### 55123 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations

T ABLE 

### 1—A FFECTED 

### T AY 

### 650–15 E N



### GINES BY 

### S ERIAL 

### N UMBER 

### (C ARRIED 

### F ORWARD 

### F ROM 

### AD 2008–10– 14)—Continued

Engine Serial Number

17521 17523 17539 17542 17556 17561 17562 17563 17580 17581 17612 17618 17635 17637 17645 17661 17686 17699 17701 17702 17736 17737 17738 17739 17741 17742 17808



### T ABLE 

### 2—A FFECTED 

### T AY 

### 650–15 E N



### GINES BY 

### S ERIAL 

### N UMBER 

### (A DDED 

### N EW IN 

### T HIS 

### AD)

Engine Serial Number

17249 17303 17358 17370 17425 17426 17433 17438 17445 17446 17460 17474 17478 17490 17491 17517 17518 17522 17534 17535 17536 17538 17540 17541 17552 17553 17585 17613 17723 17724 17740 17759 

### T ABLE 

### 2—A FFECTED 

### T AY 

### 650–15 E N



### GINES BY 

### S ERIAL 

### N UMBER 

### (A DDED 

### N EW IN 

### T HIS 

### AD)—Continued

Engine Serial Number

17760 17807

Reason

(d) Strip results from some of the engines listed in the applicability section of thisdirective revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low-pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane.

We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. Actions and Compliance

(e) Unless already done, do the following actions.

(1) Prior to accumulating 11,700 flight cycles (FC) since new, and thereafter at intervals not exceeding 11,700 FC of the engine, inspect the LP turbine disks stage 2 and stage 3 for corrosion in accordance with RRD Alert Service Bulletin No. TAY–72– A1524, Revision 2, dated June 13, 2008.

(2) For engines that already exceed 11,700 FC on the effective date of this AD, perform the inspection within 90 days after the effective date of this AD.

(3) When, during any of the inspections as required by paragraph (e)(1) of this directive, corrosion is found, replace the affected parts. The RRD TAY 650 Engine Manual—E–TAY– 3RR, Tasks 72–52–23–200–000 and 72–52– 24–200–000 contains guidance on performing the inspection for corrosion and rejection criteria.

Previous Credit

(f) Initial inspections done before the effective date of this AD on LP turbine disks stage 2 and stage 3 listed in Table 1 of this AD using RRD Alert Service Bulletin No. TAY–72–A1524, Revision 1, dated September 1, 2006, comply with the initial inspection requirements specified in this AD. Alternative Methods of Compliance (AMOCs)

(g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

(h) Refer to European Aviation Safety Agency AD 2008–0122, dated July 1, 2008, for related information.

(i) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference

(j) You must use Rolls-Royce Deutschland Alert Service Bulletin No. TAY–72–A1524, Revision 2, dated June 13, 2008, to do the actions required by this AD.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33–7086–1768; fax 49 (0) 33–7086–
3356.

(3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or 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 Burlington, Massachusetts, on October 8, 2009. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–25031 Filed 10–26–09; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0996; Directorate Identifier 2009–NM–156–AD; Amendment**  **39–16061; AD 2007–21–14 R1]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A310 Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A310 airplanes. That AD currently requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. We are


### 55124 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations

issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.

**DATES :**  This AD is effective November 12, 2009.

On November 20, 2007 (72 FR 58499, October 16, 2007), the Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD.

We must receive any comments on this AD by December 11, 2009.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 Office (telephone 800–647– 5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :**  Discussion On October 5, 2007, we issued AD 2007–21–14, amendment 39–15232 (72 FR 58499, October 16, 2007). That AD applied to all Airbus Model A310 airplanes. That AD required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems.

Critical design configuration control limitations (CDCCLs) are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection.

Actions Since AD Was Issued

Since we issued that AD, we have determined that it is necessary to clarify the AD’s intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness.

Section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c) specifies the following:

No person may operate an aircraft for which a manufacturer’s maintenance manual or instructions for continued airworthiness has been issued that contains an airworthiness limitation section unless the mandatory * * * procedures * * * have been complied with. Some operators have questioned whether existing components affected by the new CDCCLs must be reworked. We did not intend for the AD to retroactively require rework of components that had been maintained using acceptable methods before the effective date of the AD. Owners and operators of the affected airplanes therefore are not required to rework affected components identified as airworthy or installed on the affected airplanes before the required revisions of the Airworthiness Limitations Section of the Instructions for Continued Airworthiness. But once the CDCCLs are incorporated into the Airworthiness Limitations Section of the Instructions for Continued Airworthiness, future maintenance actions on components must be done in accordance with those CDCCLs. FAA’s Determination and Requirements of This AD

The affected product(s) have been approved by the aviation authority of another country, and are approved for operation in the United States. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This new AD retains the requirements of the existing AD, and adds a new note to clarify the intended effect of the AD on spare and on-airplane fuel tank system components. Costs of Compliance

This revision imposes no additional economic burden. The current costs for this AD are repeated for the convenience of affected operators, as follows:

This AD affects about 69 airplanes of U.S. registry. The required actions take about 2 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $11,040, or $160 per airplane.
FAA’s Justification and Determination of the Effective Date

This revision merely clarifies the intended effect on spare and on-airplane fuel tank system components, and makes no substantive change to the AD’s requirements. For this reason, it is found that notice and opportunity for prior public comment for this action are unnecessary, and good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2009–0996; Directorate Identifier 2009– NM–156–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.


### 55125 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations

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 have 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 the 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); and

3. 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 a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the **ADDRESSES** section for a location to examine the regulatory evaluation.
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 part 39 of the Federal Aviation Regulations (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 removing amendment 39–15232 (72 FR 58499, October 16, 2007) and adding the following new AD:

2007–21–14 R1 Airbus: Amendment 39– 16061. Docket No. FAA–2009–0996; Directorate Identifier 2009–NM–156–AD.

Effective Date

(a) This airworthiness directive (AD) is effective November 12, 2009.

Affected ADs

(b) This AD revises AD 2007–21–14. Applicability

(c) This AD applies to all Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes, certificated in any category.

Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and critical design configuration control limitations (CDCCLs). Compliance with the operator maintenance documents is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections and CDCCLs, the operator may not be able to accomplish the inspections and CDCCLs described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections and CDCCLs that will preserve the critical ignition source prevention feature of the affected fuel system.

Unsafe Condition

(d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Restatement of AD 2007–21–14, With No Changes

Revise Airworthiness Limitations Section (ALS) To Incorporate Fuel Maintenance and Inspection Tasks

(f) Within 3 months after November 20, 2007 (the effective date of AD 2007–21–14), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the European Aviation Safety Agency (EASA) on July 6, 2007), Section 1, ‘‘Maintenance/ Inspection Tasks.’’ For all tasks identified in Section 1 of Document 95A.1930/05, the initial compliance times start from the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1930/05, except as provided by paragraph (g) of this AD.

(1) November 20, 2007. (2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness.

Note 2: Airbus Operator Information Telex SE 999.0079/07, Revision 01, dated August 14, 2007, identifies the applicable sections of the Airbus A310 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1930/05.
Initial Compliance Time for Task 28–18–00–
03–1

(g) For Task 28–18–00–03–1 identified in Section 1 of Document 95A.1930/05, ‘‘Maintenance/Inspection Tasks,’’ of Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007): The initial compliance time is the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. Thereafter, Task 28–18– 00–03–1 must be accomplished at the repetitive interval specified in Section 1 of Document 95A.1930/05.

(1) Prior to the accumulation of 40,000 total flight hours.

(2) Within 72 months or 20,000 flight hours after November 20, 2007, whichever occurs first.
Revise ALS To Incorporate CDCCLs

(h) Within 12 months after November 20, 2007, revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007), Section 2, ‘‘Critical Design Configuration Control Limitations.’’ No Alternative Inspections, Inspection Intervals, or CDCCLs

(i) Except as provided by paragraph (j) of this AD: After accomplishing the actions specified in paragraphs (f) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.

New Information Explanation of CDCCL Requirements

Note 3: Notwithstanding any other maintenance or operational requirements, components that have been identified as


### 55126 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations

airworthy or installed on the affected airplanes before the revision of the ALS, as required by paragraph (f) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs.
Alternative Methods of Compliance (AMOCs)

(j)(1) 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. Send information to ATTN: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1622; fax (425)
227–1149.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office.

Related Information

(k) EASA airworthiness directive 2007– 0096 R1, dated May 2, 2007, also addresses the subject of this AD. Material Incorporated by Reference

(l) You must use Airbus A310 ALS Part 5— Fuel Airworthiness Limitations, dated May 31, 2006; and Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007; to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register previously approved the incorporation by reference of Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006; and Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007; on November 20, 2007 (72 FR 58499, October 16, 2007).

(2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// www.airbus.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221 or 425–227–1152.

(4) You may also review copies of the 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/ code

_ of

_ federal

_regulations/ ibr

_ locations.html. Issued in Renton, Washington, on October 19, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–25774 Filed 10–26–09; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0018; Directorate Identifier 2009–NE–01–AD; Amendment 39–**  **16044; AD 2009–21–07]**

**RIN 2120–AA64**

**Airworthiness Directives; General Electric Company CF6–80C2 Series**  **Turbofan Engines**

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

**ACTION :**  Final rule.

**SUMMARY :**  The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6–80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators installed. This AD requires initial visual inspections and repetitive replacements of the 3 ⁄ 8 -inch rod-ends installed on the thrust reverser ballscrew gearbox assembly adjustable-length end actuators. This AD also allows an optional terminating action to those repetitive replacements. This AD also requires initial visual inspections and replacements, if necessary, of the other hardware connecting the thrust reverser transcowls to the engine. This AD results from reports of four failures of rod-ends on certain thrust reverserballscrew gearbox assembly adjustablelength end actuators, leading to partial or complete separation of the transcowl from the engine and airplane during thrust reversal. We are issuing this AD to prevent loss of asymmetric thrust and thrust control.

**DATES :**  This AD becomes effective December 1, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 1, 2009.

**ADDRESSES :**  You can get the service information identified in this AD from Middle River Aircraft Systems, 103 Chesapeake Park Plaza, MF 46, Baltimore, MD 21220; telephone (410) 682–0080; fax (410) 682–0100; or e-mail: bulletins@mras-usa.com.

The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001.

**FOR FURTHER INFORMATION CONTACT :**  Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.j.richards@faa.gov; telephone (781) 238–7133; fax (781)
238–7199.

**SUPPLEMENTARY INFORMATION :**  The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–80C2 series turbofan engines with certain thrust reverserballscrew gearbox assembly adjustablelength end actuators installed. We published the proposed AD in the Federal Register on March 16, 2009 (74 FR 11043). That action proposed to require initial visual inspections and repetitive replacements of the 3 ⁄ 8 -inch rod-ends installed on the thrust reverserballscrew gearbox assembly adjustablelength end actuators. That action also proposed to allow optional terminating action to those repetitive replacements. That action also proposed to require initial visual inspections and replacements, if necessary, of the other hardware connecting the thrust reverser transcowls to the engine. 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 regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the
**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Continue Operating to Next C-Check

Lufthansa Technik asks if the current risk assessment for the 3 ⁄ 8 -inch rod-ends failure also takes into account mixed configurations, meaning lower or upper position with 7 ⁄ 16 -inch or fixed configuration rod-ends. The commenter states that if so, then a mixed configuration should therefore allow the operator to continue operating until next C-Check without any higher risk.