inspection was necessary to allow for an earlier 
detection of a crack or other damage. As a result, on July 11, 2013, we 
issued AD 2013-15-02, Amendment 39-17518 (78 FR 45845, July 30, 2013), 
which superseded AD 2008-10-03. These actions were intended to prevent 
failure of the T/R blade and subsequent loss of helicopter control.
    Although similar failures have not been reported on Agusta 
helicopters, T/R blade P/N 212-010-750 may be installed on Agusta Model 
AB205A1, AB212, AB412, and AB412 EP helicopters. As a result, EASA, 
which is the Technical Agent for the Member States of the European 
Union, issued AD No. 2013-0185, dated August 14, 2013, to correct an 
unsafe condition for Agusta Model AB205A1, AB212, AB412, and AB412 EP 
helicopters. EASA advised that Bell reported some failures in T/R blade 
P/N 212-010-750 (all dash numbers), which originated from a fatigue 
crack derived from surface damages. EASA consequently requires detailed 
visual inspections of the T/R blade surface for nicks, dents, 
scratches, corrosion or cracks. EASA also requires repair or 
replacement of the T/R blade, depending on the outcome of those 
inspections.

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

[[Page 13200]]

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 that the unsafe condition exists and is likely to exist or 
develop on other helicopters of these same type designs.

Related Service Information

    AgustaWestland, formerly Agusta S.p.A., issued Bollettino Tecnico 
No. 412-136, dated August 13, 2013 (BT), for Model AB412 and Model 
AB412 EP helicopters. The BT calls for visually inspecting the T/R 
blade surface for a crack, corrosion, a nick, a scratch, a dent, or 
other damage using a 3X magnifying glass every 25 hours time-in-service 
(TIS) or 30 days, whichever occurs first. The BT also calls for a 
recurring detailed visual inspection of the blade surface with a 10X 
magnifying glass between stations 20.00 to 35.00 from the T/R blade's 
leading edge to the trailing edge. If paint blistering, peeling, 
flaking, bubbling, or cracking exists, the BT calls for removing the 
paint and inspecting the affected area with a 10X magnifying glass. If 
a nick, scratch or dent exists, the BT calls for a visual inspection 
for a crack with a 10X magnifying glass and measuring any damage. If 
skin damages exceed maintenance manual limits or if a crack exists, the 
BT calls for removing the blade from service.

AD Requirements

    This AD requires within 25 hours TIS or 30 days, whichever occurs 
first, and thereafter at intervals not to exceed 25 hours TIS or 30 
days, whichever occurs first:
    <bullet> Cleaning each T/R blade by hand and, using a 3X or higher 
power magnifying glass and a light, visually inspecting the T/R blade 
skins, leading edge spar, doublers, grip plates, and trailing edge on 
both sides of each blade for a crack, corrosion, a nick, scratch, dent, 
or other damage. This inspection requires you to pay particular 
attention to the area located between blade station 20.00 to 35.00 and 
to the inboard T/R blade butt area near the attachment of the external 
balance weight and screws.
    <bullet> Using a 10X or higher magnifying glass and a light, 
visually inspecting both sides of each blade for a crack or other 
damage between blade station 20.00 to 35.00.
    <bullet> If blistering, peeling, flaking, bubbling, or cracked 
paint is detected anywhere on the blade, removing the paint and then 
visually inspecting the affected area for any corrosion or a crack 
using a 10X or higher magnifying glass and a light.
    <bullet> If a nick, scratch, or dent is found anywhere on the 
blade, visually inspecting for a crack using a 10X or higher power 
magnifying glass and a light.
    <bullet> Before further flight, removing from service any T/R blade 
that has a crack or that has corrosion, a nick, a scratch, a dent, or 
other damage that exceeds any of the maximum repair limits.
    <bullet> Before further flight, repairing or removing from service 
any T/R blade that has any corrosion, nick, scratch, dent or other 
damage that is within the maximum repair limits.

Differences Between This AD and the EASA AD

    The EASA AD applies to Agusta Model AB205A1 and AB212 helicopters. 
This AD does not because these helicopters have no FAA type 
certificate. This AD requires paying particular attention to both sides 
of each T/R blade in the area located 16 to 32 inches from the T/R 
blade tip when conducting the inspection using a 3X or higher power 
magnifying glass and a light. The EASA AD makes no such requirement.

Costs of Compliance

    There are no costs of compliance with this AD because there are no 
helicopters with this type certificate on the U.S. Registry.

FAA's Justification and Determination of the Effective Date

    There are no helicopters with this type certificate on the U.S. 
Registry. Therefore, we believe it is unlikely that we will receive any 
adverse comments or useful information about this AD from U.S. 
Operators.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are unnecessary because there are 
no helicopters on the U.S. registry and that good cause exists for 
making this amendment effective in less than 30 days.

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 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, 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.

 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 adding the following new airworthiness 
directive (AD):

2014-04-13 Agusta S.p.A. Helicopters: Amendment 39-17772; Docket No. 
FAA-2014-0109; Directorate Identifier 2013-SW-049-AD.

(a) Applicability

    This AD applies to Agusta S.p.A. (Agusta) Model AB412 and AB412 
EP helicopters with a tail rotor blade (T/R) blade, part number

[[Page 13201]]

 (P/N) 212-010-750 (all dash numbers), installed, certificated in 
any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue cracking of a T/
R blade, which could lead to failure of the T/R blade and subsequent 
loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective March 25, 2014.

(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 25 hours time-in-service (TIS) or 30 days, whichever 
occurs first, and thereafter at intervals not to exceed 25 hours TIS 
or 30 days, whichever occurs first:
    (i) Clean each T/R blade by hand using a mild soap and 
cheesecloth on both sides of the blade in a spanwise direction and 
dry thoroughly.
    (ii) Using a 3X or higher power magnifying glass and a light, 
visually inspect the T/R blade skin, leading edge spar, doublers, 
grip plates, and trailing edge on both sides of each blade for a 
crack, corrosion (which may be indicated by blistering, peeling, 
flaking, bubbling, or cracked paint), a nick, a scratch, a dent, or 
other damage. Pay particular attention to both sides of each T/R 
blade in the area located 16 to 32 inches from the T/R blade tip 
(blade station 20.00 to 35.00; the T/R blade tip is located at blade 
station 51) as depicted by the shaded area in Figure 2 of 
AgustaWestland Bollettino Tecnico No. 412-136, dated August 13, 2013 
(BT). Also, pay particular attention to the inboard T/R blade butt 
area near the attachment of the external balance weight and screws 
and to any T/R blade surface that was snagged by cheesecloth, as 
this may be an indication of a crack or paint chip that could lead 
to corrosion.
    (iii) Using a 10X or higher power magnifying glass and a light, 
visually inspect both sides of each T/R blade for a crack, corrosion 
(which may be indicated by blistering, peeling, flaking, bubbling, 
or cracked paint), a nick, a scratch, a dent or other damage between 
blade station 20.00 to 35.00 as depicted by the shaded area in 
Figure 2 of the BT.
    (iv) If there is any blistering, peeling, flaking, bubbling, or 
cracked paint on a T/R blade, remove the paint from the affected 
area by sanding in a spanwise direction first with abrasive cloth or 
paper 240-grit or finer and then with abrasive cloth or paper 400-
grit or finer. After paint removal, wipe area with a clean cloth 
dampened with alcohol and dry thoroughly and then visually inspect 
the affected area for any corrosion or a crack using a 10X or higher 
power magnifying glass and a light. If any corrosion is found, 
measure the depth of the damage.
    (v) If there is a nick, scratch, or dent on the T/R blade, 
visually inspect for a crack using a 10X or higher power magnifying 
glass and a light. Measure the depth of the damage.
    (2) Before further flight, remove from service any T/R blade 
that has a crack, corrosion, a nick, a scratch, a dent, or other 
damage that exceeds any of the maximum repair damage limits.
    (3) Before further flight, repair or remove from service any T/R 
blade that has corrosion, a nick, a scratch, a dent or other damage 
that is within the maximum repair damage limits.
    (4) Do not install on any helicopter T/R blade P/N 212-010-750 
(all dash numbers) unless it has been inspected in accordance with 
the requirements of this AD.

(f) 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.

(g) Additional Information

    The subject of this AD is addressed in the European Aviation 
Safety Agency (EASA) AD. No. 2013-0185, dated August 14, 2013. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in Docket No. FAA-2014-0109.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, tail rotor 
blades.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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.
    (i) AgustaWestland Bollettino Tecnico No. 412-136, dated August 
13, 2013.
    (ii) Reserved.
    (3) For Agusta 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) 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 20, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-04274 Filed 3-7-14; 8:45 am]
BILLING CODE 4910-13-P

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