Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 85, Number 66 (Monday, April 6, 2020)]
[Rules and Regulations]
[Pages 19080-19082]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-07138]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-1015; Product Identifier 2018-SW-104-AD; Amendment 
39-19882; AD 2020-06-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. This AD requires determining the accumulated hours time-
in-service (TIS) of certain part-numbered main gearbox (MGB) suspension 
bar attachment fittings (fittings) and bolts, and establishes new life 
limits. This AD was prompted by the outcome of tests and analyses 
performed by Airbus Helicopters. The actions of this AD are intended to 
address an unsafe condition on these products.

DATES: This AD is effective 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 the 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-2019-1015; 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 Union 
Aviation Safety Agency (previously European 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: 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 67246, 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 AS332C, AS332C1, AS332L, and AS332L1 helicopters, with an MGB 
suspension bar right-hand side (RH) rear fitting part number (P/N) 
330A22-2702-07 and bolt P/N 330A22-0135-20, MGB suspension bar left-
hand side (LH) rear fitting P/N 330A22-2702-06 and bolt P/N 330A22-
0135-20, or MGB suspension bar front bolt P/N 330A22-0134-20 installed. 
The NPRM proposed to require within 50 hours TIS, reviewing the 
helicopter records to determine the total hours TIS of the MGB 
suspension bar RH and LH rear fittings. The NPRM also proposed to 
require removing from service the RH rear fitting and its bolts and the 
LH rear fitting and its bolts based on the accumulated total hours TIS 
of the fittings and other conditions. Thereafter, the NPRM proposed to 
require removing from service the RH rear fitting and its bolts at 
intervals not to exceed 1,470 hours TIS, removing from service the LH 
rear fitting at intervals not to exceed 13,600 hours TIS, and removing 
from service the LH rear bolts during each Major Inspection ``G.'' 
Finally, the NPRM proposed to require removing from service the front 
bolts during each Major Inspection ``G.''
    The proposed requirements were intended to prevent structural 
failure of the MGB suspension bar fittings and bolts, possibly 
resulting in detachment of the MGB suspension bars.
    The NPRM was prompted by EASA AD No. 2018-0260, dated December 3, 
2018, 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 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. From 
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 
screws (bolts). Due to design similarities, Model AS 332 C, AS 332 C1, 
AS 332 L, and AS 332 L1 helicopters could also be affected by the same 
installation condition.

[[Page 19081]]

Investigations determined that a life limit reduction of the MGB 
suspension bar fittings and screws was necessary for these model 
helicopters.
    EASA states that this condition, if not corrected, could lead to 
structural failure of the MGB suspension bar fittings and screws, 
possibly resulting in detachment of the MGB suspension bars. 
Accordingly, the EASA AD requires determining the accumulated service 
life of the affected parts and introduced new life limits.

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.

Interim Action

    The FAA considers this AD to be an interim action. The design 
approval holder is currently developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA might 
consider additional rulemaking.

Differences Between This AD and the EASA AD

    The EASA AD allows an option for the first MGB RH rear fitting 
replacement to inspect torque and specifies different replacement 
compliance times based on the torque inspection results, whereas this 
AD does not.

Related Service Information

    The FAA reviewed Airbus Helicopters Alert Service Bulletin No. 
AS332-01.00.90, Revision 0, dated November 21, 2018. This service 
information specifies determining the accumulated hours TIS of certain 
part-numbered rear MGB suspension bar fittings and screws. This service 
information further specifies criteria to determine the initial 
replacement compliance time of those parts and a new life limit for 
those parts thereafter. This service information also establishes a 
life limit for the front MGB attachment screws.

Costs of Compliance

    The FAA estimates that this AD affects 14 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 total hours TIS of the rear MGB fittings takes 
about 0.5 work-hour for an estimated cost of $43 per helicopter and 
$602 for the U.S. fleet.
    Replacing a rear MGB fitting and its set of four bolts takes about 
8 work-hours and parts cost about $12,937, for an estimated cost of 
$13,617 per replacement cycle.
    Replacing a set of four MGB attachment bolts takes about 4 work-
hours and parts cost about $224, for an estimated cost of $564 per 
replacement cycle.
    Replacing a LH rear MGB fitting takes about 8 work-hours and parts 
cost about $12,713, for an estimated cost of $13,393 per replacement 
cycle.

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):

2020-06-13 Airbus Helicopters: Amendment 39-19882; Docket No. FAA-
2019-1015; Product Identifier 2018-SW-104-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category, with 
a main gearbox (MGB) suspension bar right-hand side (RH) rear 
attachment fitting (fitting) part number (P/N) 330A22-2702-07 and 
bolt P/N 330A22-0135-20, MGB suspension bar left-hand side (LH) rear 
fitting P/N 330A22-2702-06 and bolt P/N 330A22-0135-20, or MGB 
suspension bar front bolt P/N 330A22-0134-20 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as MGB suspension bar 
fittings and bolts remaining in service beyond their fatigue life. 
This condition could result in failure of an MGB attachment 
assembly, detachment of an MGB suspension bar, and subsequent 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 50 hours time-in-service (TIS), review records to 
determine the total hours TIS of each MGB suspension bar RH and LH 
rear fitting.
    (i) For any RH rear fitting that has accumulated 1,470 or more 
total hours TIS,

[[Page 19082]]

before further flight, remove from service the RH rear fitting and 
its bolts.
    (ii) For any RH rear fitting that has accumulated less than 
1,470 total hours TIS, remove from service the RH rear fitting and 
its bolts before the fitting accumulates 1,470 total hours TIS.
    (iii) For any LH rear fitting that has accumulated 13,600 or 
more total hours TIS, before further flight, remove from service the 
LH rear fitting and its bolts.
    (iv) For any LH rear fitting that has accumulated less than 
13,600 total hours TIS:
    (A) If a Major Inspection ``G'' has not been completed since the 
LH rear fitting has been installed, remove from service the LH rear 
bolts during the next Major Inspection ``G'' inspection; or
    Note 1 to paragraph (e)(1)(iv)(A) of this AD: Major Inspection 
``G'' (7,500 hours TIS between overhauls) is defined in Maintenance 
Manual MET 05-29-00-601.
    (B) If a Major Inspection ``G'' has been completed since the LH 
rear fitting has been installed, before further flight, remove from 
service the LH rear bolts; and
    (C) Remove from service the LH rear fitting before the fitting 
accumulates 13,600 total hours TIS.
    (2) Thereafter following paragraph (e)(1) of this AD, remove 
from service any RH rear fitting and its bolts at intervals not to 
exceed 1,470 hours TIS, remove from service any LH rear fitting at 
intervals not to exceed 13,600 hours TIS, and remove from service 
any LH rear bolts during each Major Inspection ``G.''
    (3) During the next Major Inspection ``G,'' remove from service 
the MGB suspension bar front bolts. Thereafter, remove from service 
the front bolts during each Major Inspection ``G.''

(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

    (1) Airbus Helicopters Alert Service Bulletin No. AS332-
01.00.90, Revision 0, dated November 21, 2018, which is not 
incorporated by reference, contains 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 the referenced 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 Union 
Aviation Safety Agency (previously European Aviation Safety Agency) 
(EASA) AD No. 2018-0260, dated December 3, 2018. You may view the 
EASA AD on the internet at https://www.regulations.gov in Docket No. 
FAA-2019-1015.

(h) Subject

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

    Issued on March 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-07138 Filed 4-3-20; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:02:57.355270+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

b9b121b5cbe05b2c7e4ec45e3cc60c477c850664552493c0e287b37d610e1695

Text SHA-256

b853765b4f132a05ba5cc711b9de74e638876ca9b3218a9532f989a6ef09b4ac