15814 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

procedures specified in paragraph (j) of this 

AD. If debris is found during any inspection 

required by this AD, before further flight, 

remove the debris in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1302, dated 

December 15, 2008; or Boeing Service 

Bulletin 737–57A1302, Revision 1, dated 

October 18, 2010. Doing the actions required 

by paragraph (i) of this AD terminates the 

actions required by paragraphs (g) and (h) of 

this AD. Installation of stainless steel 

lockwire having part number (P/N) 

MS20995C32 is acceptable for compliance in 

lieu of lockwire P/N MS20995NC32, as 

specified in Boeing Alert Service Bulletin 

737–57A1302, dated December 15, 2008, for 

this AD. 

Alternative Methods of Compliance 

(j)(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. Or, 

e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2007–18–52 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Related Information 

(k) For more information about this AD, 

contact 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; e-mail: 

nancy.marsh@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 737–57A1302, dated December 15, 

2008; or Boeing Service Bulletin 737– 

57A1302, Revision 1, dated October 18, 2010; 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information 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 February 

23, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5301 Filed 3–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0090; Directorate 

Identifier 2007–NM–312–AD; Amendment 

39–16627; AD 2011–06–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 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 

measuring the electrical bond resistance 

between the motor operated valve 

(MOV) actuators and airplane structure 

for the main, center, auxiliary, and 

horizontal stabilizer fuel tanks, as 

applicable, and corrective action if 

necessary; revising the maintenance 

program to incorporate airworthiness 

limitation (AWL) No. 28–AWL–21 or 

AWL No. 28–AWL–27, as applicable; 

and replacing production-installed 

laminate phenolic spacers with metallic 

spacers between the fuel jettison MOV 

and the airplane structure, as 

applicable. This AD was prompted by 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent electrical current from flowing 

through an MOV actuator into a fuel 

tank, which could create a potential 

ignition source inside the fuel tank. This 

condition, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: This AD is effective April 26, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 26, 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: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, Seattle Aircraft 

Certification Office, ANM–140S, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6505; fax: 425–917–6590; e-mail: 

tung.tran@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on November 19, 2010 (75 FR 

70863). That SNPRM proposed to 

require measuring the electrical bond 

resistance between the motor operated 

valve (MOV) actuators and airplane 

structure for the main, center, auxiliary, 

and horizontal stabilizer fuel tanks, as 

applicable, and corrective action if 


Emcdonald on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 15815 

necessary; revising the maintenance 

program to incorporate airworthiness 

limitation (AWL) No. 28–AWL–21 or 

AWL No. 28–AWL–27, as applicable; 

and replacing production-installed 

laminate phenolic spacers with metallic 

spacers between the fuel jettison MOV 

and the airplane structure, as 

applicable. 

Actions Since Supplemental NPRM 

Was Issued 

Since the supplemental NPRM was 

issued, Boeing issued Service Bulletin 

747–28A2292, Revision 3, dated 

December 9, 2010. The changes 

described in this service bulletin are 

minor and editorial in nature. 

Paragraphs (c) and (g) of this AD have 

been revised to refer to Revision 3 of 

this service bulletin. In addition, credit 

for accomplishing the actions in Boeing 

Service Bulletin 747–28A2292, Revision 

2, dated May 13, 2010, has been 

included in paragraph (o) of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supports the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for the changes 

that were described above. We have 

determined that these 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. 

Costs of Compliance 

We estimate that this AD affects 222 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Measurement ...................... Up to 7 work-hours × $85 per hour = Up to $595 ............ Up to $350 ....... Up to $945 ....... Up to $209,790. 

Replacement (Up to 60 airplanes).Up to 4 work-hours × $85 per hour = Up to $340 ............ $1,305 .............. Up to $1,645 ..... Up to $98,700. 

Maintenance program revision.1 work-hour × $85 per hour = $85 ................................... $0 ..................... $85 ................... $18,870. 

We estimate the following costs to do 

any necessary modification that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this modification. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Change electrical bond and rework part contact surface.436 work-hours × $85 per hour = $37,060 ............... Up to $35,760 .. Up to $72,820. 

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): 

2011–06–03 The Boeing Company: 

Amendment 39–16627; Docket No. 

FAA–2008–0090; Directorate Identifier 

2007–NM–312–AD. 

Effective Date 

(a) This AD is effective April 26, 2011. 

Affected ADs 

(b) None. 


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15816 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 747– 

200F, 747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin 747–28A2292, 

Revision 3, dated December 9, 2010. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (q) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent electrical current from 

flowing through a motor operated valve 

(MOV) actuator into a fuel tank, which could 

create a potential ignition source inside the 

fuel tank. This condition, 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. 

Measurement, Corrective Action, and 

Replacement 

(g) Within 60 months after the effective 

date of this AD, do the actions required by 

paragraphs (g)(1) and (g)(2) of this AD, as 

applicable. 

(1) Measure the electrical bond resistance 

between the MOV actuators and the airplane 

structure for the main, center, and auxiliary 

fuel tanks, as applicable; and do all 

applicable corrective actions; by 

accomplishing all of the applicable actions in 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–28A2292, Revision 3, 

dated December 9, 2010. The corrective 

actions must be accomplished before further 

flight. 

(2) For airplanes in Groups 12, 16, 17, 18, 

and 19, as identified in Boeing Service 

Bulletin 747–28A2292, Revision 3, dated 

December 9, 2010: Within 60 months after 

the effective date of this AD, replace 

production-installed laminate phenolic 

spacers with metallic spacers, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–28A2292, 

Revision 3, dated December 9, 2010. 

(h) For airplanes identified in Boeing 

Service Bulletin 747–28A2294, Revision 1, 

dated March 5, 2009: Within 60 months after 

the effective date of this AD, measure the 

electrical bond resistance between the MOV 

actuators and airplane structure for the 

horizontal stabilizer fuel tanks (HST), and do 

all the applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

747–28A2294, Revision 1, dated March 5, 

2009. The corrective actions must be 

accomplished before further flight. 

Deactivation of the HST 

(i) For airplanes identified in Boeing 

Service Bulletin 747–28A2294, Revision 1, 

dated March 5, 2009: Deactivation of the 

HST, in accordance with the applicable 

Boeing service information specified in table 

1 of this AD, terminates the requirements of 

paragraph (h) of this AD, except as provided 

by paragraph (j) of this AD. Deactivation of 

the HST before the effective date of this AD 

in accordance with the applicable service 

information specified in table 2 of this AD 

also terminates the requirements of 

paragraph (h) of this AD, except as provided 

by paragraph (j) of this AD. 

TABLE 1—DEACTIVATION SERVICE INFORMATION

Boeing— Revision— Dated— 

Service Bulletin 747–28–2265 ............................................................................................................ Original ............. February 22, 2006. 

Service Bulletin 747–28–2272 ............................................................................................................ Original ............. February 21, 2006. 

Service Bulletin 747–28–2274 ............................................................................................................ 1 ....................... May 21, 2008. 

Service Bulletin 747–28–2275 ............................................................................................................ 4 ....................... February 2, 2009. 

Service Bulletin 747–28–2279 ............................................................................................................ 2 ....................... October 16, 2007. 

Service Bulletin 747–28–2285 ............................................................................................................ 3 ....................... August 30, 2007. 

Service Bulletin 747–28–2293 ............................................................................................................ 2 ....................... March 4, 2008. 

Service Bulletin 747–28–2295 ............................................................................................................ 2 ....................... January 19, 2009. 

Service Bulletin 747–28–2296 ............................................................................................................ Original ............. July 13, 2007. 

Service Bulletin 747–28–2300 ............................................................................................................ 1 ....................... June 2, 2008. 

Service Bulletin 747–28–2314 ............................................................................................................ Original ............. December 9, 2008. 

TABLE 2—DEACTIVATION CREDIT SERVICE INFORMATION

Boeing— Revision— Dated— 

Service Bulletin 747–28–2274 ............................................................................................................ Original ............. March 13, 2006. 

Service Bulletin 747–28–2275 ............................................................................................................ Original ............. June 12, 2006. 

Service Bulletin 747–28–2275 ............................................................................................................ 1 ....................... March 16, 2007. 

Service Bulletin 747–28–2275 ............................................................................................................ 2 ....................... July 2, 2007. 

Service Bulletin 747–28–2275 ............................................................................................................ 3 ....................... March 11, 2008. 

Service Bulletin 747–28–2279 ............................................................................................................ Original ............. June 12, 2006. 

Service Bulletin 747–28–2279 ............................................................................................................ 1 ....................... May 25, 2007. 

Service Bulletin 747–28–2285 ............................................................................................................ Original ............. January 23, 2007. 

Service Bulletin 747–28–2285 ............................................................................................................ 1 ....................... May 9, 2007. 

Service Bulletin 747–28–2285 ............................................................................................................ 2 ....................... August 3, 2007. 

Service Bulletin 747–28–2293 ............................................................................................................ Original ............. May 9, 2007. 

Service Bulletin 747–28–2293 ............................................................................................................ 1 ....................... August 29, 2007. 

Service Bulletin 747–28–2295 ............................................................................................................ Original ............. November 17, 2006. 

Service Bulletin 747–28–2295 ............................................................................................................ 1 ....................... March 20, 2008. 

Service Bulletin 747–28–2300 ............................................................................................................ Original ............. January 16, 2008. 


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Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 15817 

Reactivation of the HST 

(j) For airplanes identified in Boeing 

Service Bulletin 747–28A2294, Revision 1, 

dated March 5, 2009, on which the HST is 

reactivated, the HST must be reactivated in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. For any airplane on which the 

HST is reactivated, the requirements of 

paragraphs (h) and (l) of this AD must be 

done before further flight following the 

reactivation, or within 60 months after the 

effective date of this AD, whichever occurs 

later. For a reactivation method to be 

approved, the reactivation method must meet 

the certification basis of the airplane, and the 

approval must specifically reference this AD. 

Maintenance Program Revision 

(k) For Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 747– 

200F, 747–300, 747SR, and 747SP series 

airplanes: Concurrently with accomplishing 

the actions required by paragraph (g)(1) of 

this AD, revise the maintenance program by 

incorporating airworthiness limitation (AWL) 

No. 28–AWL–21 of Section D of Boeing 

747–100/200/300/SP Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–13747–CMR, Revision March 

2008. 

(l) For Model 747–400, 747–400D, and 

747–400F series airplanes: Concurrently with 

accomplishing the actions required by 

paragraph (g)(1) of this AD, revise the 

maintenance program by incorporating AWL 

No. 28–AWL–27 of Subsection D of Boeing 

747–400 Maintenance Planning Data (MPD) 

Document, Section 9, D621U400–9, Revision 

December 2009. 

No Alternative Critical Design Configuration 

Control Limitations (CDCCLs) 

(m) After accomplishing the applicable 

action required in paragraph (k) or (l) of this 

AD, no alternative CDCCLs may be used 

unless the CDCCLs are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (q) of this AD. 

Terminating Action for Maintenance 

Program Revision 

(n) For Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series airplanes: 

Incorporating AWL No. 28–AWL–21 into the 

maintenance program in accordance with 

paragraph (g) of AD 2008–10–07, 

Amendment 39–15513; or AD 2008–10–07 

R1, Amendment 39–16070; terminates the 

action required by paragraph (k) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(o) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 747–28A2294, dated 

September 21, 2007; and Boeing Service 

Bulletin 747–28A2292, Revision 2, dated 

May 13, 2010; are acceptable for compliance 

with the corresponding requirements of this 

AD. 

Incorporation of Previous Issues of 

Airworthiness Limitation (AWL) 

(p) Incorporation of AWL No. 28–AWL–21 

of Section D of the Boeing 747–100/200/300/ 

SP Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), Document D6–13747–CMR, Revision 

January 2007, September 2007, or January 

2008, is acceptable for compliance with the 

corresponding requirements of this AD if 

done before the effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, Seattle 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 

(r) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, Seattle Aircraft 

Certification Office, ANM–140S, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; phone: 425–917–6505; fax: 425– 

917–6590; e-mail: tung.tran@faa.gov. 

Material Incorporated by Reference 

(s) You must use the applicable service 

information contained in table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. If you 

accomplish the optional terminating action 

specified in this AD, you must use the 

applicable service information specified in 

table 4 of this AD, unless the AD specifies 

otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE FOR REQUIRED ACTIONS

Document Revision Date 

Boeing Service Bulletin 747–28A2292 .............................................................................................................. 3 December 9, 2010. 

Boeing Service Bulletin 747–28A2294 .............................................................................................................. 1 March 5, 2009. 

Boeing 747–100/200/300/SP Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–13747–CMR.March 2008. 

Section 9 of Boeing 747–400 Maintenance Planning Data (MPD) Document, Section 9, D621U400–9 ........ December 2009. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE FOR OPTIONAL TERMINATING ACTION

Boeing— Revision— Dated— 

Service Bulletin 747–28–2265 ......................................................................................................................... Original ........ February 22, 2006. 

Service Bulletin 747–28–2272 ......................................................................................................................... Original ........ February 21, 2006. 

Service Bulletin 747–28–2274 ......................................................................................................................... 1 .................. May 21, 2008. 

Service Bulletin 747–28–2275 ......................................................................................................................... 4 .................. February 2, 2009. 

Service Bulletin 747–28–2279 ......................................................................................................................... 2 .................. October 16, 2007. 

Service Bulletin 747–28–2285 ......................................................................................................................... 3 .................. August 30, 2007. 

Service Bulletin 747–28–2293 ......................................................................................................................... 2 .................. March 4, 2008. 

Service Bulletin 747–28–2295 ......................................................................................................................... 2 .................. January 19, 2009. 

Service Bulletin 747–28–2296 ......................................................................................................................... Original ........ July 13, 2007. 

Service Bulletin 747–28–2300 ......................................................................................................................... 1 .................. June 2, 2008. 

Service Bulletin 747–28–2314 ......................................................................................................................... Original ........ December 9, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 


Emcdonald on DSK2BSOYB1PROD with RULES
15818 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

(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 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 February 

23, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5172 Filed 3–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0058; Directorate 

Identifier 2010–CE–071–AD; Amendment 

39–16640; AD 2011–07–03] 

RIN 2120–AA64 

Airworthiness Directives; Reims 

Aviation S.A. Model F406 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

In early 2005, several reports had been 

received regarding discovery of cracks in 

rudder pulley brackets installed on Reims 

F406 aeroplanes. This pulley bracket, Part 

Number (P/N) 6015511–1, is installed on 

aeroplanes with the optional ‘‘Camera Hole’’ 

modification. 

This condition, if not detected and 

corrected, could result in the loss of rudder 

control on the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

26, 2011. 

On April 26, 2011, the Director of the 

Federal Register approved the 

incorporation by reference of REIMS 

AVIATION INDUSTRIES Service 

Bulletin No. F406–58, REV 2, dated July 

27, 2010, listed in this AD. 

As of February 13, 2007 (72 FR 3047, 

January 24, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of REIMS 

AVIATION INDUSTRIES Service 

Bulletin No. F406–58, REV 1, dated 

October 27, 2006, listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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 service information identified in 

this AD, contact Reims Aviation 

Industries, Ae ́rodrome de Reims Prunay, 

51360 Prunay, France; telephone + 33 3 

26 48 46 65; fax + 33 3 26 49 18 57; 

e-mail Jn.sirot@reims-aviation.fr. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, ACE–112, Kansas 

City, Missouri 64106; telephone: (816) 

329–4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 21, 2011 (76 FR 

3854), and proposed to supersede AD 

2007–02–12, Amendment 39–14899 (72 

FR 3047, January 24, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states that: 

In early 2005, several reports had been 

received regarding discovery of cracks in 

rudder pulley brackets installed on Reims 

F406 aeroplanes. This pulley bracket, Part 

Number (P/N) 6015511–1, is installed on 

aeroplanes with the optional ‘‘Camera Hole’’ 

modification. 

This condition, if not detected and 

corrected, could result in the loss of rudder 

control on the airplane. 

To address this unsafe condition, DGAC 

France issued Emergency (Urgent) AD UF– 

2005–080, followed by the final AD F–2005– 

080, requiring repetitive inspections of the 

P/N 6015511–1 rudder pulley bracket and 

replacement of the bracket with a modified 

bracket, P/N 4061–2701–1, as terminating 

action. 

Recently, Reims discovered that aeroplane 

s/n F406–0091 had inadvertently not been 

included in the SB and this has been revised 

to correct the omission. 

For the reasons described above, this AD 

retains the requirements of DGAC France AD 

F–2005–080, which is superseded, and adds 

aeroplane s/n F406–0091 to the Applicability 

of the AD, by referencing Revision 2 of the 

Reims Aviation Industries SB F406–58. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 7 

products of U.S. registry. We also 

estimate that it will take about 11 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $750 per 

product. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $11,795 or $1,685 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 


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