AD 2013-12-06

[Federal Register Volume 78, Number 131 (Tuesday, July 9, 2013)]
[Rules and Regulations]
[Pages 40956-40958]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-16388]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0520; Directorate Identifier 2013-SW-027-AD; 
Amendment 39-17484; AD 2013-12-06]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland (Eurocopter) 
Helicopters

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

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, and MBB-
BK117 C-2 helicopters with a Metro Aviation (Metro) vapor-cycle air 
conditioning kit installed in accordance with Supplemental Type 
Certificate (STC) No. SH3880SW. This AD requires repetitively 
inspecting the air conditioning drive pulley (pulley) for looseness and 
properly installed lockwire, and also requires reinstalling the pulley. 
This AD is prompted by two reports of the pulley detaching from the 
rotor brake disc on the tail rotor (T/R) driveshaft. These actions are 
intended to prevent separation of the pulley, damage to the T/R 
driveshaft, and subsequent loss of control of the helicopter.

DATES: This AD becomes effective July 24, 2013.
    We must receive comments on this AD by September 9, 2013.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 STC, the economic 
evaluation, any comments received, 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 Metro 
Aviation, Inc., 1214 Hawn Ave, Shreveport, LA 71107; phone: (318) 222-
5529; Web site: <a href="http://metroproductsupport.com">metroproductsupport.com</a>. 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: Martin Crane, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5056; 
email <a href="/cdn-cgi/l/email-protection#a0978de1f6f38de1f3f78d919790e0c6c1c18ec7cfd6"><span class="__cf_email__" data-cfemail="c7f0ea869194ea869490eaf6f0f787a1a6a6e9a0a8b1">[email&#160;protected]</span></a>.

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,

[[Page 40957]]

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

    STC No. SH3880SW approves the installation of the Metro vapor-cycle 
air conditioning kit on Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4, 
MBB-BK117 B-1, and MBB-BK117 C-2 helicopters. The air conditioning 
compressor is driven by a pulley attached to the rotor brake disc. We 
received a report of a recent incident where the fasteners attaching 
the air conditioning compressor pulley to the rotor brake disc lost 
torque and allowed the pulley to separate. After the helicopter landed 
without incident, the pulley was discovered loose, rotating freely on, 
and causing damage to the T/R driveshaft. A prior incident in 2008 
occurred where the pulley mount bolts sheared, resulting in the pulley 
detaching from the rotor brake disc. Separation of the pulley from the 
rotor brake disc could damage the T/R driveshaft, resulting in 
subsequent loss of control of the helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all information 
provided by Metro and determined the unsafe condition exists and is 
likely to exist or develop on other helicopters of these same type 
designs.

Related Service Information

    We reviewed Metro Alert Service Bulletin No. MA145-21A-003, 
Revision A, dated April 26, 2013 (ASB MA145-21A-003), which describes 
procedures to inspect the pulley for properly installed lockwire, and 
for removing, inspecting, and re-installing the pulley.

AD Requirements

    This AD requires, before further flight, and thereafter at 
intervals not exceeding 10 hours time-in-service (TIS), inspecting the 
pulley for looseness and proper installation of the lockwire on the 
pulley mount bolts.
    Additionally, within 25 hours TIS, this AD requires removing the 
pulley, inspecting the bolts and mounting holes with a 10X or higher 
magnifying glass for damage or distortion, and re-installing the 
pulley. If there is any damage or distortion, this AD requires 
replacing the damaged pulley.

Differences Between This AD and the Manufacturer's Service Information

    This AD requires repetitively inspecting the pulley bolts every 10 
hours TIS; the ASB does not require the repetitive inspections after 
re-installing the pulley.
    This AD also applies to Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-
BK117 B-1, and MBB-BK117 C-2 helicopters; the ASB only applies to Model 
MBB-BK C-2 helicopters.

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 75 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. At an average labor rate of $85 per hour, 
inspecting the pulley will require about .5 work-hour, for a cost per 
helicopter of $43, and a total cost of $3,225 for the fleet per 
inspection cycle. Inspecting and re-installing the pulley will require 
about 2 work-hours, for a cost per helicopter of $170, and a total cost 
of $12,750 for the fleet.
    If necessary, replacing a damaged pulley would require about 2 
work-hours, and required parts would cost $525, for a total cost per 
helicopter of $695.

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 required corrective 
actions must be accomplished within 25 hours TIS or 30 calendar days, a 
very short time period based on the average flight hour utilization 
rate of these helicopters in the air ambulance and offshore operations 
industries.
    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 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:

[[Page 40958]]

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):

2013-12-06 Eurocopter Deutschland (Eurocopter): Amendment 39-17484; 
Docket No. FAA-2013-0520; Directorate Identifier 2013-SW-027-AD.

(a) Applicability

    This AD applies to Eurocopter Model MBB-BK 117 A-3, MBB-BK 117 
A-4, MBB-BK 117 B-1, and MBB-BK 117 C-2 helicopters with a Metro 
Aviation, Inc. (Metro) vapor-cycle air conditioning kit installed in 
accordance with Supplemental Type Certificate (STC) No. SH3880SW, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loosening of an air 
conditioning drive pulley (pulley) mount bolt, which could result in 
separation of the pulley from the rotor brake disc on the tail rotor 
(T/R) driveshaft, damage to the T/R driveshaft, and subsequent loss 
of control of the helicopter.

(c) Effective Date

    This AD becomes effective July 24, 2013.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time.

(e) Required Actions

    (1) Before further flight, and thereafter at intervals not 
exceeding 10 hours time-in-service (TIS), inspect the lockwire 
securing the pulley mount bolts for proper installation and the 
pulley for looseness. If the lockwire is damaged or broken, or is 
not installed in a tightening direction, or if the pulley is loose, 
remove and inspect the pulley as described in paragraphs (e)(2)(i) 
and (e)(2)(ii) of this AD.
    (2) Within 25 hours TIS:
    (i) Remove the pulley from the rotor brake disc and, using a 10X 
or higher power magnifying glass, inspect the bolts and mounting 
holes glass for damage or distortion. If there is any damage or 
distortion, replace the pulley.
    (ii) Install the pulley and torque each mount bolt to 90 inch-
pounds. After torqueing, determine whether a gap exists among each 
bolt head, washer, and the mating surface of the rotor brake disc. 
If there is a gap, replace the pulley.
    (iii) Lock wire each pulley mount bolt to its adjacent rotor 
brake mounting bolt with 0.6 millimeter lockwire.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Martin Crane, 
Aviation Safety Engineer, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 
76137; telephone (817) 222-5056; email <a href="/cdn-cgi/l/email-protection#b58298f4e3e698f4e6e298848285f5d3d4d49bd2dac3"><span class="__cf_email__" data-cfemail="093e24485f5a24485a5e24383e39496f6868276e667f">[email&#160;protected]</span></a>.
    (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.

(h) Additional Information

    (1) Metro Alert Service Bulletin No. MA145-21A-003, Revision A, 
dated April 26, 2013, which is not incorporated by reference, 
contains additional information about the subject of this AD. For 
service information identified in this AD, contact Metro Aviation, 
Inc., 1214 Hawn Ave, Shreveport, LA 71107; phone: (318) 222-5529; 
Web site: <a href="http://metroproductsupport.com">metroproductsupport.com</a>. 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.
    (2) STC No. SH3880SW, amended April 16, 2004, may be found on 
the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> in Docket No. FAA-2013-
0520.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6500: Tail Rotor 
Drive.

    Issued in Fort Worth, Texas, on June 13, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-16388 Filed 7-8-13; 8:45 am]
BILLING CODE 4910-13-P