[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19077-19080]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07140]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0019; Product Identifier 2017-SW-074-AD; Amendment 
39-19881; AD 2020-06-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD 
requires determining the accumulated hours time-in-service (TIS) of 
certain part-numbered main gearbox (MGB) suspension bar attachment 
bolts and fittings, applying a life limit add-on factor, and inspecting 
the torque of certain MGB suspension bar attachment nuts. This AD was 
prompted by a report of torque loss on an MGB suspension bar bolt. The 
actions of this AD are intended to address an unsafe condition on these 
products.

DATES: This AD is effective May 11, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of May 11, 2020.

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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0019.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2018-0019; or in person at Docket 
Operations between 9 a.m. and 5 p.m.,

[[Page 19078]]

Monday through Friday, except Federal holidays. The AD docket contains 
this AD, the European Union Aviation Safety Agency (previously European 
Aviation Safety Agency) (EASA) AD, any service information that is 
incorporated by reference, 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: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On December 9, 2019, at 84 FR 67248, the Federal Register published 
the FAA's notice of proposed rulemaking (NPRM), which proposed to amend 
14 CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model AS332L2 and EC225LP helicopters, with an MGB suspension bar front 
attachment bolt (bolt) part number (P/N) 332A22-1613-21 or 332A22-1613-
20, MGB suspension bar rear bolt P/N 332A22-1614-20, MGB suspension bar 
front attachment fitting (fitting) P/N 332A22-1623-01, MGB suspension 
bar rear left hand fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB 
suspension bar rear right hand fitting P/N 332A22-1624-03 or 332A22-
1624-05 installed.
    For Airbus Helicopters Model AS332L2 and EC225LP helicopters, the 
NPRM proposed to require, within 30 hours time-in-service (TIS), re-
calculating the life limit accumulated by each front and rear bolt by 
applying an add-on factor listed in the applicable service information. 
For each bolt that meets or exceeds its life limit, also known as 
service life limit (SLL), the NPRM proposed to require removing each 
bolt from service before further flight. For each bolt that has not 
exceeded its life limit, the NPRM proposed to require continuing to 
calculate and record the life limit of each bolt on its component 
history card or equivalent record and removing the bolt from service 
before reaching its life limit.
    For Model AS332L2 helicopters, the NPRM proposed to require, within 
30 hours TIS, re-calculating the life limit accumulated by the front, 
rear left hand, and rear right hand fittings by applying an add-on 
factor listed in the applicable service information. For each fitting 
that meets or exceeds its life limit, the NPRM proposed to require 
removing the fitting from service before further flight. For each 
fitting that has not exceeded its life limit, the NPRM proposed to 
require continuing to calculate and record the life limit of each 
fitting on its component history card or equivalent record and removing 
the fitting from service before reaching its life limit.
    For Model AS332L2 helicopters, the NPRM proposed to require, within 
150 hours TIS (without applying an add on-factor), inspecting the 
torque of each MGB suspension bar fitting front and rear nut. If the 
torque on any nut is higher than the maximum allowable limit, the NPRM 
proposed to require removing the nut and its bolt from service before 
further flight. If the torque on any nut is lower than the minimum 
allowable limit, the NPRM proposed to require tightening the nut before 
further flight and removing the nut and its bolt from service within 
150 hours TIS.
    The proposed requirements were intended prevent the MGB suspension 
bar bolts and fittings remaining in service beyond their fatigue life, 
which could result in structural failure of the MGB suspension bar and 
loss of helicopter control.
    The NPRM was prompted by EASA AD No. 2017-0189, dated September 22, 
2017, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition for Airbus 
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale) 
Model AS 332 L2 and EC 225 LP helicopters. EASA advises that the 
installation of the MGB upper deck fittings of the three MGB suspension 
bars could lead to tightening torque loss on the fittings' attachment 
pins (bolts). Due to design similarities, Model AS 332 L2 helicopters 
could also be affected by the same installation condition. An 
investigation determined that the life limits in the Airworthiness 
Limitations Sections for the pins and fittings are valid if an ``add-on 
penalty factor'' is applied.
    EASA states that this condition, if not corrected, could lead to 
structural failure of the MGB suspension bar attachment pins or 
fittings. Accordingly, the EASA AD requires applying the add-on penalty 
factor to the flight hours to re-calculate the life limits and 
replacing an affected part before exceeding its life limit. EASA 
further advises that Airbus Helicopters' initial service information 
contained an error that may have resulted in the installation of pins 
or fittings using an incorrect torque value. As a result, the EASA AD 
also requires replacing pins if an incorrect torque value was applied 
and reporting the information to Airbus Helicopters.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD, but the FAA did not receive any comments on the 
NPRM.

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 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 allows an optional 150 hours TIS extension to the life 
limit of an affected fitting for Model AS 332 L2 helicopters by 
performing dye-penetrant inspections. This AD does not allow this 
option. For Model AS 332 L2 helicopters, the EASA AD requires replacing 
pins (bolts) that are replacement pins installed before the AD's 
effective date with an incorrect torque value applied. This AD requires 
inspecting the torque for each nut for Model AS 332 L2 helicopters 
instead and depending on the outcome, removing the nut and its bolt 
from service. The EASA AD requires reporting certain information to 
Airbus Helicopters, while this AD does not.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Emergency Alert Service 
Bulletin (EASB) No. 01.00.86 for Model AS332 helicopters and Airbus 
Helicopters EASB No. 04A013 for Model EC225LP helicopters, both 
Revision 1 and dated August 25, 2017. This service information 
specifies applying an add-on factor to the flying hours logged by the 
pins and fittings and replacing them if the SLL is exceeded. If an 
incorrect tightening torque value was applied to the pins, the service 
information specifies replacing the pins and contacting Airbus 
Helicopters.
    This service information is reasonably available because the 
interested parties have access to it through their normal

[[Page 19079]]

course of business or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 23 helicopters of U.S. 
Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. Labor costs are estimated at $85 
per work-hour.
    Determining the adjusted life limit for the bolts and fittings 
takes about 0.5 work-hour for an estimated cost of $43 per helicopter 
and $989 for the U.S. fleet.
    Replacing a bolt takes about 4 work-hours and parts cost about $89 
for an estimated cost of $429 per bolt.
    There are no costs of compliance for replacing a fitting and 
inspecting, and if necessary tightening, the torque for Model AS332L2 
helicopters by this AD because there are no Model AS332L2 helicopters 
on the U.S. Registry.

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 helicopters 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.

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):

2020-06-12 Airbus Helicopters: Amendment 39-19881; Docket No. FAA-
2018-0019; Product Identifier 2017-SW-074-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332L2 and EC225LP 
helicopters, certificated in any category, with a main gearbox (MGB) 
suspension bar front attachment bolt (bolt) part number (P/N) 
332A22-1613-21 or 332A22-1613-20, MGB suspension bar rear bolt P/N 
332A22-1614-20, MGB suspension bar front attachment fitting 
(fitting) P/N 332A22-1623-01, MGB suspension bar rear left hand 
fitting P/N 332A22-1624-02 or 332A22-1624-04, or MGB suspension bar 
rear right hand fitting P/N 332A22-1624-03 or 332A22-1624-05 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as MGB suspension bar bolts 
and fittings remaining in service beyond their fatigue life and 
loose MGB suspension bar bolts or fittings, which could result in 
structural failure of the MGB suspension bar and loss of helicopter 
control.

(c) Effective Date

    This AD becomes effective May 11, 2020.

(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), review records to 
determine the total hours TIS of each MGB suspension bar bolt.
    (i) Determine the life limit of each bolt by applying the hours 
TIS by the add-on factor listed in Table No. 1 of Airbus Helicopters 
Emergency Alert Service Bulletin No. 01.00.86, Revision 1, dated 
August 25, 2017 (EASB 01.00.86), or Airbus Helicopters Emergency 
Alert Service Bulletin No. 04A013, Revision 1, dated August 25, 
2017, as applicable to your model helicopter.
    Note 1 to paragraph (e)(1)(i) of this AD: Airbus Helicopters 
refers to bolts as ``pins.''
    (A) Before further flight, remove from service any bolt that has 
reached or exceeded its life limit.
    (B) For each bolt that has not exceeded its life limit, continue 
to calculate and record the life limit on its component history card 
or equivalent record by applying the add-on factor each time the 
helicopter accumulates hours TIS, and remove from service any bolt 
before reaching its life limit.
    (ii) Thereafter following paragraph (e)(1)(i) of this AD, 
continue to calculate and record the life limit of each bolt on its 
component history card or equivalent record by applying the add-on 
factor each time the helicopter accumulates hours TIS and remove 
from service any bolt before reaching its life limit.
    (2) For Model AS332L2 helicopters, within 30 hours TIS, review 
records to determine the total hours TIS of each MGB suspension bar 
fitting.
    (i) Determine the life limit of each fitting by applying the 
hours TIS by the add-on factor listed in Table No. 1 of EASB 
01.00.86.
    (A) Before further flight, remove from service any fitting that 
has reached or exceeded its life limit.
    (B) For each fitting that has not exceeded its life limit, 
continue to calculate and record the life limit on its component 
history card or equivalent record by applying the add-on factor each 
time the helicopter accumulates hours TIS, and remove from service 
any fitting before reaching its life limit.
    (ii) Thereafter following paragraph (e)(2)(i) of this AD, 
continue to calculate and record the life limit of each fitting on 
its component history card or equivalent record by applying the add-
on factor each time the helicopter accumulates hours TIS and remove 
from service any fitting before reaching its life limit.
    (3) For Model AS332L2 helicopters, within 150 hours TIS (without 
the add-on factor), inspect the torque of each MGB suspension bar 
attachment front and rear nut. The allowable torque for each front 
nut is 602-663 lbf. in (6.8-7.5 daN.m) and the allowable torque for 
each rear nut is 337-398 lbf. in (3.8-4.5 daN.m).
    (i) If the torque on any nut is higher than the maximum 
allowable torque stated in paragraph (e)(3) of this AD, before 
further flight, remove from service the bolt and nut.
    (ii) If the torque on any nut is lower than the minimum 
allowable torque value stated in paragraph (e)(3) of this AD, before 
further flight, tighten the nut to the allowable torque stated in 
paragraph (e)(3) of this AD. Within 150 hours TIS (without the add-
on factor), remove from service any bolt and nut that were tightened 
as required by this paragraph.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
Matt Fuller, Senior Aviation Safety Engineer, Safety Management 
Section, Rotorcraft Standards Branch, FAA, 10101

[[Page 19080]]

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, the FAA suggests 
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 Union Aviation 
Safety Agency (previously European Aviation Safety Agency) (EASA) AD 
No. 2017-0189, dated September 22, 2017. You may view the EASA AD on 
the internet at https://www.regulations.gov in Docket No. FAA-2018-
0019.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor 
Gearbox.

(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) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 01.00.86, Revision 1, dated August 25, 2017.
    (ii) Airbus Helicopters EASB No. 04A013, Revision 1, dated 
August 25, 2017.
    (3) 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.
    (4) You may view this service information at 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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on March 25, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-07140 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P