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[Federal Register Volume 77, Number 168 (Wednesday, August 29, 2012)]
[Proposed Rules]
[Pages 52265-52270]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-21284]

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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]
RIN 2120-AA64

Airworthiness Directives; Eurocopter Deutschland GmbH Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 52266]]

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt 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 
proposed AD is 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 proposed actions 
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: We must receive comments on this proposed AD by October 29, 
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 proposed 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 proposed AD, contact 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005; telephone (972) 641-3460; fax (972) 641-3527; or at http://www.eurocopter.com. 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.

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: 

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA has issued EASA AD No. 2008-0206, dated November 25, 2008, to 
correct the unsafe condition for the 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, all serial numbers. The TCCA has issued Canadian AD No. 
CF-2009-12, dated March 24, 2009, to correct the unsafe condition for 
the 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).
    The proposed actions are 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. You may obtain 
further information by examining the EASA and TCCA ADs and any related 
service information in the AD docket.

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 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    Eurocopter has issued Alert Service Bulletin (ASB) No. ASB-MBB-BK 
117-30-113, dated September 23, 2008, for all MBB BK 117 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 has 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.

Proposed AD Requirements

    This proposed AD would require compliance with specified portions 
of the manufacturer's service bulletin in conducting repetitive visual 
inspections of each weight and lever and would provide procedures for 
installing a weight or lever. Additionally, it proposes allowable 
tolerances for corrosion or thread damage on the threaded portion of a 
weight or lever and would require that a part with

[[Page 52267]]

corrosion or mechanical damage in excess of allowable tolerances be 
replaced with an airworthy part.

Differences Between This Proposed AD and the EASA and TCCA ADs

    This proposed 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. These proposals only apply to 
those model helicopters type-certificated in the United States.

Costs of Compliance

    We estimate that this proposed AD would affect about 33 helicopters 
of U.S. Registry. We estimate that operators may incur the following 
costs in order to comply with this AD. It would 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 proposed AD would be $340 per helicopter or $11,220 on U.S. 
operators per inspection cycle. The required parts would cost about 
$5,332 per helicopter. We estimate the cost for replacement would 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 products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

EUROCOPTER DEUTSCHLAND GmbH (ECD): 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) 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.

(d) 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 to 
paragraph (d) of this AD. 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.
BILLING CODE 4910-13-P

[[Page 52268]]

[GRAPHIC] [TIFF OMITTED] TP29AU12.026

    (2) Visually inspect each weight and lever for corrosion and 
damage in the threaded areas as depicted in Figure 2 to paragraph 
(d) of this AD.

[[Page 52269]]

[GRAPHIC] [TIFF OMITTED] TP29AU12.027

BILLING CODE 4910-13-C

    (i) If there is no corrosion or thread damage on either the 
weight or lever, before further flight, reinstall the weight by 
following paragraph (d)(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 (d)(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 
(d)(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 (d)(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

[[Page 52270]]

the lever as depicted in Figure 1 to paragraph (d) of this AD. 
Ensure during installation of the weights that the weights are 
correctly assigned and installed to the control lever in accordance 
with the applied marks.

(e) Alternative Methods of Compliance (AMOC)

    (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.

(f) Additional Information

    The subject of this AD is addressed in the European Aviation 
Safety Agency (Germany) AD No. 2008-0206, dated November 25, 2008, 
and in the Transport Canada Civil Aviation AD No. CF-2009-12, dated 
March 24, 2009.

 (g) Subject

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

    Issued in Fort Worth, Texas, on August 16, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-21284 Filed 8-28-12; 8:45 am]
BILLING CODE 4910-13-P
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