## 65938 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations

airplanes; Model A300 B4–605R and B4– 622R airplanes; Model A300 F4–605R and F4–622R airplanes; Model A300 C4–605R Variant F airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category.
Subject

(d) Air Transport Association (ATA) of America Code 24: Electrical Power.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

An operator reported several cases of wire damages at the pylon/wing interface. Analysis revealed that wires damages are due to installation quality issue resulting from lack of information in installation drawings and job cards.

Moreover detailed analysis has highlighted that the Low Pressure Valve (LPV) wires were not segregated by design.


### * * * * *

If left uncorrected, the wire chafing could impact fire protection and detection system. It may also induce dormant failure on LPV preventing its closure leading to a permanent and uncontrolled fire (in case of fire ignited upstream the High Pressure Valve (HPV)).


### * * * * *
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Actions

(g) Within 30 months or 4,000 flight hours after the effective date of this AD, whichever occurs first: Modify the electrical installation in the pylon/wing interface on the left-hand and right-hand side by doing a general visual inspection of wires for damage and doing all applicable repairs, replace the cable tie with lacing tape, improve the electrical installation at the level of the electrical ramp, and improve the segregation of both routes of the LPV channels 1 and 2 between LPV connector and ramp; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24–6106, excluding Appendix 01, dated March 31, 2010 (for Airbus Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes); or Airbus Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011 (for Airbus Model A310 series airplanes). Do all applicable repairs before further flight.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(h) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9- ANM-11-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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(i) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010– 0178R1, excluding Appendix 01, dated May 20, 2011; Airbus Mandatory Service Bulletin A300–24–6106, dated March 31, 2010; and Airbus Mandatory Service Bulletin A310–24– 2106, Revision 01, including Appendix 01, dated April 4, 2011; for related information.
Material Incorporated by Reference

(j) You must use Airbus Mandatory Service Bulletin A300–24–6106, excluding Appendix 01, dated March 31, 2010; or Airbus Mandatory Service Bulletin A310–24–2106, Revision 01, including Appendix 01, dated April 4, 2011; as applicable; to do the actions required by this AD, unless the AD specifies otherwise.

(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 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.

(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 11, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–27005 Filed 10–24–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0650; Directorate Identifier 2010–NM–257–AD; Amendment**  **39–16846; AD 2011–22–04]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A310 Series Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88).

In their letters referenced 04/00/02/07/01– L296, dated March 4th, 2002, and 04/00/02/ 07/03–L024, dated February 3rd, 2003, the [Joint Aviation Authorities] JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA).

Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 3,402 kg (7,500 lb) or more which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks.


### * * * * * The unsafe condition is insufficient electrical bonding of the over-wing refueling cap adapter, which could result in a possible fuel ignition source in the fuel tanks. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective November 29, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 29, 2011.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http://


## 65939 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations

www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on July 5, 2011 (76 FR 39035). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88).

In their letters referenced 04/00/02/07/01– L296, dated March 4th, 2002, and 04/00/02/ 07/03–L024, dated February 3rd, 2003, the JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA).

Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 3,402 kg (7,500 lb) or more which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks.


### * * * * *

* * * [This EASA AD] requires the additional work introduced by Airbus SB A310–28–2142 at revision 3.


### The unsafe condition is insufficient electrical bonding of the over-wing refueling cap adapter, which could result in a possible fuel ignition source in the fuel tanks. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (76 FR 39035, July 5, 2011) or on the determination of the cost to the public. Revision to Airbus Mandatory Service Bulletin A310–28–2142

Airbus has issued Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010. No additional work is included in this revision for airplanes modified by any previous issue of this document. We have changed paragraphs (g), (g)(1), (g)(2), (h), (k), and sub-paragraph (1) of Note 1 of this AD to refer to Airbus Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010, and added paragraph (i) to this AD to give credit for actions accomplished in accordance with Airbus Mandatory Service Bulletin A310–28–2142, Revision 03, dated November 18, 2009.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance

We estimate that this AD will affect 66 products of U.S. registry. We alsoestimate that it will take about 4 workhours 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 $200 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $35,640, or $540 per product. 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 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); 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. 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 the NPRM (76 FR 39035, July 5, 2011), 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. Comments will be available in the AD docket shortly after receipt. 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:


## 65940 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations

**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 AD:

2011–22–04 Airbus: Amendment 39– 16846. FAA–2011–0650; Directorate Identifier 2010–NM–257–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 29, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to airplanes identified in paragraphs (c)(1) and (c)(2) of this AD.

(1) Airbus Model A310–203, A310–204, A310–221 and A310–222 airplanes (without trim tank), all serial numbers, except airplanes on which Airbus Mandatory Service Bulletin A310–28–2143, dated July 20, 2005; and Airbus Mandatory Service Bulletin A310–28–2142, Revision 03, dated November 18, 2009; have been done; certificated in any category.

(2) Model A310–304, A310–322, A310– 324, and A310–325 airplanes (fitted with trim tank), all serial numbers, except airplanes on which Airbus Mandatory Service Bulletin A310–28–2143, dated July 20, 2005; Airbus Mandatory Service Bulletin A310–28–2153, dated July 20, 2005; and Airbus Mandatory Service Bulletin 310–28– 2142, Revision 03, dated November 18, 2009; have been done; certificated in any category.
Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel System.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

[T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88).

In their letters referenced 04/00/02/07/01– L296, dated March 4th, 2002, and 04/00/02/ 07/03–L024, dated February 3rd, 2003, the [Joint Aviation Authorities] JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA). Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 3,402 kg (7,500 lb) or more which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks.


### * * * * * The unsafe condition is insufficient electrical bonding of the over-wing refueling cap adapter, which could result in a possible fuel ignition source in the fuel tanks.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Resistance Measurement

(g) For configuration 05 and 06 airplanes, as identified in Airbus Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010, on which any Airbus service bulletin identified in table 1 of this AD has been done: Within 3 months after the effective date of this AD, do the actions in paragraph (g)(1) or (g)(2) of this AD, as applicable.



### T ABLE 

### 1—P REVIOUSLY 

### A CCOMPLISHED 

### A IRBUS 

### S ERVICE 

### B ULLETINS

Airbus Service Bulletin Revision Date

Airbus Mandatory Service Bulletin A310–28–2142 ................................................................................. ............................ August 26, 2005. Airbus Mandatory Service Bulletin A310–28–2142 ................................................................................. 01 July 17, 2006. Airbus Mandatory Service Bulletin A310–28–2142 ................................................................................. 02 September 3, 2007.

(1) For configuration 05 airplanes: Do a resistance check of the inboard and outboard over-wing refuel cap mounts between the flange face of the refuel insert and the wing, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010.

(2) For configuration 06 airplanes: Do a resistance check of the outboard over-wing refuel cap mounts between the flange face of the refuel insert and the wing, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–28– 2142, Revision 04, dated November 30, 2010.

Corrective Action

(h) If during any resistance measurement required by paragraph (g)(1) or (g)(2) of this AD, a resistance of 10 milliohm (mohm) or greater is found: Before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–28– 2142, Revision 04, dated November 30, 2010.
Credit for Actions Accomplished in Accordance With Previous Service Information

(i) Resistance measurements and corrective actions done in accordance with Airbus Mandatory Service Bulletin A310–28–2142, Revision 03, dated November 18, 2009, before the effective date of this AD are acceptable for compliance with the corresponding resistance measurements and corrective actions required by paragraphs (g) and (h) of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows:

(1) Airbus Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010, specifies that if any resistance measurement is more than 10 mohm, corrective actions must be done. This AD specifies that if any resistance measurement is 10 mohm or greater, corrective actions must be done.

(2) Paragraphs (1), (2), and (4) of European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0199, dated September 30, 2010, include actions that are not required in this AD. These actions are required by AD 2007–20–04, Amendment 39–15214 (72 FR 56258, October 3, 2007).

Other FAA AD Provisions

(j) 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. Send information to Attn: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(k) Refer to MCAI EASA Airworthiness Directive 2010–0199, dated September 30, 2010; and Airbus Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010. Material Incorporated by Reference

(l) You must use Airbus Mandatory Service Bulletin A310–28–2142, Revision 04, dated November 30, 2010, to do the actions


## 65941 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Rules and Regulations

required by this AD, unless the AD specifies otherwise.

(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 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.

(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 13, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–27393 Filed 10–24–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0993; Directorate Identifier 2010–NE–08–AD; Amendment 39–**  **16849; AD 2011–22–07]**

**RIN 2120–AA64**



### Airworthiness Directives; Rolls-Royce **plc RB211–524 Series, RB211–Trent 700 Series, and RB211–Trent 800**  **Series Turbofan Engines**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72–D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition.

Since Rolls-Royce Service Bulletin No. 72– E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72– D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72–E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. 

### We are issuing this AD to detect cracks in the front combustion liner, which could result in hot section distress, multiple blade release, and possible damage to the airplane.

**DATES** 

### : This AD becomes effective November 29, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 29, 2011.

**ADDRESSES** 

### : 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** 

### : Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; phone: 781– 238–7143; fax: 781–238–7199.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 5, 2010 (75 FR 61363). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that:

Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72–D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition.

Since Rolls-Royce Service Bulletin No. 72– E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72– D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72–E902 are also considered to be potentially affected and are therefore included in the applicability of this AD.

This AD requires a change to the initial and repeat borescope inspection intervals for the front combustion liner.



### Comments

We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Expand Address for Service Information

One commenter, Rolls-Royce plc (RR), asked us to consider changing the information for getting the service information to ‘‘For any questions concerning the technical content of the requirements in this AD (NPRM), please contact your designated Rolls-Royce representative for a copy of the service information, please download the publication from your Aeromanager
account at http://
www.aeromanager.com . If you do not have a designated representative or an Aeromanager account, please contactCorporate Communications at RollsRoyce plc, PO Box 31, Derby, DE24 8BJ, United Kingdom, phone: 011–44–1331– 242424, fax: 011–44–1332–249936, or e-mail: http://www.rolls-royce.com/ contact/civil

_ team.jsp identifying the correspondence as being related to Airworthiness Directives.’’ RR states that this should make sure that any questions from operators of their engines and those from other parties are directed to the area best equipped to

answer.

We partially agree. We agree that operators and maintenance providers need to get timely and accurate service information, and that additional information is worth including. We changed paragraph (k) of the AD to state ‘‘* * * contact Corporate Communications at Rolls-Royce plc PO Box 31, Derby, DE24 8BJ, United Kingdom, Phone: 011–44–1331–242424, fax 011–44–1332–249936 or e-mail from http://www.rolls-royce.com/contact/ civil

_ team.jsp identifying the correspondence as being related to Airworthiness Directives.’’

We do not agree that operators or maintenance providers should contact RR for questions about this AD. We did not include that information in the AD. Requests To Change References to the Service Bulletin That Is Incorporated by Reference

Two commenters, American Airlines (AA) and The Boeing Company (Boeing), asked us to add ‘‘or later