[Federal Register Volume 84, Number 236 (Monday, December 9, 2019)]
[Proposed Rules]
[Pages 67248-67251]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-26430]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Airbus Helicopters Model AS332L2 and EC225LP helicopters. This 
proposed AD would require 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 proposed AD is prompted by a report of torque loss on an MGB 
suspension bar bolt. The actions of this proposed AD are intended to 
address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by February 7, 
2020.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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.

[[Page 67249]]

     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 https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0019; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received, and other information. The 
street address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed 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 
review the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

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: 

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites 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.
    The FAA will file in the docket all comments received, as well as a 
report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, 
the FAA will consider all comments received on or before the closing 
date for comments. The FAA will consider comments filed after the 
comment period has closed if it is possible to do so without incurring 
expense or delay. The FAA may change this proposal in light of the 
comments received.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2017-0189, dated September 22, 
2017, to correct an unsafe condition for Airbus Helicopters (formerly 
Eurocopter, Eurocopter France, Aerospatiale) Model AS 332 L2 and EC 225 
LP helicopters. Following review of reported Model EC 225 LP data, 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.

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 proposing this AD 
after evaluating all known relevant information and determining 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

    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 service life limit (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 course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements

    This proposed AD would require for Airbus Helicopters Model AS332L2 
and EC225LP helicopters, within 30 hours time-in-service (TIS) and 
thereafter following each flight, re-calculating the life limit 
accumulated by each front bolt part number (P/N) 332A22-1613-21 or 
332A22-1613-20 and rear bolt P/N 332A22-1614-20 by applying an add-on 
factor listed in the applicable service information. If the bolt meets 
or exceeds its life limit, also known as SLL, this proposed AD would 
require removing the bolt from service before further flight.
    For Model AS332L2 helicopters, within 30 hours TIS and thereafter 
following each flight, this proposed AD would require re-calculating 
the life limit accumulated by the front attachment fitting P/N 332A22-
1623-01, rear left hand attachment fitting P/N 332A22-1624-02 or 
332A22-1624-04, and rear right hand attachment fitting P/N 332A22-1624-
03 or 332A22-1624-05 by applying an add-on factor listed in the 
applicable service information. If the fitting meets or exceeds its 
life limit, this proposed AD would require removing the fitting from 
service before further flight.
    For Model AS332L2 helicopters, within 150 hours TIS (without 
applying an add on-factor), this proposed AD would require 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 
proposed AD would 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, this proposed AD would require tightening the 
nut before further flight and removing the nut and its bolt from 
service within 150 hours TIS.

[[Page 67250]]

Differences Between This Proposed 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 AS332L2 helicopters 
instead and depending on the outcome, removing the nut and its bolt 
from service.

Costs of Compliance

    The FAA estimates that this proposed AD affects 23 helicopters of 
U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this proposed AD.
    Determining the adjusted life limit for the bolts and fittings 
would take about 0.5 work-hour for an estimated cost of $43 per 
helicopter and $989 for the U.S. fleet. Replacing a bolt would take 
about 4 work-hours and parts would 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 proposed 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 products identified in this rulemaking action.

Regulatory Findings

    The FAA 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. 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.
    The FAA 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):

Airbus Helicopters: 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) Comments Due Date

    The FAA must receive comments by February 7, 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

[[Page 67251]]

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 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 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 
the AD Docket.

(h) Subject

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

    Issued in Fort Worth, Texas, on November 29, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-26430 Filed 12-6-19; 8:45 am]
 BILLING CODE 4910-13-P