[Federal Register Volume 77, Number 141 (Monday, July 23, 2012)]
[Rules and Regulations]
[Pages 42958-42962]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-17559]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0704; Directorate Identifier 2012-SW-040-AD; 
Amendment 39-17113; AD 2012-13-11]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

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 
Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and 
BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor 
pitch link spherical bearing for proper swaging. This AD is prompted by 
a report of a tail rotor pitch link with a spherical bearing that had 
migrated out of the bearing bore. The actions specified by this AD are 
intended to prevent failure of the tail rotor pitch link and subsequent 
loss of control of the helicopter.

DATES: This AD becomes effective August 7, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents August 7, 2012.
    We must receive comments on this AD by September 21, 2012.

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, 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 Able 
Engineering and Support Services, 2920 East Chambers Street, Phoenix, 
AZ 85040; telephone (602) 304-1227; fax (602) 304-1277; email 
[email protected]. You may review a copy of 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: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110; 
email [email protected].

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

[[Page 42959]]

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

    Able Engineering & Component Services (Able) received a report of a 
tail rotor pitch link with a spherical bearing that had migrated out of 
the bearing bore. Investigation by Able revealed that the migration 
resulted from the spherical bearing being improperly swaged during a 
repair process and that the affected parts were limited to those 
repaired after January 1, 2011. Able determined that an inspection of 
other tail rotor pitch links repaired after that date is necessary to 
determine their airworthiness and issued Alert Service Bulletin (ASB) 
No.: 2012-001, Revision IR, dfated March 7, 2012 (Able ASB).
    On March 19, 2012, Eurocopter issued one ASB with multiple numbers: 
Eurocopter Emergency Alert Service Bulletin (EASB) No. BO105 LS-30A-013 
for model BO-105LS A-3 helicopters; EASB No. BO105 LS A-3-STC-0654/
3058-30A-001 for model BO-105LS A-3 Superlifter helicopters; EASB No. 
MBB-BK117-30A-115 for model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 
helicopters; and EASB No. MBB-BK117 C-2-67A-016 for model MBB-BK117 C-2 
helicopters, all Revision 0. The EASB specifies complying with the 
inspection described in the Able ASB.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other helicopters of these same type 
designs.

Related Service Information

    We reviewed the Able ASB, which identifies certain tail rotor pitch 
links (pitch links) that are affected by the improper swaging of the 
spherical bearings. The Able ASB describes procedures to remove the 
pitch links and visually inspect the spherical bearings with an 8X 
magnifying glass for a bearing that has not been swaged and will 
migrate out of the bearing bore. If a pitch link is discovered with a 
bearing not properly swaged, the Able ASB specifies removing the pitch 
link from service and returning it to Able Engineering.

AD Requirements

    This AD requires:
     Removing the pitch link from the helicopter and cleaning 
the spherical bearings.
     Applying hand pressure to the bearing faces and inspecting 
with an 8X or higher power magnifying glass for complete swaging of the 
bearing bore.
     If the pitch link has not been completely swaged, removing 
the pitch link and replacing it with an airworthy pitch link.

Differences Between This AD and the Service Information

    The service information requires returning unairworthy pitch links 
to Able Engineering; this AD does not. The Eurocopter ASB applies to 
the Model BO105 LS A-3 ``Superlifter,'' and this AD does not as that 
model is not type certificated in the U.S.

Costs of Compliance

    We estimate that this AD will affect 130 helicopters of U.S. 
Registry, and that operators may incur the following costs in order to 
comply with this AD. Inspecting each pitch link will require about 1.5 
work hours at an average labor rate of $85 per hour, for a total cost 
per helicopter of about $127 and a cost to the U.S. operator fleet of 
$16,510. If required, replacing a pitch link with an airworthy pitch 
link will require about 1.5 work hours at an average labor rate of $85 
per hour, and required parts will cost $1,442, for a total cost per 
helicopter of about $1,569.

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 some of the 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 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 42960]]

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):

2012-13-11 Eurocopter Deutschland GmbH Helicopters: Amendment 39-
17113; Docket No. FAA-2012-0704; Directorate Identifier 2012-SW-040-
AD.

(a) Applicability

    This AD applies to Eurocopter Deutschland GmbH (ECD) Model MBB-
BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 
117 B-2, MBB-BK 117 C-1, MBB-BK 117 C-2, and BO-105LS A-3 
helicopters, with a tail rotor pitch link (pitch link) part number 
(P/N) 117-31821, 117-31822, or B642M1018101 with a serial number 
listed in Appendix 1 of Able Engineering & Component Services (Able) 
Alert Service Bulletin (ASB) No. 2012-001, Revision IR, dated March 
7, 2012, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as an improperly swaged 
spherical bearing on the pitch link, which could result in loss of 
tail rotor control and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes August 7, 2012.

(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

    For pitch links installed within the last 10 hours time-in-
service (TIS), before further flight; for all other affected pitch 
links, within the next 10 hours TIS:
    (1) Remove the pitch link.
    (2) Clean the area around the spherical bearings and pitch link 
bearing bore chamfer.
    (3) Apply axial hand pressure to the faces of both spherical 
bearings as shown in Figure 1 to Paragraph (e) of this AD.
[GRAPHIC] [TIFF OMITTED] TR23JY12.000


[[Page 42961]]


    (4) Using an 8X or higher power magnifying glass, inspect the 
boundaries between the bearing and the bearing bore chamfer surface. 
Determine that the bearings have been completely swaged and there is 
no gap between the edge of the bearing and the chamfer as shown in 
Figure 2 to Paragraph (e) of this AD.
[GRAPHIC] [TIFF OMITTED] TR23JY12.001

    (5) If a bearing is not completely swaged or there is a gap 
between the edge of the bearing and the chamfer, as shown in Figure 
3 to Paragraph (e) of this AD, replace the pitch link with an 
airworthy pitch link.

[[Page 42962]]

[GRAPHIC] [TIFF OMITTED] TR23JY12.002

(f) Special Flight Permits

    Special flight permits will not be issued.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Sharon Miles, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; 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, 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) Subject

    Joint Aircraft Service Component (JASC) Code: 6420: Tail Rotor 
Head.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Able Engineering & Component Services Alert Service Bulletin 
No. 2012-001, Revision IR, dated March 7, 2012.
    (ii) Reserved.
    (3) For Able Engineering & Component Services service 
information identified in this AD, contact Able Engineering & 
Component Services, 2920 East Chambers Street, Phoenix, AZ 85040; 
telephone (602) 304-1227; fax (602) 304-1277; email 
[email protected].
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.
    (5) You may also view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on July 2, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-17559 Filed 7-20-12; 8:45 am]
BILLING CODE 4910-13-P