80 FR 16603 - Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 60 (March 30, 2015)

We propose to supersede airworthiness directive (AD) 2014-05- 06 for certain Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters to correct an error. AD 2014-05-06 currently requires inspecting the flight-control bearings repetitively, replacing any loose bearing with an airworthy flight-control bearing, and installing bushings and washers. This proposed AD would require the same actions. This proposed AD results from the discovery of an error in the compliance time for AD 2014-05-06. These proposed actions are intended to prevent the affected control lever from shifting, contacting the helicopter structure, and reducing control of the helicopter.

[Federal Register Volume 80, Number 60 (Monday, March 30, 2015)]
[Proposed Rules]
[Pages 16603-16606]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-06806]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0674; Directorate Identifier 2014-SW-019-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(Previously Eurocopter Deutschland GmbH) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2014-05-
06 for certain Eurocopter Deutschland GmbH (ECD) (now Airbus 
Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 
helicopters to correct an error. AD 2014-05-06 currently requires 
inspecting the flight-control bearings repetitively, replacing any 
loose bearing with an airworthy flight-control bearing, and installing 
bushings and washers. This proposed AD would require the same actions. 
This proposed AD results from the discovery of an error in the 
compliance time for AD 2014-05-06. These proposed actions are intended 
to prevent the affected control lever from shifting, contacting the 
helicopter structure, and reducing control of the helicopter.

DATES: We must receive comments on this proposed AD by May 29, 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 proposed AD, the European 
Aviation Safety Agency

[[Page 16604]]

(EASA) 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 
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 service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is 
also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0674.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
[email protected].

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

    On February 20, 2014, we issued AD 2014-05-06, Amendment 39-17779 
(79 FR 13196, March 10, 2014), for certain ECD (now Airbus Helicopters 
Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters. AD 2014-
05-06 requires inspecting the flight-control bearings repetitively, 
replacing any loose bearing with an airworthy flight-control bearing, 
and installing bushings and washers. AD 2014-05-06 was prompted by the 
discovery of loose flight control bearings because of incorrect 
installation. This condition, if not corrected, could result in the 
affected control lever shifting, contacting the helicopter structure, 
and reducing control of the helicopter.

Actions Since AD 2014-05-06 Was Issued

    Since we issued AD 2014-05-06 (79 FR 13196, March 10, 2014), we 
discovered an error regarding the compliance time for certain model 
helicopters. Paragraph (e)(1)(i) should have required that certain 
actions be accomplished within the next 100 hours time-in-service or at 
the next annual inspection, whichever occurs first. However, we omitted 
the word ``first'' from that sentence, which changes the meaning of the 
required compliance time.
    Also since we issued AD 2014-05-06, ECD changed its name to Airbus 
Helicopters Deutschland GmbH. This proposed AD reflects that change and 
updates the contact information to obtain service documentation.

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 Under 1 CFR Part 51

    ECD, now called Airbus Helicopters, has issued Alert Service 
Bulletin (ASB) MBB BK117 C-2-67A-010, Revision 3, dated February 8, 
2010, and ASB EC135-67A-019, Revision 3, dated December 16, 2009. These 
ASBs specify:
     Within the next 50 flight hours (FHs), inspecting the 
affected bearings and, if necessary, rebonding any affected bearings or 
replacing the lever assembly.
     Within 12 months, retrofitting bushings and washers on the 
levers to prevent movement of the bearings.
     After the retrofit, repeating the inspection every 800 FHs 
or 36 months for the Model EC135 helicopters, whichever comes first, 
and 600 FHs or 24 months, whichever comes first, for the Model MBB-BK 
117 C-2 helicopters.
    EASA classified these ASBs as mandatory and issued AD No. 2010-0058 
to ensure the continued airworthiness of these helicopters. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this NPRM.

Proposed AD Requirements

    For Airbus Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters 
this proposed AD would require:
     Within the next 100 hours time-in-service (TIS) or at the 
next annual inspection, whichever occurs first, modifying the left-hand 
(LH) and right-hand (RH) guidance units and the cyclic shaft by 
installing bushings and washers to prevent shifting of the bearings in 
the axial direction.
     At intervals not to exceed 800 hours TIS or 36 months, 
whichever occurs first, inspecting the bearings in the LH guidance 
unit, RH guidance unit, cyclic control, upper guidance unit, and linear 
voltage differential transducer plate for play. If any bearing is 
loose, replacing the affected bearing with an airworthy bearing.
    For Model MBB-BK 117 C-2 helicopters, this proposed AD would 
require:
     Within the next 100 hours TIS or at the next annual 
inspection, whichever occurs first, modifying the LH and RH guidance 
units and the lateral control lever by installing bushings and washers 
to prevent shifting of the bearings in the axial direction.
     At intervals not to exceed 600 hours TIS or 24 months, 
whichever occurs first, inspecting the bearings in the RH guidance 
unit, LH guidance unit, and lateral control guidance unit for play. If 
any bearing is loose, replacing the affected bearing with an airworthy 
bearing.

Differences Between This Proposed AD and the EASA AD

    Differences between this proposed AD and the EASA AD are:
     The EASA AD is applicable to the EC 635 helicopter, 
whereas this proposed AD is not because the EC 635 helicopter is not 
type certificated in the U.S.
     The EASA AD requires an initial inspection within 50 
flight hours or one

[[Page 16605]]

month, whichever occurs first after May 31, 2008, and a modification 
within the next 12 months. This proposed AD would require the 
modification within 100 hours TIS or at the next annual inspection, 
whichever occurs first, and no inspection until after the modification 
has been accomplished.
     The EASA AD applies to all EC135 and MBB-BK 117 C-2 
helicopters, while this proposed AD would apply to certain serial-
numbered Model EC135 and Model MBB-BK 117 C-2 helicopters, as 
recommended by the appropriate ECD ASB.

Costs of Compliance

    We estimate that this proposed AD would affect 175 Model EC135 and 
112 Model MBB-BK 117 C-2 helicopters of U.S. Registry and that labor 
costs would average $85 per work-hour. Based on these estimates, we 
expect the following costs:
     For EC135 helicopters, it would take about 32 work-hours 
to perform the modification. Parts would cost about $312. The total 
cost for the modification would be about $3,032 per helicopter and 
$530,600 for the U.S. operator fleet. The repetitive inspections would 
require 6.5 work-hours for a cost of about $553 per helicopter and 
about $96,775 for the fleet per inspection cycle.
     For MBB-BK 117 C-2 helicopters, it would take about 32 
work-hours to perform the modification. Parts would cost about $396. 
The total cost for the modification would be $3,116 per helicopter and 
$348,992 for the U.S. operator fleet. The cost for the repetitive 
inspections thereafter would be about $85 per helicopter and $9,520 for 
the fleet per inspection cycle.

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

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 removing Airworthiness Directive (AD) 
2014-05-06, Amendment 39-17779 (79 FR 13196, March 10, 2014), and 
adding the following new AD:

Airbus Helicopters Deutschland GmbH (Previously Eurocopter 
Deutschland GmbH): Docket No. FAA-2015-0674; Directorate Identifier 
2014-SW-019-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, serial 
number (S/N) 0005 through 00829, with a tail rotor control lever, 
part number (P/N) L672M2802205 or L672M1012212; cyclic control 
lever, P/N L671M1005250; collective control lever assembly, P/N 
L671M2020108; or collective control plate, P/N L671M5040207; 
installed; and
    (2) Model MBB-BK 117 C-2 helicopters, S/N 9004 through 9310, 
with a tail rotor control lever assembly, P/N B672M1007101 or 
B672M1807101; tail rotor control lever, P/N B672M1002202 or 
L672M2802205; or lateral control lever assembly, P/N B670M1008101, 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as incorrectly installed 
flight control bearings. This condition could cause the affected 
control lever to shift and contact the helicopter structure, 
resulting in reduced control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2014-05-06, Amendment 39-17779 (79 FR 
13196, March 10, 2014).

(d) Comments Due Date

    We must receive comments by May 29, 2015.

(e) 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.

(f) Required Actions

    (1) For Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters:
    (i) Within the next 100 hours time-inservice (TIS) or at the 
next annual inspection, whichever occurs first, modify the left-hand 
(LH) and right-hand (RH) guidance units and the cyclic shaft by 
installing bushings and washers to prevent shifting of the bearings 
in the axial direction as follows:
    (A) Remove and disassemble the LH guidance unit and install a 
bushing, P/N L672M1012260, between the bearing block and the lever 
of the LH guidance unit as depicted in Detail A of Figure 5 of 
Eurocopter Alert Service Bulletin EC135-67A-019, Revision 3, dated 
December 16, 2009 (EC135 ASB).
    (B) For helicopters without a yaw brake, remove and disassemble 
the RH guidance unit and install a bushing, P/N L672M1012260, 
between the bearing block and the lever as depicted in Detail B of 
Figure 5 of EC135 ASB.
    (C) Remove and disassemble the cyclic shaft and install a 
washer, P/N L671M1005260, between the bearing block and the lever as 
depicted in Detail C of Figure 6 of EC135 ASB.
    (D) Remove the collective control rod from the bellcrank and 
install a washer, P/N L221M1042208, on each side of the collective 
control rod and bellcrank as depicted in Detail D of Figure 6 of 
EC135 ASB.
    (E) At intervals not to exceed 800 hours TIS or 36 months, 
whichever occurs first, inspect the bearings in the LH guidance 
unit, RH guidance unit, cyclic control, upper guidance unit, and 
linear voltage differential transducer plate for play. If any 
bearing is

[[Page 16606]]

loose, replace the affected bearing with an airworthy bearing.
    (2) For Model MBB-BK 117 C-2 helicopters:
    (i) Within the next 100 hours TIS or at the next annual 
inspection, whichever occurs first, modify the LH and RH guidance 
units and the lateral control lever by installing bushings and 
washers to prevent shifting of the bearings in the axial direction 
as follows:
    (A) Remove and disassemble the RH guidance unit and install a 
bushing, P/N L672M1012260, between the lever and the bracket as 
depicted in Detail B of Figure 4 of Eurocopter Alert Service 
Bulletin MBB BK117 C-2-67A-010, Revision 3, dated February 8, 2010 
(BK117 ASB). Remove and disassemble the LH guidance unit and install 
a bushing, P/N L672M1012260, between the lever and the bracket as 
depicted in Detail C of Figure 4 of BK117 ASB.
    (B) Remove the lateral control lever and install new bushings in 
accordance with the Accomplishment Instructions, paragraphs 
3.C(9)(a) through 3.C(9)(g), of BK 117 ASB.
    (C) Identify the modified lever assembly by writing ``MBB BK117 
C-2-67A-010'' on the lever with permanent marking pen and protect 
with a single layer of lacquer (CM 421 or equivalent).
    (D) Apply corrosion preventive paste (CM 518 or equivalent) on 
the shank of the screws and install airworthy parts as depicted in 
Figure 5 of BK117 ASB.
    (E) At intervals not to exceed 600 hours TIS or 24 months, 
whichever occurs first, inspect the bearings in the RH guidance 
unit, LH guidance unit, and lateral control guidance unit for play. 
If any bearing is loose, replace the affected bearing with an 
airworthy bearing.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management Group, Rotorcraft Directorate, 
FAA, 2601 Meacham Blvd., Fort Worth, Texas 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) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2010-0058, dated March 30, 2010. You may view 
the EASA AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2015-0674.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor 
Control.

    Issued in Fort Worth, Texas, on March 18, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-06806 Filed 3-27-15; 8:45 am]
 BILLING CODE 4910-13-P