### 74665 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

fuel feed tube, and could result in a fire or explosion.
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

(g) Within 24 months after the effective date of this AD, do a general visual inspection to determine the routing of the wire bundles in the number two and number three engine pylons near the leading edge; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–29A2114, Revision 1, dated July 15, 2010. Do all applicable related investigative and corrective actions before further flight.
Concurrent Requirements

(h) For Model 747–400 series airplanes: Before or concurrently with accomplishing the requirements of paragraph (g) of this AD, install all applicable cable support brackets in the number two and number three engine pylon areas, and do all applicable related investigative and corrective actions, in accordance with Phase II of Boeing Service Bulletin 747–24A2168, Revision 3, dated July 29, 1993. Do all applicable related investigative and corrective actions before further flight. Doing the actions required by paragraph (c) of AD 92–27–13, Amendment 39–8488, is an acceptable method of compliance with the installation required by this paragraph.

Note 1: For the purposes of this AD, a detailed inspection is: ‘‘ An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. ’’

Credit for Actions Accomplished in Accordance With Previous Service Information

(i) Actions accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–29A2114, dated October 1, 2009, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD.

(j) Actions accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–24A2168, Revision 1, dated December 5, 1991; or Revision 2, dated September 24, 1992; are considered acceptable for compliance with the corresponding actions specified in paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)

(k)(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. Send information to ATTN: Tung Tran, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356, telephone (425) 917–6505; fax (425) 917–6590. Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(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. The AMOC approval letter must specifically reference this AD.

Issued in Renton, Washington, on November 15, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–30134 Filed 11–30–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1162; Directorate Identifier 2010–NM–099–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A310 Airplanes, and Airbus Model**  **A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R**  **Variant F Airplanes (Collectively Called A300–600 Series Airplanes)** 

**AGENCY :**  Federal Aviation Administration, DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed 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:

Prompted by a reported in-service event, EASA issued AD 2009–0084 to prevent unwanted movement of pilot- or co-pilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.
* * * * * Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  We must receive comments on this proposed AD by January 18, 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.

For service information identified in this proposed 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. You may review copies of the referenced 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. 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 proposed 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 :**  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 :** 


### 74666 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2010–1162; Directorate Identifier 2010–NM–099–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 proposed AD.

Discussion

On May 15, 2009, we issued AD 2009–11–09, Amendment 39–15919 (74 FR 25399, May 28, 2009). That AD required actions intended to address an unsafe condition on the products listed above.

Since we issued AD 2009–11–09, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0070, dated April 14, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

Prompted by a reported in-service event, EASA issued AD 2009–0084 [which corresponds to FAA AD 2009–11–09] toprevent unwanted movement of pilot- or copilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.

AD 2009–0084 required the deactivation of the electrical power of SOGERMA pilot seats P/N 2510112 series and co-pilot seats P/N 2510113 series. Optional intermediate actions were also provided by AD 2009–0084 to allow partial or full restoration of seat adjustment functionality.

Since AD 2009–0084 was issued, a permanent solution has been developed that terminates the de-activation requirement and invalidates the intermediate actions.

Consequently, this AD retains requirements of EASA AD 2009–0084, which is superseded, and requires implementing the terminating action. In addition, this AD prohibits the (re)installation of unmodified pilot- and co-pilot seats on any aeroplane that has been modified in accordance with the requirements of this AD.

Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued the service information specified in the following table.



### TABLE

### —S ERVICE 

### I NFORMATION

Document Revision Date

Airbus Mandatory Service Bulletin A300–25–6217 ....................................................... Original ........................................ August 31, 2009. Airbus Mandatory Service Bulletin A310–25–2205 ....................................................... Original ........................................ August 31, 2009.

The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed 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 proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.

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 proposed 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 proposed AD. Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 132 products of U.S. registry.

The actions that are required by AD 2009–11–09 and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $170 per product.

We estimate that it would take about 2 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $5,000 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 costs. 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 the proposed AD on U.S. operators to be $704,880, or $5,340 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.


### 74667 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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 proposed 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. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 39–15919 (74 FR 25399, May 28, 2009) and adding the following new AD:

Airbus: Docket No. FAA–2010–1162; Directorate Identifier 2010–NM–099–AD.

Comments Due Date

(a) We must receive comments by January 18, 2011.

Affected ADs

(b) This AD supersedes AD 2009–11–09, Amendment 39–15919.
Applicability

(c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category; all serial numbers having SOGERMA 2510112 series pilot electrical seats or SOGERMA 2510113 series co-pilot electrical seats installed.

(1) Airbus Model A300 B4–601, A300 B4– 603, A300 B4–620, and A300 B4–622, A300 B4–605R and A300 B4–622R; A300 F4–605R and A300 F4–622R; and A300 C4–605R Variant F airplanes.

(2) Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes.
Subject

(d) Air Transport Association (ATA) of America Code 25: Equipment/Furnishings.

Reason

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

Prompted by a reported in-service event, EASA issued AD 2009–0084 to prevent unwanted movement of pilot- or co-pilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.
* * * * *

Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control 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.
Restatement of Requirements of AD 2009– 11–09, With No Changes

(g) Within 15 days after June 12, 2009 (the effective date of AD 2009–11–09): Deactivate the electrical supply of SOGERMA 2510112 series pilot seats and SOGERMA 2510113 series co-pilot seats, in accordance with the instructions of Airbus All Operators Telex (AOT) A310–25A2203, Revision 02, dated March 2, 2009; or Airbus AOT A300– 25A6215, Revision 02, dated March 2, 2009; as applicable.

(h) For optional intermediate action for restoration of the electrical adjustment of the vertical seat movement only: Deactivating the electrical powered horizontal movement of SOGERMA 2510112 series pilot seats or SOGERMA 2510113 series co-pilot seats, in accordance with the instructions of EADS SOGERMA Alert Service Bulletin A2510112– 25–764, Revision 1, dated February 17, 2009, allows restoration of the vertical adjustment only.

(i) For optional intermediate action for restoration of the electrical adjustment of the vertical seat and horizontal seat movement: Inspecting the position of switch ‘S4’ and the related shim of SOGERMA 2510112 seriespilot seats or SOGERMA 2510113 series copilot seats, in accordance with EADS SOGERMA Inspection Service Bulletin 2510112–25–807, dated February 20, 2009, allows reactivation of both horizontal and vertical electrical movements, provided the measurement results of the inspection are within the acceptable value indicated in the service bulletin, and provided that the inspection is repeated thereafter at intervals not to exceed 2 months. If the measurement result of any inspection is not within the acceptable value indicated in the EADS SOGERMA Inspection Service Bulletin 2510112–25–807, dated February 20, 2009, the horizontal movement must be deactivated before further flight.

(j) At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD: Submit a report of the findings for the first inspection done in accordance with paragraph (i) of this AD to Airbus SAS–EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include a detailed fleet inspection report, including measurement values, and pin and serial numbers for each seat.

(1) If the inspection was done on or after June 12, 2009: Submit the report within 30 days after the inspection.

(2) If the inspection was accomplished prior to June 12, 2009: Submit the report within 30 days after June 12, 2009.

(k) Modifications made prior to June 12, 2009, in accordance with EADS SOGERMA Alert Service Bulletin A2510112–25–764, dated December 19, 2008, are considered acceptable for compliance with the applicable action specified in this AD.
New Requirements of This AD

(l) Within 12 months after the effective date of this AD: Install an enlarged shim for the horizontal switch actuation on each affected seat, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–25–6217 (for Model A300–600 airplanes) or A310–25– 2205 (for Model A310 airplanes), both dated August 31, 2009. Doing the installation required by paragraph (l) of this AD terminates the requirements of paragraphs (g), (h), and (i) of this AD.

(m) As of the effective date of this AD, no person may install any SOGERMA 2510112 series pilot seat or SOGERMA 2510113 series co-pilot seat, on any airplane, unless that seat has been modified in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–25–6217 (for Model A300–600 airplanes) or A310–25– 2205 (for Model A310 airplanes), both dated August 31, 2009; as applicable.

FAA AD Differences

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

Other FAA AD Provisions

(n) 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. 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. 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.


### 74668 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Proposed Rules

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.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (o) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2010–0070, dated April 14, 2010; and the service information specified in Table 1 of this AD; as applicable; for related information.



### TABLE 

### 1—S ERVICE 

### I NFORMATION

Document Revision Date

Airbus All Operators Telex A300–25A6215 .................................................................. 02 ................................................. March 2, 2009. Airbus All Operators Telex A310–25A2203 .................................................................. 02 ................................................. March 2, 2009. Airbus Mandatory Service Bulletin A300–25–6217 ....................................................... Original ........................................ August 31, 2009. Airbus Mandatory Service Bulletin A310–25–2205 ....................................................... Original ........................................ August 31, 2009. EADS SOGERMA Alert Service Bulletin A2510112–25–764 ....................................... 1 ................................................... February 17, 2009. EADS SOGERMA Inspection Service Bulletin A2510112–25–807 .............................. Original ........................................ February 20, 2009.

Issued in Renton, Washington, on November 18, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–30135 Filed 11–30–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1156; Directorate Identifier 2010–NM–128–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 777–200, –200LR,**  **–300, and –300ER Series Airplanes**

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD would require repetitive detailed inspections for disbonding and tearing and measurements 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; repetitive installations of the horizontal stabilizer trim actuator (HSTA); and if necessary, replacement of the bushings with new bushings and all applicable related investigative and corrective actions. This proposed 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 HSTA components; the broken liner had worn and disbonded from the bushing. We are proposing 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.

**DATES :**  We must receive comments on this proposed AD by January 18, 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.

For service information identified in this proposed 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. You may review copies of the referenced 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. 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 proposed 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 :**  Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2010–1156; Directorate Identifier 2010–NM–128–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD.