AD 2017-03-01

We are superseding airworthiness directive (AD) 2014-05-06 for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters to correct an error in the compliance time. AD 2014-05-06 required inspecting the flight- control bearings and installing bushings and washers. This AD requires the same actions. These actions are intended to prevent an unsafe condition on these products.

Final rule.

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:

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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:

2017-03-01 Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH): Amendment 39-18792; 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) Effective Date

This AD becomes effective March 31, 2017.

(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-in-service (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 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 421or 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, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222- 5110; email 9-ASW-FTW-AMOC-Requests@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.

(h) Additional InformationThe 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.

(j) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise.
(3) The Director of the Federal Register previously approved the incorporation by reference of the service information listed in this paragraph on April 14, 2014 (79 FR 13196, March 10, 2014).
(i) Eurocopter Alert Service Bulletin EC135-67A-019, Revision 3, dated December 16, 2009.
(ii) Eurocopter Alert Service Bulletin MBBBK117 C-2-67A-010, Revision 3, dated February 8, 2010.
(4) For service information identified in this final rule, 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.
(5) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110.
(6) 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.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2014-05-06, Amendment 39-17779 (79 FR 13196, March 10, 2014) and add a new AD. AD 2014-05-06 required inspecting the flight control bearings repetitively, replacing any loose bearing with an airworthy flight control bearing, and installing bushings and washers. The NPRM published in the Federal Register on March 30, 2015 (80 FR 16603). The NPRM proposed to retain all of the required actions and correct an error in the compliance time. AD 2014-05-06 should have required installing the bushings and washers on Model EC135 helicopters 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.
AD 2014-05-06 was prompted by the discovery of loose flight control bearings because of incorrect installation. This condition could result in the affected control lever shifting, contacting the helicopter structure. The actions in AD 2014-05-06 were intended to prevent this unsafe condition, which could reduce control of the helicopter.
Also since we issued AD 2014-05-06, ECD changed its name to Airbus Helicopters Deutschland GmbH (Airbus Helicopters). This AD reflects that change and updates the contact information to obtain service documentation.

Comments

After our NPRM (80 FR 16603, March 30, 2015) was published, we received comments from one commenter.

Request

Airbus Helicopters first requested revising the compliance times for the repetitive inspections to match that in its current service information. For the Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters, Airbus Helicopters requested increasing the 800 hour interval to 1000 hours with an additional 10% margin. For MBB-BK 117 C- 2 helicopters, Airbus Helicopters requested increasing the 600 hour interval to 800 hours with an additional 10% margin.
We disagree. Airbus Helicopters did not provide any technical justification to support this request. The final rule has not been changed as a result of this comment.
Airbus Helicopters also requested that if any bearing is loose, we require

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replacing the lever or rebonding the affected bearing in accordance with its maintenance instructions.
We agree with the comment but disagree that a change to the AD is necessary. If there is a loose bearing, the AD requires replacing it with an airworthy part. If a bearing can be re-bonded in a manner acceptable to the FAA, then it would be an airworthy part.

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, reviewed the relevant information, considered the comments received, and determined the unsafe condition exists and is likely to 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 with the changes described previously. These changes are consistent with the intent of the proposals in the NPRM (80 FR 16603, March 30, 2015), and will not increase the economic burden on any operator nor increase the scope of this AD.

Differences Between This AD and the EASA AD

Differences between this AD and the EASA AD are:
The EASA AD is applicable to the EC 635 helicopter, whereas this 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 month, whichever occurs first after May 31, 2008, and a modification within the next 12 months. This AD requires 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 specifies repetitive inspection intervals not to exceed 800 hours TIS or 12 months, plus a 10% percent margin, whichever occurs first, for Model EC135 helicopters and 600 hours TIS or 12 months, plus a 10% percent margin, whichever occurs first, for the Model MBB-BK 117 C-2 helicopters. This AD requires repetitive inspection intervals not to exceed 800 hours TIS or 36 months, whichever occurs first, for Model EC135 helicopters and 600 hours TIS or 24 months, whichever occurs first, for Model MBB-BK 117 C-2 helicopters.
The EASA AD applies to all Model EC135 and Model MBB-BK 117 C-2 helicopters, while this AD applies to certain serial-numbered Model EC135 and Model MBB-BK 117 C-2 helicopters, as recommended by the appropriate ECD ASB.

Related Service Information Under 1CFR Part 51

Eurocopter (now Airbus Helicopters) has issued Alert Service Bulletin (ASB) MBB BK117 C-2-67A-010, Revision 3, dated February 8, 2010 for Model MBB-BK 117 C-2 helicopters, and ASB EC135-67A-019, Revision 3, dated December 16, 2009 for Model EC135 helicopters. 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.
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.

Costs of Compliance

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

Authority for This Rulemaking

Title 49 of the United StatesCode 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 betweenthe 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.