
[Federal Register Volume 80, Number 10 (Thursday, January 15, 2015)]
[Rules and Regulations]
[Pages 1997-1999]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00543]



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  Federal Register / Vol. 80, No. 10 / Thursday, January 15, 2015 / 
Rules and Regulations  

[[Page 1997]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1058; Directorate Identifier 2014-SW-065-AD; 
Amendment 39-18053; AD 2014-26-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters (previously Eurocopter France) Model EC155B1 and AS 365 N3 
helicopters with a certain automated flight control system (AFCS) and 
with a Garmin global positioning system (GPS) installed. This AD 
requires revising the Rotorcraft Flight Manual (RFM) to prohibit using 
the autopilot coupled with a Localizer/Instrument Landing System (LOC/
ILS) or Very High Frequency Omnidirectional Range (VOR) approach. This 
AD is prompted by a report of unpredictable and unexpected roll 
oscillations during coupled LOC or VOR approaches.This condition, if 
not corrected, could result in loss of helicopter control.

DATES: This AD becomes effective January 30, 2015.
    We must receive comments on this AD by March 16, 2015.

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 or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the economic evaluation, and 
other information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this AD, contact Airbus 
Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.airbushelicopters.com/techpub. You may review the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
george.schwab@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite 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. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We were informed that an Airbus Helicopter Model EC155B1 helicopter 
experienced intermittent, unpredictable roll oscillations while 
attempting to capture the inbound course during coupled ILS and LOC 
approaches. Airbus Helicopters analyzed the issue through flight and 
laboratory tests and determined that, under certain circumstances 
related to physical location of the helicopter during initialization of 
the GPS, the Garmin GPS equipment declares the helicopter's position as 
invalid on the data output bus, even though the GPS correctly displays 
the position and other information. APM2000, part number 416-00297-163, 
an Airbus Helicopters AFCS, utilizes this GPS position from the output 
data bus to estimate ground speed. When the helicopter's position is 
declared invalid, the APM2000 AFCS calculates the estimated ground 
speed at zero, causing an adverse effect on the vectoring calculations 
(angle, speed, intercepts, etc.), which results in the unpredictable 
and unexpected roll oscillations.
    Airbus Helicopters reported that while it plans further tests on 
Model EC155 helicopters to determine short- and long-term solutions, it 
proposes in the interim that pilots, shortly before taxiing, confirm 
that the Garmin equipment is properly displaying the helicopter's 
``true present position'' and then press the AP RST (autopilot reset) 
switch overhead. Airbus Helicopters states that these steps will ensure 
the system functions correctly. The European Aviation Safety Agency has 
declined to issue an AD.
    We have determined that an unsafe condition exists whenever a 
helicopter with this part-numbered autopilot system installed attempts 
a coupled

[[Page 1998]]

LOC/ILS or VOR approach, and that this condition is not corrected by 
resetting the autopilot before taxiing. Rather, the issue continues 
until the autopilot system is manually disconnected. The pilot is not 
alerted that an issue exists until the VOR, LOC, and glide slope 
indications on the flight instrument panel when the intercept course 
capture fails to perform as expected. The autopilot system is intended 
to reduce a pilot's workload and for that reason is required to be 
functional when a single pilot is operating the helicopter under 
instrument flight rules. We are including the Model AS 365 N3 
helicopter in this AD because these helicopters may have the same 
technology installed and could experience the same unsafe condition.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. We are 
issuing this AD because we evaluated all the relevant information and 
determined the unsafe condition exists and is likely to exist or 
develop on other helicopters of these same type designs.

Related Service Information

    Airbus Helicopters has issued Technical Agreement AE-155-14-003-22, 
dated June 27, 2014, for Model EC155B1 helicopters, which advises of 
two procedures in order to prevent an anomaly with the autopilot in the 
LOC mode. The first procedure is to only stay on the GPS test page for 
a short time, and the second procedure is to reset the autopilot before 
taxiing.

AD Requirements

    This AD requires before further flight, revising the RFM by 
inserting a copy of this AD or by making pen-and-ink changes to 
prohibit using the autopilot coupled with a LOC/ILS or VOR approach. 
This AD also requires, for Model EC155B1 helicopters, revising the RFM 
to prohibit certain procedures for resetting the autopilot before 
taxiing.

Interim Action

    We consider 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, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this AD will affect 16 helicopters of U.S. 
Registry and that labor costs average $85 an hour. Based on these 
estimates, we expect that making pen-and-ink changes to the flight 
manual will require a half work-hour for a labor cost of about $43 per 
helicopter, or $688 for the U.S. fleet. No parts are needed.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because the unsafe condition can 
adversely affect control of the helicopter and the required corrective 
actions must be accomplished before further flight.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and contrary to 
the public interest and that good cause exists 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.
    We are 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

    We 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;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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.
    We 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.

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):

2014-26-02 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-18053; Docket No. FAA-2014-1058; Directorate Identifier 
2014-SW-065-AD.

(a) Applicability

    This AD applies to Model EC155B1 and AS 365 N3 helicopters with 
an automated flight control system APM2000 Auto Pilot Module, part 
number 416-00297-163, with a Garmin GNS- or GTN-series global 
positioning system (GPS) installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as an autopilot software 
design that incorrectly calculates the estimated ground speed at 
zero. This condition results in unpredictable roll oscillations 
during a coupled Very High Frequency Omnidirectional Range (VOR) or 
Localizer/Instrument Landing System (LOC/ILS) approach, which could 
result in loss of helicopter control.

(c) Effective Date

    This AD becomes effective January 30, 2015.

(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 1999]]

(e) Required Actions

    Before further flight, insert a copy of this AD in the 
Rotorcraft Flight Manual or make the following pen-and-ink changes:
    (1) In the Eurocopter EC 155B1 Flight Manual, under Limitations 
(Prohibited Maneuvers) add: ``Coupled LOC/VOR approaches.''
    (2) In the Airbus Helicopters Flight Manual EC155B1:
    (i) Under Limitations, add: ``Autopilot coupled with a LOC/ILS 
or VOR approach is prohibited.''
    (ii) Under Normal Procedures, remove paragraphs 4.2 (Power-on 
GPS on Ground or In Flight) and 4.3 (Pre-taxiing checklist) in their 
entirety. Performing the procedures in Paragraphs 4.2 and 4.3 is 
prohibited.
    (3) In the Eurocopter Flight Manual AS 365 N3, under 
Limitations, add: ``Autopilot coupled with a LOC/ILS or VOR approach 
is prohibited.''

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: George Schwab, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email george.schwab@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest 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

    For service information identified in this AD, contact Airbus 
Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at http://www.airbushelicopters.com/techpub. You may review a copy 
of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 2210, Autopilot 
System.

    Issued in Fort Worth, Texas, on December 4, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-00543 Filed 1-14-15; 8:45 am]
BILLING CODE 4910-13-P


