### 49442 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations

(i) Embraer S.A. Phenom Alert Service Bulletin No. 500–55–A004, Revision 02, dated July 25, 2014

(ii) Reserved. (3) For Embraer S.A. service information identified in this AD, contact: EMBRAER S.A., Phenom Maintenance Support, Avenida Brigadeiro Faria Lima, 2170, Putim, CEP: 12227–901, Sao Jose dos Campos, Sao Paulo, Brasil; phone: (+55 12) 3927–1000; Fax: (+55 12) 3927–6600, Ext. 1448; email: phenom.reliability@embraer.com.br: Internet:http://www.embraerexecutivejets.com/enUS/customer-support/Pages/Service-CenterNetwork.aspxt.

(4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

(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/ibrlocations.html

Issued in Kansas City, Missouri, on August
11, 2014. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–19365 Filed 8–20–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0251; Directorate Identifier 2013–NM–179–AD; Amendment**  **39–17946; AD 2014–16–22]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200 Freighter, A330–200, A330–300, and A340–200, A340–300, A340–500, and A340–600 series airplanes. This AD was prompted by a determination that the service life limits of the cabin pressure control system (CPCS) safety valves installed on the aft pressure bulkhead were being exceeded. This AD requires repetitive replacement of the CPCS safety valves with serviceable valves. We are issuing this AD to prevent exceeding the service life limits of the CPCS safety valves, which, in the event of a failure, could result in excessive positive or negative differential pressure in the fuselage and consequent incapacitation or injuries to airplane occupants.

**DATES :**  This AD becomes effective September 25, 2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 25, 2014.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0251; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

**FOR FURTHER INFORMATION CONTACT :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330–200 Freighter, A330–200, A330–300, and A340–200, A340–300, A340–500, and A340–600 series airplanes. The NPRM published in the Federal Register on May 15, 2014 (79 FR 27814).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0201, dated September 4, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information to correct an unsafe condition on all Airbus Model A330–200 Freighter, A330–200, A330– 300, and A340–200, –300, –500, and –600 series airplanes. The MCAI states:

Investigation results on the Cabin Pressure Control System (CPCS) safety valve demonstrate that this part is subject to repetitive restoration every 50,000 flight hours (FH) or 12 years, but this airworthiness instruction is not yet reflected in the instructions for continuing airworthiness. Moreover, this safety valve, part of the CPCS, is not failure monitored.

In order to maintain the required safety objectives, the CPCS safety valves must be replaced by a serviceable part no later than the above values.

For the reasons describe above, this [EASA] AD requires repetitive replacement of CPCS safety valves.

Exceeding the service life limits of the CPCS safety valve, in the event of a failure, could result in excessive positive or negative differential pressure in the fuselage, and consequent incapacitation or injuries to airplane occupants.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0251-

0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 27814, May 15, 2014) or on the determination of the cost to the public.
‘‘Contacting the Manufacturer’’ Paragraph in This AD

Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD.

The MCAI or referenced service information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved.

In the NPRM (79 FR 11016, February 27, 2014), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority


### 49443 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations

design organization approval (DOA), as applicable, to refer to a DAH authorized to approve required repairs for the proposed AD.

No comments were provided to the NPRM (79 FR 11016, February 27, 2014) about these proposed changes. However, a comment was provided for an NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013). The commenter stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an AD mandated Airbus service bulletin.’’

This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19.

To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (DOA).

The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the documentare EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information.

This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance.

Other commenters to the NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013) pointed out that in many cases the foreign manufacturer’s service bulletin and the foreign authority’s MCAI might have been issued some time before the FAA AD. Therefore, the DOA might have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition, before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit.

Based on these comments, weremoved the requirement that the DAHprovided repair specifically refer to this AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the unsafe condition addressed in this AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 27814, May 15, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 27814, May 15, 2014).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.
Costs of Compliance

We estimate that this AD affects 77 airplanes of U.S. registry.

We also estimate that it takes about 25 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $9,784 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $916,993, or $11,909 per product, per replacement 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 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 the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska; 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.


### 49444 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations

Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0251; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section.
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** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

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

2014–16–22 Airbus: Amendment 39–17946. Docket No. FAA–2014–0251; Directorate Identifier 2013–NM–179–AD.

(a) Effective Date

This AD becomes effective September 25,

2014.

(b) Affected ADs

None.
(c) Applicability

This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F,
–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; Model A340–211, –212, –213, –311, –312, and –313 airplanes; and Model A340–541 and –642 airplanes; certificated in any category; all manufacturer serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 21, Air Conditioning.

(e) Reason

This AD was prompted by a determination that the service life limits of the cabin pressure control system (CPCS) safety valves installed on the aft pressure bulkhead were being exceeded. We are issuing this AD to prevent exceeding the service life limits of the CPCS safety valve, which, in the event of a failure, could result in excessive positive or negative differential pressure in the fuselage, and consequent incapacitation or injuries to airplane occupants.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) Replacement of CPCS Safety Valves

(1) For airplanes on which the total number of flight hours accumulated on the CPCS safety valves are known: Replace the CPCS safety valve with a serviceable valve at the later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. Replace the valve in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD. Repeat the replacement at intervals not to exceed 50,000 flight hours or 12 years accumulated on the CPCS safety valve, whichever occurs first.

(i) Before the safety valve accumulates 50,000 total flight hours or 12 years since first installation or since the last restoration, as applicable, whichever occurs first.

(ii) Within 26 months after the effective date of this AD.

(2) For airplanes on which the total number of flight hours accumulated on the CPCS safety valve are unknown: Replace the CPCS safety valve with a serviceable valve within 26 months after the effective date of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD. Repeat the replacement at intervals not to exceed 50,000 flight hours or 12 years accumulated on the CPCS safety valve, whichever occurs first.

(3) Use the applicable service information identified in paragraph (g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD to accomplish the specified actions in paragraph (g) of this AD.

(i) Airbus Service Bulletin A330–21–3154, Revision 01, dated April 10, 2013 (for Model A330–200 Freighter, A330–200 and A330– 300 series airplanes).

(ii) Airbus Service Bulletin A340–21–4150, Revision 01, dated April 10, 2013 (for Model A340–200 and A340–300 series airplanes).

(iii) Airbus Service Bulletin A340–21– 5044, Revision 01, dated April 10, 2013 (for Model A340–500 and A340–600 series airplanes).

(h) Definition of Serviceable Valves

For the purposes of this AD, a serviceable CPCS safety valve is a safety valve which has not exceeded the following service life limits, as applicable: 12 years since its manufacturing date, or 50,000 total flight hours since first installation on an airplane, whichever occurs first; or 12 years since its last restoration, or 50,000 total flight hours since its last restoration, whichever occurs first.

(i) Optional Method of Compliance

Accomplishment of Task 21.31.00/09, Remove Safety Valve for Restoration, of Section C–21, Air Conditioning, of Section C, Systems and Power-plant Section, of the Airbus A330 Maintenance Review Board Report, Revision 14, dated June 2013; or
Airbus A340 Maintenance Review Board Report, Revision 14, dated June 2013; as applicable; constitutes compliance with any replacement required by paragraph (g) of this

AD.

(j) Credit for Previous Actions

This paragraph provides credit for actions required by paragraphs (g)(1) and (g)(2) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, which are not incorporated by reference in this AD.

(1) Airbus Service Bulletin A330–21–3154, dated November 17, 2011.

(2) Airbus Service Bulletin A340–21–4150, dated November 17, 2011.

(3) Airbus Service Bulletin A340–21–5044, dated November 17, 2011.

(k) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0201, dated September 4, 2013, for related information. This MCAI may be found in the AD docket on the

Internet at http://www.regulations.gov/# !documentDetail;D=FAA-2014-0251-0002.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD.


### 49445 Federal Register / Vol. 79, No. 162 / Thursday, August 21, 2014 / Rules and Regulations

(m) 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 this AD specifies otherwise.

(i) Airbus Service Bulletin A330–21–3154, Revision 01, dated April 10, 2013.

(ii) Airbus Service Bulletin A340–21–4150, Revision 01, dated April 10, 2013.

(iii) Airbus Service Bulletin A340–21– 5044, Revision 01, dated April 10, 2013.

(iv) Task 21.31.00/09, Remove Safety Valve for Restoration, of Section C–21, Air Conditioning, of Section C, Systems and Power-plant Section, of the Airbus A330 Maintenance Review Board Report, Revision 14, dated June 2013.

(v) Task 21.31.00/09, Remove Safety Valve for Restoration, of Section C–21, Air Conditioning, of Section C, Systems and Power-plant Section, Airbus A340 Maintenance Review Board Report, Revision 14, dated June 2013.

(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;

Internet http://www.airbus.com.

(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(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/ibrlocations.html.

Issued in Renton, Washington, on August

7, 2014. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–19555 Filed 8–20–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0034; Directorate Identifier 2013–SW–006–AD; Amendment**  **39–17948; AD 2014–16–24]**

**RIN 2120–AA64**

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

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2012–10– 53 for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2012–10–53 required, before further flight and at specified intervals, checking and inspecting the upper and lower main rotor hub (MRH) shaft flanges for a crack, and inspecting the lower hub-shaft flange bolt attachment areas for a crack. Since we issued AD 2012–10–53, it has been determined that it is safe to increase the visual inspection intervals of the MRHshaft flanges from 10 hours time-inservice (TIS) to 50 hours TIS and remove the inspection of the lower MRH shaft flange bolt attachment areas. This new AD continues to require checking and inspecting the upper and lower MRH shaft flanges for a crack. These actions are intended to detect a crack on the MRH shaft flange, which if not corrected, could result in failure of the MRH and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective September
25, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 25, 2014.

**ADDRESSES :**  For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0034; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference information, the economic evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On May 18, 2012, we issued Emergency AD 2012–10–53, which superseded Emergency AD 2012–10–51. Emergency AD 2012–10–53 was published in the Federal Register as a Final rule; request for comments on November 20, 2012, at 77 FR 69558. AD 2012–10–53 required a repetitive pilot check of the lower MRH shaft flange for a crack, a repetitive inspection of the upper and lower MRH shaft flanges and bolt attachment areas for a crack, and replacing the MRH shaft if there is a crack. AD 2012–10–53 was prompted by three reported incidents of cracking on the lower hub-shaft flanges of EC135 model helicopters.

After we issued AD 2012–10–53, Eurocopter revised Alert Service Bulletin (ASB) No. EC135–62A–029, now at Revision 7, dated October 22, 2012, which contains the procedures for the repetitive pilot checks and inspections. The inspection interval for the visual inspection of the MRH shaft flanges was increased to 50 flight hours based on results from full scale component testing. The note regarding the preflight check states that the time between two preflight checks must not exceed 6 flight hours, and clarifies that one flight may comprise of multiple take-offs and landings and a flight starts when the helicopter takes off and ends when the helicopter is on the ground with the engines shut off. Eurocopter also removed the visual inspection of