[Federal Register Volume 86, Number 62 (Friday, April 2, 2021)]
[Rules and Regulations]
[Pages 17285-17287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-06783]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0912; Product Identifier 2015-SW-071-AD; Amendment 
39-21492; AD 2021-07-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 82-20-05 
for Societe Nationale Industrielle Aerospatiale (now Airbus 
Helicopters) Model AS-350 and AS-355 series helicopters. AD 82-20-05 
required inspecting and establishing a life limit for the tail rotor 
(TR) drive shaft bearing (bearing). This new AD requires replacing 
certain part-numbered TR bearings with one part-numbered bearing and 
repetitively inspecting one part-numbered bearing. This AD was prompted 
by inconsistencies that have been identified between inspections and 
maintenance actions required by ADs and inspections and maintenance 
actions specified in the applicable maintenance manual. The actions of 
this AD are intended to address an unsafe condition on these products.

DATES: This AD is effective May 7, 2021.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at 
https://www.airbus.com/helicopters/services/technical-support.html. You 
may view this referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2020-0912; 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 AD, the European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, 
any comments received, and other information. The street 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: Bang Nguyen, Aerospace Engineer, 
Structures Certification Section, Fort Worth ACO Branch, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to remove AD 82-20-05, Amendment 39-4466 (47 FR 43018, 
September 30, 1982) (AD 82-20-05), and add a new AD. AD 82-20-05 
applied to Societe Nationale Industrielle Aerospatiale (now Airbus 
Helicopters) Model AS-350 and AS-355 series helicopters. The NPRM 
published in the Federal Register on October 14, 2020 (85 FR 64995) and 
proposed to apply to Airbus Helicopters Model AS350B, AS350B1, AS350B2, 
AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, 
AS355F2, AS355N, and AS355NP helicopters with a bearing part number (P/
N) 593404, 6007-2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or 
manufacturer part number (MP/N) 704A33-651-010, 704A33-651-111, 704A33-
651-143, or 704A33-651-181 installed. The NPRM proposed to require, 
within 100 hours time-in-service (TIS), and thereafter at intervals not 
to exceed 165 hours TIS, for helicopters with certain part-numbered 
bearings installed, inspecting each bearing holder damper bushing for 
wear, a crack, tears, and play between each bushing and support plate; 
each bearing holder for a crack, fretting, and corrosion around the 
attachment holes; and each rubber sleeve for rotation, crazing, play 
between the inner races and the rubber sleeve, and lack of integrity of 
the elastomer. Depending on the inspection results, the NRPM proposed 
to require removing certain parts from service. The NPRM also proposed 
to require making a mark with white paint on the rubber sleeves and on 
the shaft within 100 hours TIS. For helicopters with bearing P/N 6007-
2RS1MT47CA, P9107NPP7,

[[Page 17286]]

83A851BC3, or 83A851B-1C3, or MP/N 704A33-651-010, 704A33-651-111, or 
704A33-651-143 installed, the NPRM proposed to require removing those 
part numbered bearings from service and installing bearing P/N 593404 
or MP/N 704A33-651-181. The NPRM also proposed to prohibit installing 
certain bearings on any helicopter.
    The NPRM was prompted by EASA AD 2015-0195, dated September 23, 
2015 (EASA AD 2015-0195), issued by EASA, which is the Technical Agent 
for the Member States of the European Union, to correct an unsafe 
condition for Airbus Helicopters Model AS 350 B, BA, BB, B1, B2, B3, 
and D, and AS 355 E, F, F1, F2, N, and NP helicopters with certain part 
numbered bearings installed. EASA advises that after inconsistencies 
were identified between inspections and maintenance actions required by 
French Civil Aviation Authority ADs and EASA ADs, Airbus Helicopters 
issued service information to specify replacing four different part 
numbered bearings with one bearing P/N 593404 (also listed as MP/N 
704A33-651-181) and to provide inspection procedures for the new 
bearing. Accordingly, EASA AD 2015-0195 retains the inspections for the 
older design bearings, requires replacing the bearings with the new 
bearings, and requires repetitive inspections for the new bearings.

Comments

    After the NPRM was published, the FAA received comments from two 
commenters.

Request

    Both commenters stated that the recurring 165 hour TIS inspections 
for TR bearing P/N 593404 and MP/N 704A33-651-181 are already captured 
in the FAA-approved manufacturer Airworthiness Limitations Schedule 
(ALS) as a 150 hour recurring inspection, and should not be part of 
this AD. One of the commenters added that the AD's recurring inspection 
would create a double sign-off and more paperwork.
    The FAA disagrees. Operators may not have to follow the version of 
the ALS referred to by the commenters because operators might be 
following an older or newer version depending on the delivery date of 
the helicopter. Additionally, the repetitive inspections required by 
this AD must be accomplished at intervals not to exceed 165 hours TIS; 
if operators accomplish these inspections every 150 hours TIS as stated 
in the ALS, they are meeting the AD's required compliance time.

FAA's Determination

    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 of the 
unsafe condition described in its AD. The FAA is issuing this AD after 
evaluating all of the information provided by EASA and determining 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.

Differences Between This AD and the EASA AD

    The EASA AD requires replacing the older design bearings within 10 
months, while this AD requires replacing the bearings within 100 hours 
TIS instead. The EASA AD applies to Model AS350BB helicopters, whereas 
this AD does not as this model helicopter is not FAA type-certificated. 
Finally, this AD applies to Model AS350C and AS350D1 helicopters as 
they have the same bearings installed, and the EASA AD does not.

Related Service Information

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS355-01.00.57, Revision 2, dated January 19, 2016, for Model AS355 
helicopters, and ASB AS350-01.00.70, Revision 1, dated September 21, 
2015, for Model AS350 helicopters. This service information describes 
procedures for inspecting bearing P/N 593404 and MP/N 704A33-651-181 
for position, condition, and wear. This service information also 
advises customers that older designed bearings are not fit for flight, 
and specifies replacing the older designed bearings with new bearing P/
N 593404 or MP/N 704A33-651-181. This service information also 
references procedures for repetitively inspecting the newer bearings.

Costs of Compliance

    The FAA estimates that this AD will affect 915 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this AD.
    For Model AS350 B, BA, B1, B2, B3, and C helicopters, inspecting 
the bearings takes about 2.5 work hours, for an estimated cost of $213 
per helicopter per inspection cycle. Replacing each bearing with a 
single part numbered bearing takes about 2.5 work hours and parts cost 
about $1,225, for an estimated cost of $1,438 per helicopter.
    For Model AS350 D, D1, and AS355-series helicopters, inspecting the 
bearings takes about 3 work hours, for an estimated cost of $255 per 
helicopter per inspection cycle. Replacing each bearing with a single 
part numbered bearing takes about 3 work hours and parts cost about 
$1,470, for an estimated cost of $1,725 per helicopter.
    Making a mark with white paint on the rubber sleeves and shaft 
takes a minimal amount of time and has a nominal parts cost.

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

    The FAA has 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) 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.

[[Page 17287]]

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:
0
a. Removing Airworthiness Directive (AD) 82-20-05, Amendment 39-4466 
(47 FR 43018, September 30, 1982); and
0
b. Adding the following new AD:

2021-07-15 Airbus Helicopters: Amendment 39-21492; Docket No. FAA-
2020-0912; Product Identifier 2015-SW-071-AD.

(a) Applicability

    This airworthiness directive (AD) applies to Airbus Helicopters 
Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, 
AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters, certificated in any category, with a tail rotor (TR) 
drive shaft bearing (bearing) part number (P/N) 593404, 6007-
2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or manufacturer 
part number (MP/N) 704A33-651-010, 704A33-651-111, 704A33-651-143, 
or 704A33-651-181, installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure or seizure of a 
TR bearing, which if not corrected could result in loss of the TR 
drive and subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 82-20-05, Amendment 39-4466 (47 FR 43018, 
September 30, 1982).

(d) Effective Date

    This AD becomes effective May 7, 2021.

(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) For helicopters with TR bearing P/N 593404 or MP/N 704A33-
651-181 installed, within 100 hours time-in-service (TIS) and 
thereafter at intervals not to exceed 165 hours TIS:
    (i) Inspect each bearing holder damper bushing for wear, a 
crack, tears, and play between each bushing and support plate. If 
there is any wear, a crack, tears, or play between the bushing and 
support plate, remove the bearing holder damper bushing from 
service.
    (ii) Inspect each bearing holder for a crack, fretting, and 
corrosion around the attachment holes. If there is a crack, 
fretting, or corrosion, remove the bearing holder from service.
    (iii) Inspect each rubber sleeve for rotation, crazing, play 
between the inner races and the rubber sleeve, and lack of integrity 
of the elastomer. For the purposes of this inspection, lack of 
integrity may be indicated by brittle or cracked rubber. If there is 
any rotation, crazing, play between the inner races and the rubber 
sleeve, or lack of integrity of the elastomer, remove the rubber 
sleeve from service.
    (2) Within 100 hours TIS:
    (i) Make a mark with white paint on the rubber sleeves and on 
the shaft.
    (ii) For helicopters with TR shaft bearing P/N 6007-2RS1MT47CA, 
P9107NPP7, 83A851BC3, or 83A851B-1C3, or MP/N 704A33-651-010, 
704A33-651-111, or 704A33-651-143 installed, remove the affected 
bearings from service and replace with bearing P/N 593404 or MP/N 
704A33-651-181.
    (3) After the effective date of this AD, do not install bearing 
P/N 6007-2RS1MT47CA, P9107NPP7, 83A851BC3, or 83A851B-1C3, or MP/N 
704A33-651-010, 704A33-651-111, or 704A33-651-143 on any helicopter.

(g) 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: Bang Nguyen, Aerospace Engineer, Structures 
Certification Section, Fort Worth ACO Branch, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; Information may 
be emailed to: [email protected].
    (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.

(h) Additional Information

    (1) Airbus Helicopters Alert Service Bulletin (ASB) No. AS355-
01.00.57, Revision 2, dated January 19, 2016, and Airbus Helicopter 
ASB No. AS350-01.00.70, Revision 1, dated September 21, 2015, which 
are not incorporated by reference, contain additional information 
about the subject of this AD. For service information identified in 
this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand 
Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972-
641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of the service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2015-0195, dated September 23, 2015. You may view the EASA AD on the 
internet at https://www.regulations.gov in Docket FAA-2020-0912.

(i) Subject

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

    Issued on March 25, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-06783 Filed 4-1-21; 8:45 am]
BILLING CODE 4910-13-P