### 13075 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

under the criteria of the Regulatory Flexibility Act. 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):
2011–05–12 The Boeing Company: Amendment 39–16622; Docket No. FAA–2010–1156; Directorate Identifier 2010–NM–128–AD.

Effective Date

(a) This AD is effective April 14, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010. Subject

(d) Air Transport Association (ATA) of America Code 55: Stabilizers.

Unsafe Condition

(e) This AD results from a report indicating that a Karon-lined bushing with the liner broken into five pieces was found during a scheduled inspection of the horizontal stabilizer trim actuator (HSTA) components; the broken liner had worn and disbonded from the bushing. The Federal Aviation Administration is issuing this AD to detect and correct discrepancies of the HSTA attachment locations, which could result in reduced structural integrity of the horizontal stabilizer and consequent loss of controllability of the airplane.
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.
Inspection/Related Investigative and Corrective Actions

(g) Before the accumulation of 32,000 total flight cycles, or within 24 months after the effective date of this AD, whichever occurs later: Do a detailed inspection for disbonding and tearing, and a measurement for wear of the internal diameter (ID) of the Karon-lined bushings of the bulkhead support jackscrew fitting and of the jackscrew fitting of the horizontal stabilizer; replace bushings with new bushings, as applicable; do all applicable related investigative and corrective actions; and install either a known serviceable or overhauled HSTA. Do the actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, except as provided by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the actions required by this paragraph thereafter at intervals not to exceed 16,000 flight cycles.
Exceptions to Corrective Actions

(h) If, during any inspection or measurement required by this AD, any damage is found, or the inner diameter is greater than the allowable hole diameter, and Part 1, Step 3.B.2.a.(1)(a)1)a) of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, specifies to contact Boeing for appropriate action: Before further flight, do the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)

(i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane.

Related Information

(j) For more information about this AD, contact Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590; email duong.tran@faa.gov.
Material Incorporated by Reference

(k) You must use Boeing Alert Service Bulletin 777–55A0017, dated May 20, 2010, 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com

.

(3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). 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 an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, February 22, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5086 Filed 3–9–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0156; Directorate Identifier 2010–NM–231–AD; Amendment**  **39–16628; AD 2011–06–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A330–243F Airplanes** 

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

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

**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:

During a recent in-service event the flight crew of a Trent 700 powered A330 aircraft


### 13076 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

reported a temporary Engine Pressure Ratio(EPR) shortfall on engine 2 during the takeoff phase of the flight. * * *

Data analysis confirmed a temporary fuel flow restriction and subsequent recovery, and indicated that also engine 1 experienced a temporary fuel flow restriction shortly after the initial event on engine 2 * * *.

Based on previous industry-wide experience, the investigation of the event has focused on the possibility for ice to temporarily restrict the fuel flow. * * *

* * * The scenario of ice being shed and causing a temporary blockage in the engine fuel system may lead to a temporary fuel flow restriction to the engine. This may result in a possible engine surge or stall condition, and in the engine not being able to provide the commanded thrust.
* * * * *

This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective March 25, 2011.

We must receive comments on this AD by April 25, 2011.

**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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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. Comments will be available in the AD docket shortly after receipt.

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

**SUPPLEMENTARY INFORMATION :**  Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0132, dated June 28, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

During a recent in-service event the flight crew of a Trent 700 powered A330 aircraft reported a temporary Engine Pressure Ratio(EPR) shortfall on engine 2 during the takeoff phase of the flight. The ENG STALL warning was set. The flight crew followed the standard procedures which included reducing throttle to idle. The engine recovered and provided the demanded thrust level for the remainder of the flight.

Data analysis confirmed a temporary fuel flow restriction and subsequent recovery, and indicated that also engine 1 experienced a temporary fuel flow restriction shortly after the initial event on engine 2, again followed by a full recovery. The engine 1 EPR shortfall was insufficient to trigger any associated warning and was only noted through analysis of the flight data. No flight crew action was necessary to recover normal performance on this engine. The remainder of the flight was uneventful.

Based on previous industry-wide experience, the investigation of the event has focused on the possibility for ice to temporarily restrict the fuel flow. While no direct fuel system fault has been identified, the operation of the water scavenge system at Rib 3 cannot be excluded as being a contributory factor.

Testing and analysis are continuing to identify the root cause of the event. The scenario of ice being shed and causing a temporary blockage in the engine fuel system may lead to a temporary fuel flow restriction to the engine. This may result in a possible engine surge or stall condition, and in the engine not being able to provide the commanded thrust.

Therefore, as a precautionary measure to reduce the possibility of ingesting ice into the engine fuel feed system, EASA EAD 2010– 0042–E [which corresponds to FAA AD 2010–08–08] required to: —Deactivate the automatic Standby Fuel

Pump Scavenge System, which operates during Taxi and Take-off by removing relays Functional Item Numbers (FIN) 80QA1 and 80QA2 (this will not affect normal standby pump operation) for aeroplanes identified in the applicability section of this AD and on which this deactivation has not been performed in production through the modification 200801, and —Prohibit the dispatch with * * * [a] MAIN

Fuel Pump inoperative on all aeroplanes identified in the applicability section of this AD.
This AD * * * is issued to extend the applicability to the newly certified model A330–243F.

This AD also requires revising the Limitations section of the airplane flight manual to advise the flight crew of the dispatch prohibition. You may obtain further information by examining the MCAI in the AD docket. FAA’s Determination and Requirements of This AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. 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.

There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Register in the future.

Differences Between the 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 FAA policies. Any such differences are highlighted in a Note within the AD.

FAA’s Determination of the Effective Date

Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2011–0156; Directorate Identifier 2010–NM–231– AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic,


### 13077 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

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. 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. 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 AD:

2011–06–04 Airbus: Amendment 39–16628. Docket No. FAA–2011–0156; Directorate Identifier 2010–NM–231–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March 25, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A330– 243F airplanes; certificated in any category; all manufacturer serial numbers on which Airbus modification 56966H16199 has been embodied in production or Airbus Service Bulletin A330–28–3105 has been embodied in service;.
Subject

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

Reason

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

During a recent in-service event the flight crew of a Trent 700 powered A330 aircraft reported a temporary Engine Pressure Ratio(EPR) shortfall on engine 2 during the takeoff phase of the flight. * * *

Data analysis confirmed a temporary fuel flow restriction and subsequent recovery, and indicated that also engine 1 experienced a temporary fuel flow restriction shortly after the initial event on engine 2 * * *.

Based on previous industry-wide experience, the investigation of the event has focused on the possibility for ice to temporarily restrict the fuel flow. * * *

* * * The scenario of ice being shed and causing a temporary blockage in the engine fuel system may lead to a temporary fuel flow restriction to the engine. This may result in a possible engine surge or stall condition, and in the engine not being able to provide the commanded thrust.
* * * * *
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. Inoperative Fuel Pump Prohibition (g) Dispatch of an airplane with any inoperative main fuel pump is prohibited as of the effective date of this AD.
Airplane Flight Manual Revision

(h) Before further flight after the effective date of this AD, revise the Limitations section of the airplane flight manual (AFM) to include the following statement. This may be done by inserting a copy of this AD into the AFM.

‘‘Dispatch with any inoperative main fuel pump is prohibited. ’’

Note 1: When a statement identical to that in paragraph (h) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: EASA AD 2010–0132, dated June 28, 2010, affected certain Model A330–243, –243F, –341, –342, and –343 airplanes. This AD affects only the newly certified Model A330–243F airplanes. FAA AD 2010–08–08 addresses the identical unsafe condition for the Model A330–243, –341, –342, and –343 airplanes.

Other FAA AD Provisions

(i) 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 manager of the ACO, send it to Attn: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; phone: 425–227–1138; 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

(j) Refer to Airworthiness Information (MCAI) EASA Airworthiness Directive 2010– 0132, dated June 28, 2010, for related information.


### 13078 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

Material Incorporated by Reference

(k) None. Issued in Renton, Washington, on February 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5293 Filed 3–9–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0199; Directorate Identifier 2011–CE–005–AD; Amendment**  **39–16631; AD 2011–06–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500**  **Airplanes Equipped With a Pratt and Whitney Canada, Corp. (PWC)**  **PW610F–A Engine**

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

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

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires you to incorporate operating limitations of maximum operating altitude of 37,000 feet into Section 2, Limitations, of the airplane flight manual (AFM). This AD requires you to incorporate operating limitations of maximum operating altitude of 30,000 feet into Section 2, Limitations, of the AFM. This AD was prompted by several incidents of engine surge. We are issuing this AD to prevent hard carbon buildup on the static vane, which could result in engine surges. Engine surges may result in a necessary reduction in thrust and decreased power for the affected engine. In some cases, this could result in flight and landing under single-engine conditions. It is also possible this could affect both engines at the same time, requiring dual-engine shutdown.

**DATES :**  This AD is effective March 21,
2011.

We must receive any comments on this AD by April 25, 2011.

**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. 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 (phone: 800–647– 5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Eric Kinney, Aerospace Engineer, Ft. Worth Aircraft Certification Office, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5459; fax: (817) 222–5960; e-mail: eric.kinney@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On November 17, 2008, we issued AD 2008–24–07, amendment 39–15747 (73 FR 70866, November 24, 2008), for certain Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes equipped with a Pratt and Whitney Canada, Corp. (PWC) PW610F–A engine. That AD requires you to incorporate operating limitations into Section 2, Limitations, of the airplane flight manual (AFM). That AD resulted from several incidents of engine surge. We issued that AD to prevent hard carbon buildup on the static vane, which could result in engine surges. Engine surges may result in a necessary reduction in thrust and decreased power for the affected engine. In some cases, this could result in flight and landing under single-engine conditions.

Actions Since AD was Issued

Since we issued AD 2008–24–07, the unsafe condition of engine surges due to hard carbon build up blocking the static vanes has continued to occur at 37,000 feet altitude and lower.

Six known events have occurred, five of which were at or below 37,000 feet altitude and four of which were in a two-week period.

Operating effects may include areduction of available thrust or an inflight shutdown of the affected engine. This could occur in flight and require landing under single-engine conditions. It is also possible that this could affect both engines at the same time, requiring dual-engine shutdown.

FAA’s Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
AD Requirements

This AD requires you to incorporate operating limitations of maximum operating altitude of 30,000 feet into Section 2, Limitations, of the AFM.

Interim Action

We consider this AD interim action. The PWC PW610F–A engine is certificated in Canada and is certificated as a foreign type-validated engine under FAA TCDS E00074EN. The FAA understands that Transport Canada (the airworthiness authority for Canada) and PWC are considering potential actions to address the engine aspects of this condition. In the meantime, the FAA is issuing this AD on the Eclipse Model EA500 to address the immediate unsafe condition and to mandate the altitude limitation.
FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because a reduction of available thrust or an in-flight shutdown of the affected engine might occur. This could occur in flight and require landing under single-engine conditions. It is also possible that this could affect both engines at the same time, requiring dual-engine shutdown. Therefore, we find that notice and opportunity for prior public comment are impracticable and that 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 the docket number