Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24345 

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 


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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 


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

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: 

• Are 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. 

TABLE—ESTIMATED COSTS

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 


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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. 

TABLE 1—ADDITIONAL SOURCES OF GUIDANCE FOR REPLACING THE MAIN TANK BOOST PUMP RELAYS

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 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24349 

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 ultrasonic 

inspections 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 ultrasonic 

inspections 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 


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