### 24345 Federal Register / Vol. 76, No. 84 / Monday, May 2, 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:
2011–09–12 Bombardier, Inc.: Amendment 39–16674. Docket No. FAA–2010–1157; Directorate Identifier 2010–NM–137–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective June 6, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the Bombardier, Inc. airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD.

(1) Model DHC–8–101, –102, –103, –106, –201, –202, –301, –311, and –315, serial numbers 003 through 566 inclusive.

(2) Model DHC–8–401, and –402 airplanes, serial numbers 4001, 4003, 4004, 4006, and 4008 through 4274 inclusive.
Subject

(d) Air Transport Association (ATA) of America Code 56: Windows.

Reason

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

There have been several in-service reports of finding trapped water on the bottom of the cockpit windshield frames (or lower windshield frames) that resulted in either corrosion or water ingress into the cockpit. In one occurrence, the trapped water caused severe corrosion of numerous anchor nuts that secure the windshield to the lower windshield frame, such that the intended fastening function was seriously compromised.

Corrosion of the lower windshield frames, including the anchor nuts that secure the windshield to the aircraft structure, can result in a serious structural degradation possibly leading to the loss of the windshield during flight. Also, water could leak into the cockpit and cause either a malfunction or failure of the electrical and electronics systems in the area of the cockpit instrument panels.
* * * * *
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 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, install a drain system in the cockpit windshield lower frames, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–53–78, Revision D, dated July 6, 2010 (for Model DHC–8–101, –102, –103, –106, –201, –202, –301, –311, and –315 airplanes); or 84–53–43, dated April 27, 2010 (for Model DHC–8–401 and –402 airplanes); except where these service bulletins state to contact the manufacturer, contact the New York Aircraft Certification Office or Transport Canada Civil Aviation (TCCA) or its delegated agent. Do all applicable related investigative and corrective actions before further flight.
Credit for Actions Accomplished in Accordance With Previous Service Information

(h) For Models DHC–8–101, –102, –103, –106, –201, –202, –301, –311, and –315 airplanes: Modification of the drain system is also acceptable for compliance with the requirements of paragraph (g) of this AD, if done before the effective date of this AD, in accordance with Bombardier Service Bulletin 8–53–78, dated December 23, 1999; Revision A, dated June 7, 2001; Revision B, dated May 2, 2002; or Revision C, dated April 29, 2010.

FAA AD Differences

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

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, 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 ACO, send it 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, 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 MCAI Canadian Airworthiness Directive CF–2010–16, dated May 18, 2010; Bombardier Service Bulletin 8–53–78, Revision D, dated July 6, 2010; and Bombardier Service Bulletin 84–53–43, dated April 27, 2010; for related information. Material Incorporated by Reference (k) You must use Bombardier Service Bulletin 8–53–78, Revision D, dated July 6, 2010; or Bombardier Service Bulletin 84–53– 43, dated April 27, 2010; 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 Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; e-mail thd.qseries@aero.bombardier.com; Internet http://www.bombardier.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 April 12,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–9673 Filed 4–29–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1205; Directorate Identifier 2010–NM–146–AD; Amendment**  **39–16677; AD 2011–09–15]**

**RIN 2120–AA64**

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

**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 requires, for certain airplanes, replacing certain boost pump relays with ground fault interrupter (GFI) relays. For certain other airplanes, this AD requires installing new panels in the main equipment center, making certain wiring changes, installing new GFI relays in the new panels, and installing


### 24346 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations

new electrical load management system (ELMS) software. For certain other airplanes, this AD requires doing certain bond resistance measurements, and corrective actions if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

**DATES :**  This AD is effective June 6, 2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 6, 2011.

**ADDRESSES :**  For Boeing 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

.

For Smiths and GE Aviation service information identified in this AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, Cincinnati, Ohio 45215; telephone 513–552–3272; e-mail cs.techpubs@ge.com; Internet http://www.geaviation.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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office ( phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: 425– 917–6482; fax: 425–917–6590; e-mail: georgios.roussos@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on December 28, 2010 (75 FR 81508). That NPRM proposed to require, for certain airplanes, replacing certain boost pump relays with ground fault interrupter (GFI) relays. For certain other airplanes, that NPRM proposed to require installing new panels in the main equipment center, making certain wiring changes, installing new GFI relays in the new panels, and installing new electrical load management system (ELMS) software. For certain other airplanes, that NPRM proposed to require doing certain bond resistance measurements, and corrective actions if
necessary.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Boeing supported the NPRM. Request to Extend Compliance Time

American Airlines (AAL) requested that we extend the compliance time in paragraphs (g) and (h) of the NPRM for the work done in accordance with Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010, from 36 months to 60 months. AAL stated that they have already accomplished Boeing Service Bulletin 777–28A0037, Revision 1, dated June 15, 2009, on 75 percent of their Model 777 fleet. The proposed 36-month compliance time would require special scheduling for those airplanes. AAL proposed that the compliance time for all actions in the NPRM be extended to 60 months to be consistent with the 60- month compliance time in paragraph (i) of the NPRM for the GFI relay replacement for the main tank boost pumps specified in Boeing Service Bulletin 737–28A0038, Revision 1, dated September 20, 2010.

We disagree with the request to extend the compliance time for the actions required by paragraphs (g) and (h) of the NPRM (bond resistance measurements and the installation of new panels, new fuel pump control GFI relays, software, and wiring changes). In developing appropriate compliance times for those actions, we considered the safety implications and practical aspects of accomplishing these actions within a period of time that corresponds to the normal scheduled maintenance for most affected operators. In consideration of these items, we have determined that a 36-month compliance time will ensure an acceptable level of safety and allow those actions to be done during scheduled maintenance intervals for most affected operators. However, under the provisions of paragraph (k) of this AD, we will consider requests for approval of an alternative method of compliance (AMOC) if sufficient data are submitted to substantiate that the request would provide an acceptable level of safety. We have not changed this AD in this regard. Request To Delay Rule Pending Release of New Service Bulletins

Japan Airlines (JAL) requested that we delay the issuance of this AD until Boeing and GE Aviation publish new revisions to their service information (referenced in the NPRM) to include certain changes. JAL stated these changes are to correct or add numbers for wires, modules, connectors, and figures. JAL also stated that, in addition, certain GE Aviation service information also needed to be revised to add another procedure to install labels or separate the labels from the conversion kit. JAL explained that when it receives the labels as part of the conversion kit, the remaining shelf life of the labels is not adequate to allow the labels to be installed on the airplanes. JAL is concerned that, unless the service information is revised, these issues could delay incorporation of this AD or result in multiple AMOC requests. JAL stated that they are in communication with Boeing and GE Aviation in regard to these issues with the service information.

We agree with JAL’s concerns about the shelf life of the labels possibly affecting operators’ ability to comply with this AD within the required compliance times. This AD requires all actions, including labeling, in the Accomplishment Instructions of Boeing Service Bulletins 777–28A0038, Revision 1; and 777–28A0037, Revision 2; both dated September 20, 2010; to be accomplished. We have added paragraph (j) to this AD to provide an optional method of labeling panels. However, we disagree with the request to delay this AD until Boeing and GE Aviation issue revised service information to correct or add numbers for wires, modules, connectors, and figures. No data or information to justify that request was provided. However, under the provisions of paragraph (k) of this AD, we will consider requests for


### 24347 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations

an AMOC if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed the AD in this regard.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the change described previously and minor editorial changes. We have determined that these minor changes:

• A re consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM.

We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.
Costs of Compliance

We estimate that this AD will affect 130 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD.



### T ABLE 

### —E STIMATED 

### C OSTS

Action Work hours Average labor rate per hour Parts Cost per product Number of U.S.- registered airplanes Fleet cost

Replacements: Group 1 airplanes identified in

Boeing Service Bulletin 777-28A0038. 3 $85 $25,577 $25,832 126 $3,254,832.

Replacements: Group 2 airplanes identified in

Boeing Service Bulletin 777-28A0038. 3 85 52,545 52,800 0 No airplanes currently on U.S. Register. Replacements: Group 3 airplanes identified in

Boeing Service Bulletin 777-28A0038. 4 85 37,257 37,597 4 $150,388.

Replacements: Group 4 airplanes identified in

Boeing Service Bulletin 777-28A0038. 4 85 17,816 18,156 0 No airplanes currently on U.S. Register.Installations and Measurement: Boeing Service Bulletin 777-28A0037. 76 85 29,934 36,394 130 $4,731,220.

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

This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

(1) Is not a ‘‘ significant regulatory action ’’ under Executive Order 12866, (2) Is not a ‘‘ significant rule ’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. 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):
2011–09–15 The Boeing Company: Amendment 39–16677; Docket No. FAA–2010–1205; Directorate Identifier 2010–NM–146–AD.

Effective Date

(a) This AD is effective June 6, 2011. Affected ADs (b) AD 2008–11–13, Amendment 39– 15536, affects this AD.
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 the service information specified in paragraphs (c)(1) and (c)(2) of this AD.

(1) Boeing Service Bulletin 777–28A0038, Revision 1, dated September 20, 2010.

(2) Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010.
Subject

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

Unsafe Condition

(e) This AD was prompted by fuel system reviews conducted by the manufacturer. The Federal Aviation Administration is issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss 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.

Related Airworthiness Limitation

Note 1: AD 2008–11–13 requires a revision of the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to include limitations for the fuel tank systems. One of the limitations, AWL 28–AWL–18, requires a repetitive


### 24348 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations

inspection of the ground fault interrupter (GFI) functions.

Installations and Software Changes

(g) For Groups 1 and 2 airplanes identified as Configuration 2 in Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010: Within 36 months after the effective date of this AD, install new panels, P301 and P302, in the main equipment center; make certain wiring changes; install new GFI relays in the P301 and P302 panels; and install new electrical load management system (ELMS) software; as applicable. Do the applicable actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010, except as specified in paragraph (j) of this AD.

Note 2: Boeing Service Bulletin 777– 28A0039, Revision 2, dated September 20, 2010, is an additional source of guidance for installing ELMS software.

Note 3: Smiths Service Bulletin 5000ELM– 28–454, dated August 13, 2007; and GE Aviation Service Bulletin 6000ELM–28–455, Revision 1, dated February 1, 2010; are additional sources of guidance for making a wiring change in the P110 and P210 panels, respectively.

(h) For Groups 1 and 2 airplanes identified as Configuration 1 in Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010: Within 36 months after the effective date of this AD, do bonding resistance measurements to verify bonding requirements as specified in Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010, are met, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–28A0037, Revision 2, dated September 20, 2010. Replacement of GFI Relays (i) For airplanes identified in Boeing Service Bulletin 777–28A0038, Revision 1, dated September 20, 2010: Within 60 months after the effective date of this AD, replace 4 main tank boost pump relays in electrical load management system panels P110, P210, and P320 with new GFI relays, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777–28A0038, Revision 1, dated September 20, 2010, except as specified in paragraph (j) of this AD.

Note 4: Boeing Service Bulletin 777– 28A0038, Revision 1, dated September 20, 2010, references the service bulletins identified in Table 1 of this AD as additional sources of guidance for replacing the main tank boost pump relays.



### T ABLE 

### 1—A DDITIONAL 

### S OURCES OF 

### G UIDANCE FOR 

### R EPLACING THE 

### M AIN 

### T ANK 

### B OOST 

### P UMP 

### R ELAYS

Group number of airplanes, as identified in Boeing Service Bulletin 777– 28A0038, Revision 1, dated September 20, 2010 Panel No. Service bulletin Revision level Date

Group 1 ................................................... P110 Smiths Service Bulletin 5000ELM–28– 443. Original ................... August 8, 2007.

Group 1 ................................................... P210 Smiths Service Bulletin 6000ELM–28– 444. Original ................... August 8, 2007.

Group 1 ................................................... P320 Smiths Service Bulletin 4000ELM–28– 445. Original ................... August 8, 2007.

Group 2 ................................................... P110 GE Aviation Service Bulletin 5000ELM– 28–446. 1 ............................. January 7, 2010.

Group 2 ................................................... P210 Smiths Service Bulletin 6000ELM–28– 447. Original ................... August 8, 2007.

Group 2 ................................................... P320 GE Aviation Service Bulletin 4000ELM– 28–448. 1 ............................. January 7, 2010.

Group 3 ................................................... P110 GE Aviation Service Bulletin 5000ELM– 28–449. 1 ............................. January 7, 2010.

Group 3 ................................................... P210 Smiths Service Bulletin 6000ELM–28– 450. Original ................... August 8, 2007.

Group 3 ................................................... P320 GE Aviation Service Bulletin 4000ELM– 28–451. 1 ............................. January 7, 2010.

Group 4 ................................................... P110 Smiths Service Bulletin 5000ELM–28– 463. Original ................... August 8, 2007.

Group 4 ................................................... P210 Smiths Service Bulletin 6000ELM–28– 464. Original ................... August 8, 2007.

Group 4 ................................................... P320 Smiths Service Bulletin 4000ELM–28– 465. Original ................... August 8, 2007.

Optional Method To Install a Label

(j) Where Boeing Service Bulletin 777– 28A0037, Revision 2, dated September 20, 2010; and Boeing Service Bulletin 777– 28A0038, Revision 1, dated September 20, 2010: specify installing a label, an operator’s equivalent procedure may be used as a method to indelibly mark the applicable service bulletin number on the panel.

Note 5: Additional guidance on indelibly marking the panel may also be found in Boeing Standard BAC5307.

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. 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.

Related Information

(l) For more information about this AD, contact Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone: 425–917–6482; fax: 425–917–6590; e-mail: georgios.roussos@faa.gov

. Material Incorporated by Reference

(m) You must use Boeing Service Bulletin 777–28A0038, Revision 1, dated September 20, 2010; or Boeing Service Bulletin 777– 28A0037, Revision 2, dated September 20, 2010; 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 Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC


### 24349 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations

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) For Smiths and GE Aviation service information identified in this AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, Cincinnati, Ohio 45215; telephone 513–552–3272; e-mail cs.techpubs@ge.com; Internet http:// www.geaviation.com

.

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

(5) 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, on April 8,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–9917 Filed 4–29–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1111; Directorate Identifier 2010–NM–129–AD; Amendment**  **39–16676; AD 2011–09–14]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 747–200B, –300, –400,**  **–400D, and –400F Series Airplanes Powered by Pratt and Whitney 4000 or**  **General Electric CF6–80C2 Series 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 requires an inspection to determine the part number of the mid-pivot access door and to determine if the correct door is installed, and the installation of a marker on the mid-pivot access door, and if necessary, repetitive ultrasonicinspections for cracking of the midpivot bolt assembly and eventual replacement of the mid-pivot bolt assembly. This AD was prompted by a report that the left and right access doors of the spring beam mid-pivot bolt assembly for the No. 1 strut were inadvertently installed in the incorrect position during strut modification. We are issuing this AD to detect and correct incorrectly installed mid-pivot bolt assemblies on the spring beam on the outboard struts. Incorrectly installed bolt assemblies could lead to fatigue cracking and consequent fracturing of the mid-pivot bolt assembly, which could lead to loss of the spring beam load path and the possible separation of a strut and engine from the airplane during flight.

**DATES :**  This AD is effective June 6, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 6, 2011.

**ADDRESSES :**  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 . 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Kenneth Paoletti, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057–3356; phone: (425) 917–6434; fax (425) 917–6590; e-mail: Kenneth.Paoletti@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on November 15, 2010 (75 FR 69612). That NPRM proposed to require an inspection to determine the part number of the mid-pivot access door and to determine if the correct door is installed, and the installation of a marker on the mid-pivot access door, and if necessary, repetitive ultrasonicinspections for cracking of the midpivot bolt assembly and eventual replacement of the mid-pivot bolt assembly.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. Support for the NPRM

Boeing supported the contents of the NPRM. Request To Include References to Airplane Maintenance Manual

United Airlines (UAL) stated that it is concerned about the actions in Boeing Alert Service Bulletin 747–54A2232, dated April 15, 2010, being undone and leading to the same condition. UAL suggested that we revise the NPRM to include airplane maintenance manual (AMM) references, including a check for marker BAC27EPP667 before installing the access door. As an alternative, UAL also suggested that the mid-pivot access door part number could be changed instead of keeping the same part number. UAL stated that if the NPRM is not changed to incorporate one of the two options, then the required actions could be undone if doors without the marker are installed.

We disagree with the request to revise this AD. Section 39.7 of the Federal Aviation Regulations (14 CFR 39.7) states the following: ‘‘ Anyone who operates a product that does not meet the requirements of an applicable airworthiness directive is in violation of this section. ’’ Therefore, operators are prohibited from installing a door that does not meet the requirements of this AD. However, operators are permitted to add a check to applicable AMM to prevent installing the incorrect access door. We have not changed the final rule in regard to this issue. Request To Clarify Figures in Service Information

UPS requested that we clarify the figures C–C and D–D on sheets 7 and 8 of Appendix B of Boeing Alert Service Bulletin 747–54A2232, dated April 15, 2010. UPS stated that the transducer