[Federal Register Volume 84, Number 203 (Monday, October 21, 2019)]
[Rules and Regulations]
[Pages 56109-56112]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-22567]



[[Page 56109]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0738; Product Identifier 2019-SW-017-AD; Amendment 
39-19749; AD 2019-19-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model EC225LP helicopters. This AD requires 
determining the total hours time-in-service (TIS) of the free wheel 
shafts of certain main rotor gearboxes (MGBs), replacing the MGB or 
right-hand side (RH) free wheel shaft, installing placard(s), and 
revising the Rotorcraft Flight Manual (RFM) for your helicopter. This 
AD was prompted by a report of wear of the ramps of the RH free wheel 
shaft. The actions of this AD are intended to address an unsafe 
condition on these products.

DATES: This AD becomes effective November 5, 2019. The FAA must receive 
comments on this AD by December 20, 2019.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://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.
     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 http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0738; 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 (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 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 
http:/www.helicopters.airbus.com/website/en/ref/Technical-
Support_73.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: Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, 
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and the FAA did not provide you with notice and an opportunity 
to provide your comments prior to it becoming effective. However, 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 resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, 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 them 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 rulemaking during the 
comment period. The FAA will consider all the comments received and may 
conduct additional rulemaking based on those comments.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2019-0152-E, dated June 28, 
2019, to correct an unsafe condition for Airbus Helicopters (AH), 
formerly Eurocopter, Eurocopter France, Model EC 225 LP helicopters 
with MGB part number (P/N) 332A325001.XX, P/N 332A325002.XX, or P/N 
332A325003.XX equipped with main reduction gear module P/N 
332A325011.XX, P/N 332A325012.XX, or P/N 332A325013.XX in post-mod 07-
53016 configuration installed, where XX represents any dash number, and 
with RH free wheel shaft P/N 332A322191.20 (16-roller free wheel) 
installed. EASA advises of a report of wear of the ramps and a broken 
roller cage of the RH free wheel shaft that were discovered during 
overhaul of an MGB. EASA states an investigation to determine the root 
cause of the occurrence is ongoing. EASA advises that this condition, 
if not corrected, could lead to reduced capacity to transfer one engine 
inoperative (OEI) power delivered by the right side engine following an 
event of in-flight shut down of the left side engine, resulting in 
reduced control of the helicopter.
    Accordingly, the EASA AD requires repetitive replacement of the 
affected MGBs, installing placards that specify an operational 
limitation for OEI training flights, and introduces conditions for 
installing a replacement MGB. EASA states its AD is considered an 
interim action and further AD action may follow.

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 the EASA 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 the same type design.

Related Service Information

    Airbus Helicopters has issued Emergency Alert Service Bulletin No. 
04A016, Revision 1, dated June 28, 2019, which specifies procedures to 
determine the total hours TIS of the free wheel shafts, a life limit 
schedule and instructions to replace the MGB or RH free wheel shaft, 
and instructions to install one or two labels (placards) in view of 
both pilots about OEI training procedures.

[[Page 56110]]

AD Requirements

    This AD requires determining the total hours TIS of each free wheel 
shaft. For the purpose of this AD, if the total hours TIS of the RH and 
LH free wheel shafts are different, the greater number of total hours 
TIS will be considered as the RH free wheel shaft total hours TIS. If 
the RH free wheel shaft has accumulated 1,000 or more total hours TIS, 
or before the RH free wheel shaft exceeds 1,000 total hours TIS, this 
AD requires replacing the MGB with an airworthy MGB or replacing the RH 
free wheel shaft. This AD also requires installing placard(s) in full 
view of both pilots and revising the RFM for your helicopter with OEI 
training procedures pertaining to the ``TRAINING IDLE'' switches. As an 
option, this AD specifies installing alternate MGB configurations that 
would constitute terminating action for the requirements of this AD.

Differences Between This AD and the EASA AD

    The EASA AD requires repetitive replacement of the MGB, whereas 
this AD requires an initial replacement of the MGB instead. The FAA 
plans to publish a notice of proposed rulemaking to give the public an 
opportunity to comment on this longer-term requirement. This AD 
requires revising the RFM for your helicopter, whereas the EASA AD does 
not.

Interim Action

    The FAA considers this AD to be an interim action. Repetitively 
replacing the MGB at a longer interval is also necessary. However, the 
planned compliance time for the repetitive replacement would allow 
enough time to provide notice and opportunity for prior public comment 
on the merits of the replacement.

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 hours TIS of each free wheel shaft takes about 0.25 
work-hour, for an estimated cost of $21 per helicopter and $483 for the 
U.S. fleet. Installing placard(s) and revising the RFM for your 
helicopter takes about 0.5 work-hour for an estimated cost of $43 per 
helicopter and $989 for the U.S. fleet. Replacing an MGB takes about 40 
work-hours and parts cost about $850,000 (overhauled), for an estimated 
cost of $853,400.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without seeking comment prior to the 
rulemaking.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies foregoing notice and comment prior to adoption of this rule 
because the required corrective actions must be completed within 10 
hours TIS. Therefore, notice and opportunity for prior public comment 
are impracticable and contrary to public interest pursuant to 5 U.S.C. 
553(b)(3)(B). In addition, for the reason(s) stated above, the FAA 
finds that good cause exists pursuant to 5 U.S.C. 553(d) for making 
this amendment effective in less than 30 days.

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 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, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.
    The FAA prepared an economic evaluation of the estimated costs to 
comply with this 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 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):

2019-19-13 Airbus Helicopters: Amendment 39-19749; Docket No. FAA-
2019-0738; Product Identifier 2019-SW-017-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC225LP helicopters, 
certificated in any category, with a main rotor gearbox (MGB) part 
number (P/N) 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX, 
with a main reduction gear module (main module), with modification 
(MOD) 07-53016 (16-roller free wheel of free wheel shaft P/N 
332A322191.20) installed, P/N 332A325011.XX, P/N 332A325012.XX, or 
P/N 332A325013.XX, with ``XX'' denoting any dash number.

(b) Unsafe Condition

    This AD defines the unsafe condition as wear of the ramps of the 
right-hand side (RH) free wheel shaft. During an in-flight shutdown 
of the left-hand side (LH) engine, this condition could result in 
reduced ability to transfer one engine inoperative (OEI) power from 
the RH engine to the main rotor, and subsequent reduced control of 
the helicopter.

(c) Effective Date

    This AD becomes effective November 5, 2019.

(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.

[[Page 56111]]

(e) Required Actions

    (1) Within 10 hours time-in-service (TIS), determine the total 
hours TIS of the RH and LH free wheel shafts since new or last RH 
free wheel shaft replacement during overhaul. For the purpose of 
this AD, if the total hours TIS of the RH and LH free wheel shafts 
are different, use the greater number of total hours TIS as the RH 
free wheel shaft total hours TIS.
    (i) If the total hours TIS of the RH free wheel shaft is 1,000 
or more hours TIS, before further flight, replace the MGB or replace 
the RH free wheel shaft under the supervision of an Airbus 
Helicopter Specialist that is qualified for this replacement.
    (ii) If the total hours TIS of the RH free wheel shaft is less 
than 1,000 hours TIS, before exceeding 1,000 hours TIS, replace the 
MGB or replace the RH free wheel shaft under the supervision of an 
Airbus Helicopter Specialist that is qualified for this replacement.
    (2) Within 10 hours TIS:
    (i) Install one or two self-adhesive placards on the instrument 
panel in full view of the pilot and co-pilot with 6-millimeter red 
letters on a white background that state the information contained 
in Figure 1 to paragraph (e)(2)(i) of this AD. Refer to Figure 1 of 
Airbus Helicopters Emergency Alert Service Bulletin No. 04A016, 
Revision 1, dated June 28, 2019, for an example of this placard.
[GRAPHIC] [TIFF OMITTED] TR21OC19.006

    (ii) After installing the placard(s) required by paragraph 
(e)(2)(i) of this AD, before further flight, revise the limitations 
section of the Rotorcraft Flight Manual (RFM) for your helicopter by 
adding the information in Figure 2 to paragraph (e)(2)(ii) of this 
AD, by inserting a copy of this AD, or by making pen-and-ink 
changes. This action may be done by the owner/operator (pilot) 
holding at least a private pilot certificate and must be entered 
into the aircraft records showing compliance with this AD by 
following 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). 
The record must be maintained as required by 14 CFR 91.417, 121.380, 
or 135.439
[GRAPHIC] [TIFF OMITTED] TR21OC19.007

    (3) After the effective date of this AD, do not install an MGB 
P/N 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX, with a 
main reduction gear module (main module), with modification (MOD) 
07-53016 (16-roller free wheel of free wheel shaft P/N 
332A322191.20) installed, P/N 332A325011.XX, P/N 332A325012.XX, or 
P/N 332A325013.XX, with ``XX'' denoting any dash number unless the 
requirements of paragraph (e)(2) of this AD have been accomplished.
    (4) As an optional terminating action for the requirements of 
this AD, install MGB P/N 332A325001.XX, P/N 332A325002.XX, or P/N 
332A325003.XX, with a main module (12-roller free wheel), without 
MOD 07-53016 installed, P/N 332A325011.XX, P/N 332A325012.XX, or P/N 
332A325013.XX, with ``XX'' denoting any dash number.

(f) Credit for Previous Actions

    Actions accomplished before the effective date of this AD by 
following the procedures specified in Airbus Helicopters Emergency 
Alert Service Bulletin No. 04A016, Revision 1, dated June 28, 2019, 
are considered acceptable for compliance with the corresponding 
requirements specified in paragraphs (e)(1) through (e)(2)(i) of 
this AD.

(g) Special Flight Permits

    A one-time special flight permit to a maintenance facility may 
be permitted.

(h) 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 
Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy 
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.

(i) Additional Information

    (1) Airbus Helicopters Emergency Alert Service Bulletin No. 
04A016, Revision 1, dated June 28, 2019, which is not incorporated 
by reference, contains additional information about the subject of 
this AD. For service information identified in

[[Page 56112]]

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 http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review 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 (EASA) No. 2019-0152-E, dated June 28, 2019. You may 
view the EASA AD on the internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2019-0738.

(j) Subject

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

    Issued in Fort Worth, Texas, on September 30, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-22567 Filed 10-18-19; 8:45 am]
 BILLING CODE 4910-13-P