## 17884 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules

Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009.

(1) Within 30 days after August 5, 2008. (2) Within 90 days after the installation of a new HVOF-coated spindle.

Note 1: Boeing Alert Service Bulletin 737– 57A1304, dated June 2, 2008; and Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009; reference Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003; for further guidance on accomplishing the related investigative actions.

RESTATEMENT OF REQUIREMENTS OF AD 2009–23–10, AMENDMENT 39–16084: Repetitive Inspections, Related Investigative Actions, and Corrective Action for Certain Airplanes

(i) For airplanes on which a carriage spindle having a serial number identified in Table 3 of Appendix A of Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009, is installed: At the latest of the times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, as applicable, do a detailed inspection (or, as an option for the forward end of the spindle only, a borescope inspection technique may be used) of the spindle for corrosion and potential indications of corrosion of the carriage spindle, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737– 57A1304, Revision 1, dated August 11, 2009. Do all applicable related investigative and corrective actions before further flight. Repeat the detailed inspection (or, as an option for the forward end of the spindle only, the borescope inspection) and related investigative actions (i.e., the gap-check or optional NDT ultrasonic inspection) at the applicable compliance times specified in paragraph 1.E. of Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11,
2009.

(1) Within 30 days after November 24, 2009 (the effective date of AD 2009–23–10).

(2) Within 90 days after the installation of a new HVOF-coated spindle identified in Table 3 of Appendix A of Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009.

(3) Within 90 days after doing an inspection in accordance with Boeing Alert Service Bulletin 737–57A1304, dated June 2,
2008.

Parts Installation

(j) As of August 5, 2008, an HVOF-coated spindle without an ‘R’ suffix on the serial number may be installed on an airplane provided the actions required by paragraph (h) or (i) of this AD, as applicable, are done on that spindle.

NEW REQUIREMENTS OF THIS AD: Terminating Action

(k) Within 48 months after the effective date of this AD: Replace any HVOF-coated carriage spindle having a serial number identified in Table 2 or 3 of Appendix A of Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009, with a non-HVOF coated carriage spindle, or with a serviceable HVOF-coated carriage spindle with an ‘R’ suffix on the serial number, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1304, dated June 2, 2008; or Boeing Service Bulletin 737–57A1304, Revision 1, dated August 11, 2009. Replacing all affected carriage spindles terminates the repetitive inspections required by this AD.
Alternative Methods of Compliance (AMOCs)

(l)(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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. Or, e-mail information to9-ANM-Seattle-ACO-AMOCRequests@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.

(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 Delegation 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 and the approval must specifically refer to this AD.

Issued in Renton, Washington, on April 1,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–7944 Filed 4–7–10; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0375; Directorate Identifier 2010–NM–014–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes; Model**  **CL–600–2C10 (Regional Jet Series 700, 701, & 702) Airplanes; Model CL–600–**  **2D15 (Regional Jet Series 705) and Model CL–600–2D24 (Regional Jet**  **Series 900) Airplanes**

**AGENCY** 

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

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : We propose to adopt a new airworthiness directive (AD) for the products listed above. 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: Following five reported cases of balance washer screw failure on similar ADGs [air-driven generators]/ ram air turbines installed on other aircraft types, investigation by Hamilton Sundstrand determined that a specific batch of the screws had a metallographic non-conformity that increased their susceptibility to brittle fracture. Failure of a balance washer screw can result in loss of the related balance washer, with consequent turbine imbalance. Such imbalance could potentially result in ADG structural failure (including blade failure), loss of ADG electrical power and structural damage to the aircraft and, if deployment was activated by a dual engine shutdown, could also result in loss of hydraulic power for the flight controls [and consequent reduced ability of the flightcrew to maintain the safe flight and landing 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 May 24, 2010.

**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–


## 17885 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules

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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Bombardier, Inc., 400 Co ˆ te-Vertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.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** 

### : Christopher Alfano, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7340; fax (516) 794–5531.

**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–2010–0375; Directorate Identifier 2010–NM–014–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 have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs.

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

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2009–48, dated December 14, 2009 (referred to after this as ‘‘the MCAI’’ ), to correct an unsafe condition for the specified products. The MCAI states:

Following five reported cases of balancewasher screw failure on similar ADGs [airdriven generators]/ram air turbines installed on other aircraft types, investigation by Hamilton Sundstrand determined that a specific batch of the screws had a metallographic non-conformity that increased their susceptibility to brittle fracture. Subsequently, it was established that 152 ‘‘ dry’’ ADGs [Hamilton Sundstrand Part Numbers (P/Ns) in the 761339 series and1711405; see Note] either had nonconforming screws installed duringproduction or may possibly have had nonconforming screws installed during maintenance or repair at Hamilton Sundstrand repair stations.

Failure of a balance washer screw can result in loss of the related balance washer, with consequent turbine imbalance. Such imbalance could potentially result in ADG structural failure (including blade failure), loss of ADG electrical power and structural damage to the aircraft and, if deployment was activated by a dual engine shutdown, could also result in loss of hydraulic power for the flight controls [and consequent reduced ability of the flightcrew to maintain the safe flight and landing of the airplane].

This [Canadian] directive mandates checking the ADG and replacing the balance washer screws, if required. It also prohibits future installation of unmodified ADGs.

Note: ADGs with Hamilton Sundstrand P/ Ns in the 761339 series and 1711405 are installed on the aircraft models listed in the Applicability section above in addition to Bombardier Inc. Model CL–600–2B16. The latter model is covered in a separate directive. 

### You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Bombardier has issued Service Bulletins 601R–24–127, Revision A, dated February 25, 2010; and 670BA– 24–026, dated October 23, 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 1,008 products of U.S. registry. We also estimate that it would take about 10 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 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 $856,800, or $850 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


## 17886 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules

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 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 adding the following new AD:
Bombardier, Inc.: Docket No. FAA–2010– 0375; Directorate Identifier 2010–NM– 014–AD.

Comments Due Date

(a) We must receive comments by May 24,
2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7305 through 7990 inclusive and 8000 and subsequent; Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10003 and subsequent; Model CL– 600–2D15 (Regional Jet Series 705) and Model CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 and subsequent; 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:

Following five reported cases of balancewasher screw failure on similar ADGs [airdriven generators]/ram air turbines installed on other aircraft types, investigation by Hamilton Sundstrand determined that a specific batch of the screws had a metallographic non-conformity that increased their susceptibility to brittle fracture. Subsequently, it was established that 152 ‘‘ dry’’ ADGs [Hamilton Sundstrand Part Numbers (P/Ns) in the 761339 series and1711405; see Note] either had nonconforming screws installed duringproduction or may possibly have had nonconforming screws installed during maintenance or repair at Hamilton Sundstrand repair stations.

Failure of a balance washer screw can result in loss of the related balance washer, with consequent turbine imbalance. Such imbalance could potentially result in ADG structural failure (including blade failure), loss of ADG electrical power and structural damage to the aircraft and, if deployment was activated by a dual engine shutdown, could also result in loss of hydraulic power for the flight controls [and consequent reduced ability of the flightcrew to maintain the safe flight and landing of the airplane].

This [Canadian] directive mandates checking the ADG and replacing the balance washer screws, if required. It also prohibits future installation of unmodified ADGs. Note: ADGs with Hamilton Sundstrand P/ Ns in the 761339 series and 1711405 are installed on the aircraft models listed in the Applicability section above in addition to Bombardier Inc. Model CL–600–2B16. The latter model is covered in a separate directive.

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) For Model CL–600–2C10, CL–600–2D15 and CL–600–2D24 airplanes: At the earliest of the times identified in paragraphs (g)(1), (g)(2), (g)(3), or (g)(4) of this AD, do an inspection to determine the serial number of the installed air-driven generator (ADG), in accordance with the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection if the serial number of the ADG can be conclusively identified from that review.

(1) Within 4,000 flight hours or 18 months after the effective date of this AD, whichever occurs first; or.

(2) Prior to the next in-flight or on-ground functional check of the ADG, whichever occurs first after the effective date of this AD;

or (3) Prior to the next in-flight or on-ground operational check of the ADG, whichever occurs first after the effective date of this AD;

or (4) Before the next scheduled ADG in-flight deployment.

(h) For Model CL–600–2B19 airplanes: At the earliest of the times identified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, do an inspection to determine the serial number of the installed ADG, in accordance with the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the ADG can be conclusively identified from that review.

(1) Within 4,000 flight hours after the effective date of this AD; or

(2) Prior to the next in-flight or on-ground functional check of the ADG, whichever occurs first after the effective date of this AD;

or (3) Prior to the next in-flight or on-ground operational check of the ADG, whichever occurs first after the effective date of this AD;

or (4) Before the next scheduled ADG in-flight deployment.



### TABLE 

### 1—S ERVICE 

### B ULLETINS

Model— Bombardier Service Bulletin— Revision— Dated—

CL–600–2B19 airplanes ...................................................... 601R–24–127 ...................... A .................. ........................ February 25, 2010.


## 17887 Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules

TABLE 

### 1—S ERVICE 

### B ULLETINS

### —Continued

Model— Bombardier Service Bulletin— Revision— Dated—

CL–600–2C10, CL–600–2D15, CL–600–2D24 airplanes ... 670BA–24–026 .................... Original ................................ Octob er 23, 2009.

(i) If the ADG serial number determined in paragraph (g) or (h) of this AD is identified in paragraph 1.A. of the applicable service bulletin listed in Table 1 of this AD, before further flight do an inspection to determine if the symbol ‘‘ 24–5 ’’ is marked on the ADG identification plate. A review of airplane maintenance records is acceptable in lieu of this inspection if the symbol ‘‘ 24–5 ’’ mark can be conclusively identified from that review.

(1) If the symbol ‘‘ 24–5 ’’ is marked on the ADG identification plate, the balance washer screws have already been replaced, and no further action is required by this paragraph.

(2) If the symbol ‘‘ 24–5 ’’ is not marked on the ADG identification plate, before further flight replace all balance washer screws with new balance washer screws, part number MS24667–14, and mark the ADG identification plate with symbol ‘‘ 24–5, ’’ in accordance with the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD.

(j) As of the effective date of this AD, no person may install on any airplane, a replacement or spare ADG, Hamilton Sundstrand part number in the 761339 or 1711405 series, having one of the serial numbers identified in paragraph 1.A. of the applicable service bulletin identified in Table 1 of this AD, unless the ADG is identified with the symbol ‘‘ 24–5 ’’ on the identification plate.
Actions Accomplished According to Previous Issue of Service Bulletin

(k) Inspections accomplished before the effective date of this AD according to Bombardier Service Bulletin 601R–24–127, dated October 23, 2009, are considered acceptable for compliance with the corresponding action specified in this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI specifies to inspect only airplanes having certain serial numbers that are part of the MCAI applicability. Because the affected part could be rotated onto any of the airplanes listed in the applicability, this AD requires the inspection be done on all airplanes. We have coordinated this with the TCCA.

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. 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.

(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

(m) Refer to MCAI Canadian Airworthiness Directive CF–2009–48, dated December 14, 2009; and Bombardier Service Bulletins 601R–24–127, Revision A, dated February 25, 2010, and 670BA–24–026, dated October 23, 2009; for related information.

Issued in Renton, Washington, on April 1,
2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–7947 Filed 4–7–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0377; Directorate Identifier 2009–NM–246–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Model 767 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 767 airplanes. This proposed AD would require doing a detailed inspection for correct main track downstop assembly, thread protrusion, and damaged and missing parts of the main track downstop assemblies of the outboard slats, and related investigative and corrective actions if necessary. This proposed AD would also require doing a detailed inspection for foreign objects debris and damage to the wall of the track housing of the outboard slats, and corrective actions if necessary. This proposed AD results from reports of broken bolts in the outboard slat main track downstop assembly. We are proposing this AD to detect and correct incorrectly installed main track downstop assemblies, which can allow the main track downstop hardware to fall into the track housing and cause a puncture in the track housing when the slat is retracted. This condition, if not corrected, could result in a fuel leak and an increased risk of fire.

**DATES** 

### : We must receive comments on this proposed AD by May 24, 2010.

**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.