[Federal Register Volume 86, Number 136 (Tuesday, July 20, 2021)]
[Rules and Regulations]
[Pages 38218-38220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-15303]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0348; Project Identifier 2018-SW-076-AD; Amendment 
39-21645; AD 2021-14-18]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.a. (Type Certificate 
Previously Held by Agusta S.p.A.) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2011-18-52 
for certain Agusta S.p.A. (now Leonardo S.p.a.) Model AB139 and AW139 
helicopters. AD 2011-18-52 required revising the life limit for certain 
part-numbered tail rotor (T/R) blades, updating the helicopter's 
historical records, repetitively inspecting each T/R blade for a crack 
or damage, and depending on the results, replacing the T/R blade. This 
AD was prompted by the manufacturer developing improved T/R blades 
using different materials and establishing life limits for each 
improved blade. This AD retains certain requirements from AD 2011-18-
52, revises certain requirements from AD 2011-18-52, and expands the 
applicability to include the newly-designed T/R blades. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective August 24, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 24, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of 
Airworthiness, Viale G.Agusta 520, 21017 C. Costa di Samarate (Va) 
Italy; telephone +39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home. You may view this service information 
at the 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. It 
is also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0348.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0348; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, the 
European Aviation Safety Agency (now European Union Aviation Safety 
Agency) (EASA) AD, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, 
General Aviation & Rotorcraft Unit, Airworthiness Products Section, 
Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5110; email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2011-18-52, Amendment 39-17020 (77 FR 
23109, April 18, 2012) (AD 2011-18-52). AD 2011-18-52 applied to Agusta 
S.p.A. (now Leonardo S.p.a.) Model AB139 and AW139 helicopters with a 
T/R blade part number (P/N) 3G6410A00131 or P/N 4G6410A00131 installed. 
The NPRM published in the Federal Register on May 10, 2021 (86 FR 
24780). AD 2011-18-52 required, within 5 hours time-in-service (TIS), 
establishing a life limit of 600 hours TIS or 1,500 takeoff and landing 
cycles (cycles), whichever occurs first, on the affected T/R blades and 
updating the helicopter's historical records. If a T/R blade's total 
number of cycles was unknown, determining the T/R blade cycles by 
multiplying the T/R blade's hours TIS by 4 was required. For a T/R 
blade that, on the effective date of AD 2011-18-52, had already 
exceeded 600 hours TIS or 1,500 cycles, the AD required replacing the 
T/R blade with an airworthy T/R blade within 5 hours TIS.
    AD 2011-18-52 also required, within 25 hours TIS, and thereafter at 
intervals not to exceed 25 hours TIS, inspecting the T/R blade for a 
crack or damage that exceeds the limits of the applicable maintenance 
manual. The inspection was required to be accomplished using a mirror, 
magnifying glass (5X or greater), and light source; or borescope. If 
there was a crack, or if there was damage that exceeded the limits of 
the applicable maintenance manual, AD 2011-18-52 required, before 
further flight, replacing the T/R blade with an airworthy T/R blade.
    AD 2011-18-52 was prompted by a fatal accident involving an Agusta 
Model AW139 helicopter, which may have been caused by cracks in a T/R 
blade. EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA Emergency AD 2011-0156-E, dated August 25, 
2011 (EASA AD 2011-0156-E) to require repetitive inspections and 
reducing the life limit of the T/R blades. According to EASA, this 
condition, if not detected and corrected, could result in failure of a 
T/R blade and subsequent loss of control of the helicopter.
    After the FAA issued AD 2011-18-52, EASA issued a series of ADs as 
follows:
     EASA AD 2012-0030, dated February 17, 2012 (EASA AD 2012-
0030), which superseded Emergency AD 2011-0156-E, advised that the 
manufacturer developed improved, newly-designed T/R blades P/N 
3G6410A00132 and P/N 4G6410A00132, established life limits for each 
improved T/R blade, added repetitive inspections for the improved T/R 
blades, and advised that each T/R blade P/N had its own individual life 
limit.
     EASA AD 2012-0076, dated May 2, 2012 (EASA AD 2012-0076), 
which superseded EASA AD 2012-0030 and was issued after the 
manufacturer developed another version of improved T/R blades P/N 
3G6410A00133 and P/N 4G6410A00133 with different materials. AD 2012-
0076 required interim life limits for the new improved version of the 
T/R blades while also retaining the inspection requirements of EASA AD 
2012-0030.
     EASA AD 2012-0076R1, dated July 13, 2012 (EASA AD 2012-
0076R1), which revised EASA AD 2012-0076 after a modification was 
developed to allow installation of certain part-numbered T/R blades 
under certain conditions.
     EASA AD 2012-0076R2, dated February 20, 2014 (EASA AD 
2012-0076R2), which revised EASA AD 2012-0076R1, was issued after 
another modification was developed. EASA AD 2012-0076R2 requires 
removing the 25 hours TIS inspection of certain part-numbered T/R 
blades, extending the life

[[Page 38219]]

limit of certain part-numbered T/R blades, retaining the repetitive 
inspections of certain part-numbered T/R blades and depending on the 
inspection results, performing certain applicable corrections.
    Also, after AD 2011-18-52 was issued, the FAA issued an NPRM (78 FR 
54596), which published in the Federal Register on September 5, 2013. 
The NPRM proposed to require retaining the inspection requirements for 
certain part-numbered blades and expand the applicability to include 
the newly designed blades and establish life limits for those blades. 
The NPRM also proposed to require replacing any cracked blade or any 
blade that has reached its life limit. That NPRM was prompted by 
improved modifications of the T/R blades. However, because the FAA 
determined that the NPRM did not adequately address the identified 
unsafe condition, the NPRM was withdrawn on February 25, 2021 (86 FR 
11477).
    Additional review also revealed necessary changes to address the 
unsafe condition. Therefore, in the NPRM published in the Federal 
Register on May 10, 2021 (86 FR 24780), the FAA proposed to clarify the 
repetitive inspection for T/R blade P/Ns 3G6410A00131 and P/N 
4G6410A00131 from, ``visually inspect the T/R blade for a crack or 
damage'' to ``visually inspect the T/R blade for a crack and damage.'' 
The NPRM further proposed to revise that repetitive inspection from 
``damage that exceeds the limits of the applicable maintenance manual'' 
to ``damage that exceeds allowable limits'' to meet current publishing 
requirements. The NPRM also clarified the inspection area for that 
repetitive inspection by proposing to require using a figure in the 
related service information instead of using a figure in the body of 
the AD action. The NPRM also proposed to revise the requirements of AD 
2011-18-52 by removing unnecessary information, including the special 
flight permits paragraph.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these helicopters.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed AgustaWestland Mandatory Bollettino Tecnico No. 
139-265, Revision B, dated February 18, 2014. This service information 
specifies a precautionary inspection for a crack, a life limit for the 
affected T/R blades, and a quarantine of T/R blades that have exceeded 
their life limit. This service information also provides instructions 
for mixed usage of the affected T/R blades and sending certain data to 
the manufacturer.
    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.

Differences Between This AD and the EASA AD

    The EASA AD does not list the T/R blade life limits and instead 
references the Airworthiness Limitations Section of AW139 AMPI Chapter 
4, while this AD includes the life limits in the AD. The EASA AD 
requires reporting information to Product Support Engineering, whereas 
this AD does not. The EASA AD requires contacting AgustaWestland if a 
crack or damage is found during the inspection, whereas this AD 
requires removing the T/R blade from service.

Costs of Compliance

    The FAA estimates that this AD affects 130 helicopters of U.S. 
Registry and that operators may incur the following costs in order to 
comply with this AD. Labor costs are estimated at $85 per work-hour.
    Inspecting one T/R blade for a crack will take about 1 work-hour 
for an estimated cost of $85 per T/R blade per inspection cycle and up 
to $44,200 for the U.S. fleet per inspection cycle.
    Replacing one T/R blade will take about 8 work-hours and parts will 
cost about $40,560 for an estimated cost of $41,240 per replacement.

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.
    The FAA is 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

    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) Will not affect intrastate aviation in Alaska, and
    (3) 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.

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:
0
a. Removing Airworthiness Directive (AD) 2011-18-52, Amendment 39-17020 
(77 FR 23109, April 18, 2012); and
0
b. Adding the following new AD:

2021-14-18 Leonardo S.p.a. (Type Certificate Previously Held by 
Agusta S.p.A.): Amendment 39-21645; Docket No. FAA-2021-0348; 
Project Identifier 2018-SW-076-AD.

[[Page 38220]]

(a) Effective Date

    This airworthiness directive (AD) is effective August 24, 2021.

(b) Affected ADs

    This AD replaces AD 2011-18-52, Amendment 39-17020 (77 FR 23109, 
April 18, 2012) (AD 2011-18-52).

(c) Applicability

    This AD applies to Leonardo S.p.a. (type certificate previously 
held by Agusta S.p.A.) Model AB139 and AW139 helicopters, 
certificated in any category, with tail rotor (T/R) blade, part 
number (P/N) 3G6410A00131, 3G6410A00132, 3G6410A00133, 4G6410A00131, 
4G6410A00132, or 4G6410A00133, installed.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor 
Blades.

(e) Unsafe Condition

    This AD defines the unsafe condition as a crack in a T/R blade. 
This condition could result in failure of a T/R blade and subsequent 
loss of control of the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, within 5 
hours time-in-service (TIS) after May 3, 2012 (the effective date of 
AD 2011-18-52), establish a life limit of 600 hours TIS or 1,500 
takeoff and landing cycles (cycles), whichever occurs first, on the 
affected T/R blades and update the helicopter's historical records. 
If a T/R blade's total number of cycles is unknown, determine the T/
R blade cycles by multiplying the T/R blade's hours TIS by 4.
    (2) For T/R blade P/Ns 3G6410A00131 and 4G6410A00131, thereafter 
following paragraph (g)(1) of this AD, remove any T/R blade from 
service before accumulating 600 total hours TIS or 1,500 total 
cycles, whichever occurs first.
    (3) For T/R blade P/Ns 3G6410A00132, 3G6410A00133, 4G6410A00132, 
and 4G6410A00133, within 5 hours TIS after the effective date of 
this AD, determine the total number of cycles. If a T/R blade's 
total number of cycles is unknown, determine the T/R blade cycles by 
multiplying the blade's hours TIS by 4. Before further flight, 
remove any T/R blade from service that has accumulated or exceeded 
its life limit as follows. Thereafter, remove any T/R blade from 
service before accumulating its life limit as follows:
    (i) T/R blade P/Ns 3G6410A00132 and 4G6410A00132: 1,200 total 
hours TIS or 3,200 total cycles, whichever occurs first.
    (ii) T/R blade P/N 3G6410A00133: 40,000 total cycles.
    (iii) T/R blade P/N 4G6410A00133: 4,033 total hours TIS or 
40,000 cycles, whichever occurs first.
    Note 1 to paragraph (g)(3): A combination of T/R blades having 
different P/Ns can be installed on the same helicopter. The eligible 
combinations of T/R blades P/N are listed in AgustaWestland 
Mandatory Bollettino Tecnico No. 139-265, Revision B, dated February 
18, 2014 (BT No. 139-265).
    (4) For T/R blade P/Ns 3G6410A00131 and P/N 4G6410A00131, within 
25 hours TIS after the effective date of this AD, and thereafter at 
intervals not to exceed 25 hours TIS, visually inspect the T/R blade 
for a crack and damage that exceeds allowable limits. Inspect in the 
area depicted in Figure 1 of BT No. 139-265 using a mirror, a 5X or 
higher power magnifying glass, and a flashlight, or borescope. If 
there is a crack or damage that exceeds allowable limits, before 
further flight, remove the T/R blade from service.
    (5) As of the effective date of this AD, do not install on any 
helicopter any T/R blade P/N 3G6410A00131 or P/N 4G6410A00131, 
unless the actions required by paragraphs (g)(1), (2), and (4) of 
this AD have been accomplished.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (i)(1) of 
this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    (1) For more information about this AD, contact Matt Fuller, AD 
Program Manager, General Aviation & Rotorcraft Unit, Airworthiness 
Products Section, Operational Safety Branch, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
matthew.fuller@faa.gov.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2012-0076R2, dated February 20, 2014. You may view the EASA AD at 
https://www.regulations.gov in Docket No. FAA-2021-0348.

(j) 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 Mandatory Bollettino Tecnico No. 139-265, 
Revision B, dated February 18, 2014.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Leonardo S.p.A. Helicopters, Emanuele Bufano, Head of Airworthiness, 
Viale G.Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone 
+39-0331-225074; fax +39-0331-229046; or at https://www.leonardocompany.com/en/home.
    (4) You may view this service information at the 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.
    (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, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 2, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-15303 Filed 7-19-21; 8:45 am]
BILLING CODE 4910-13-P


