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[Federal Register Volume 78, Number 164 (Friday, August 23, 2013)]
[Rules and Regulations]
[Pages 52410-52412]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19442]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0887; Directorate Identifier 2009-SW-02-AD; 
Amendment 39-17551; AD 2013-16-13]
RIN 2120-AA64

Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Eurocopter Deutschland GmbH (ECD) Model BO-105A, BO-105C, BO-105S, BO-
105LS A-1, BO-105LS A-3, 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, and MBB-BK 117 C-1 helicopters to 
require inspections for corrosion or thread damage to each tail rotor 
balance weight (weight) and each tail rotor control lever (lever). This 
AD was prompted by a European Aviation Safety Agency (EASA) AD and a 
Transport Canada Civil Aviation (TCCA) AD, both issued based on a 
report that corrosion was detected on a weight in the area of the 
attachment thread on a model BO-105 helicopter. The actions of this AD 
are intended to detect corrosion and thread damage in the threaded area 
of the weight and lever, and to prevent failure of a weight or lever, 
separation of tail rotor parts, severe vibration, and subsequent loss 
of control of the helicopter.

DATES: This AD is effective September 27, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of September 27, 
2013.

ADDRESSES: For service information identified in this AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.eurocopter.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, TX 76137.

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 EASA and TCCA ADs, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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 sharon.y.miles@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On August 29, 2012, at 77 FR 52265, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 to include an AD that would apply to ECD Model BO-105A, BO-
105C, BO-105S, BO-105LS A-1, BO-105LS A-3, MBB-BK 117 A-1, MBB-BK 117 
A-3, MBB-BK 117 A-4, MBB-BK117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 
helicopters with certain levers and weights installed. The NPRM 
proposed to require conducting repetitive visual inspections of each 
weight and lever and proposed procedures for installing a weight or 
lever. Additionally, the NPRM proposed allowable tolerances for 
corrosion or thread damage on the threaded portion of a weight or lever 
and proposed to require that a part with corrosion or mechanical damage 
in excess of allowable tolerances be replaced with an airworthy part. 
The proposed requirements were intended to detect corrosion and thread 
damage in the threaded area of a weight or lever, to prevent failure of 
a weight or lever, separation of tail rotor parts, severe vibration, 
and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2008-0206, dated November 25, 2008, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, and AD No. CF-2009-12, dated March 24, 2009, issued 
by the TCCA, which is the aviation authority for Canada. EASA issued AD 
No. 2008-0206 to correct the unsafe condition for ECD Model BO 105 A, 
BO 105 C, BO 105 LS A-1, BO 105 D, BO 105 DS, BO 105 DB, BO 105 DBS, BO 
105 DB-4, BO 105 DBS-4, BO 105 DBS-5, BO 105 S, 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, and MBB-BK 117 
C-1 helicopters. The TCCA issued AD No. CF-2009-12 to correct the 
unsafe condition for Eurocopter Model BO 105 LS A-3 helicopters. These 
ADs state that during a periodical inspection, corrosion was detected 
on the weights in the area of the attachment thread. Since the issuance 
of the Canadian AD, the type certificate for the Model BO 105 LS A-3 
has been transferred from Eurocopter Canada Limited to Eurocopter 
Deutschland (Germany).

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (77 FR 52265, 
August 29, 2012).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Germany and are approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to

[[Page 52411]]

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, except we are updating some of the contact 
information to obtain service information from American Eurocopter 
Corporation and we are incorporating the two figures by reference 
instead of including them in our AD to meet current publication 
requirements. These minor changes are consistent with the intent of the 
proposals in the NPRM (77 FR 52265, August 29, 2012) and will not 
increase the economic burden on any operator nor increase the scope of 
this AD.

Differences Between This AD and the EASA and TCCA ADs

    This AD does not provide an extra 60 flight hours or 6 months 
beyond the repetitive compliance time of 600 flight hours or 48 months 
for the repetitive inspections. This AD only applies to those model 
helicopters type-certificated in the United States.

Related Service Information

    Eurocopter issued Alert Service Bulletin (ASB) No. ASB-MBB-BK117-
30-113, dated September 23, 2008, for all MBB BK117 model ``A-1 to C-
1'' helicopters; ASB No. ASB BO105-30-116, dated September 23, 2008, 
for all Model BO105 helicopters ``including BO105 CB-3 and BO105 CBS-5 
KLH;'' and Eurocopter Canada Limited issued ASB No. ASB BO 105 LS 30-
12, dated December 12, 2008, for Model BO 105 LS A-3 helicopters. These 
ASBs specify visually inspecting the weights and levers to detect 
corrosion or mechanical damage; corrosion at an advanced stage could 
destroy the threads. These ASBs also specify replacing damaged weights 
and levers that exceed certain limits. The actions described in the 
mandatory EASA and TCCA ADs are intended to correct the unsafe 
condition, identified in these ASBs, to ensure the continued 
airworthiness of these helicopters.

Costs of Compliance

    We estimate that this AD will affect 33 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. It will take approximately 4 work-hours 
per helicopter to remove, inspect, and install 2 lever assemblies and 4 
weights per helicopter at an average labor rate of $85 per work-hour. 
Based on these figures, we estimate the inspection cost of this AD will 
cost $340 per helicopter or $11,220 on U.S. operators per inspection 
cycle. The required parts will cost about $5,332 per helicopter. We 
estimate the cost for replacement will be $5,672 per helicopter, 
assuming both lever assemblies and all 4 weights are replaced.

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 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) 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):

2013-16-13 Eurocopter Deutschland GmbH (ECD): Amendment 39-17551; 
Docket No. FAA-2012-0887; Directorate Identifier 2009-SW-02-AD.

(a) Applicability

    This AD applies to Model BO-105A, BO-105C, BO-105S, and BO-105LS 
A-1 helicopters, with a tail rotor control lever (lever), part 
number (P/N) 105-317231, 105-317365, 105-31736, 105-31767, 105-
31728, or 1121-31730, with tail rotor balance weight (weight) P/N 
117-31715.01, 117-31715.02, 105-31728.03, 105-31732.07, or 105-
31732.08; Model BO-105LS A-3 helicopters, with lever P/N 105-31736 
or 105-31767, with weight P/N 117-31715.01, 117-31715.02, B642M1011 
201, or 105-317171.10; and Model MBB-BK 117 A-1, MBB-BK 117 A-3, 
MBB-BK 117 A-4, MBB-BK117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 
helicopters, with lever P/N 117-31730, 117-317361, or 105-31736, 
with weight P/N 117-31714.07, 117-31715.01, 117-31720.01, or 117-
31730.02, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as corrosion or thread 
damage in the threaded area of a lever or weight. This condition 
could result in failure of a weight or lever, separation of a tail 
rotor part, severe tail rotor vibration, and subsequent loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective September 27, 2013.

(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

    Within 100 hours time-in-service (TIS) or 2 months, whichever 
occurs first, and thereafter at intervals not to exceed 600 hours 
TIS or 48 months, whichever occurs first:
    (1) Remove the weights from the lever as depicted in Figure 1 of 
Eurocopter Alert Service Bulletin (ASB) No. ASB-MBB-BK117-30-113, 
dated September 23, 2008; ASB No. ASB BO105-30-116, dated September 
23, 2008; or ASB No. ASB BO 105 LS 30-12, dated December 12, 2008; 
as applicable to your model helicopter. Apply marks to the weights 
before they are removed in order to be able to re-establish the 
correct assignment and the old installation position towards the 
lever when the weights are installed.

[[Page 52412]]

    (2) Visually inspect each weight and lever for corrosion and 
damage in the threaded areas as depicted in Figure 2 of ASB No. ASB-
MBB-BK117-30-113, dated September 23, 2008; ASB No. ASB BO105-30-
116, dated September 23, 2008; or ASB No. ASB BO 105 LS 30-12, dated 
December 12, 2008; as applicable to your model helicopter.
    (i) If there is no corrosion or thread damage on either the 
weight or lever, before further flight, reinstall the weight by 
following paragraph (e)(3) of this AD.
    (ii) If there is corrosion or thread damage on the threaded 
portion of a weight:
    (A) If the total area of corrosion or thread damage, or both, 
covers less than 25 percent of the length of the threaded area, the 
weight can be threaded (screwed) onto the lever, and the cylindrical 
mating surface has no damage, before further flight, remove the 
corrosion and reinstall the weight by following paragraph (e)(3) of 
this AD.
    (B) If the total area of corrosion or thread damage, or both, 
covers 25 percent or more of the length of the threaded area, the 
weight cannot be threaded (screwed) onto the lever, or the 
cylindrical mating surface has damage, before further flight, 
replace the weight with an airworthy weight by following paragraph 
(e)(3) of this AD.
    (iii) If there is corrosion or thread damage on the threaded 
portion of the lever, polish out the corrosion and thread damage 
using a polishing cloth 600 and:
    (A) If the thread depth does not exceed 0.3 millimeter (mm) and 
the diameter of the lever in the area before the threaded area is 
not less than 9.95 mm after polish out, before further flight, 
install airworthy weights to the lever by following paragraph (e)(3) 
of this AD.
    (B) If the thread depth is 0.3 mm or greater or the diameter of 
the lever in the area before the threaded area is less than 9.95 mm 
after polish out, before further flight, replace the lever with an 
airworthy lever.
    (3) Apply corrosion preventive paste onto the thread of the 
lever and install weights to the lever as depicted in Figure 1 of 
ASB No. ASB-MBB-BK117-30-113, dated September 23, 2008; ASB No. ASB 
BO105-30-116, dated September 23, 2008; or ASB No. ASB BO 105 LS 30-
12, dated December 12, 2008; as applicable to your model helicopter. 
Ensure during installation of the weights that the weights are 
correctly assigned and installed to the control lever in accordance 
with the applied marks.

(f) 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 sharon.y.miles@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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2008-0206, dated November 25, 2008, and in 
Transport Canada Civil Aviation (TCCA) AD No. CF-2009-12, dated 
March 24, 2009. You may view the EASA and the TCCA AD on the 
Internet at http://www.regulations.gov in Docket No. FAA-2012-0887.

(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) Eurocopter Alert Service Bulletin (ASB) No. ASB-MBB-BK117-
30-113, dated September 23, 2008.
    (ii) Eurocopter ASB No. ASB BO105-30-116, dated September 23, 
2008.
    (iii) Eurocopter ASB No. ASB BO 105 LS 30-12, dated December 12, 
2008.
    (3) For Eurocopter service information identified in this AD, 
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand 
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax 
(972) 641-3775; or at http://www.eurocopter.com/techpub.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, TX 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference 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/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on August 2, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-19442 Filed 8-22-13; 8:45 am]
BILLING CODE 4910-13-P
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