Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 37997 

Accomplishment Instructions of the 

applicable service bulletin listed in Table 1 

of this AD. 

Note 2: The part numbers in parentheses in 

paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), and 

(g)(3) of this AD, are equivalent specification 

part numbers, as specified in the applicable 

service bulletin listed in Table 1 of this AD. 

(4) Replacement of an accumulator with a 

new accumulator having the same part 

number is also acceptable for compliance 

with the requirements of paragraph (g)(2) of 

this AD, if done before the effective date of 

this AD in accordance with the applicable 

service bulletin listed in Table 2 of this AD. 

TABLE 2—PREVIOUS SERVICE BULLETINS

Airplane model— 

Bombardier 

service 

bulletin— 

Revision— Dated— 

CL–600–1A11 (CL–600) .................................................................................................. 600–0742 Original ......... November 10, 2008. 

CL–600–1A11 (CL–600) .................................................................................................. 600–0742 01 ................. July 6, 2009. 

CL–600–2A12 (CL–601), CL–600–2B16 (CL–601–3A, CL–601–3R variant) ................ 601–0597 Original ......... November 10, 2008. 

CL–600–2A12 (CL–601), CL–600–2B16 (CL–601–3A, CL–601–3R variant) ................ 601–0597 01 ................. July 6, 2009. 

CL–600–2B16 (CL–604 variant) ...................................................................................... 604–29–008 Original ......... November 10, 2008. 

CL–600–2B16 (CL–604 variant) ...................................................................................... 604–29–008 01 ................. July 6, 2009. 

CL–600–2B16 (CL–605) .................................................................................................. 605–29–001 Original ......... November 10, 2008. 

CL–600–2B16 (CL–605) .................................................................................................. 605–29–001 01 ................. July 6, 2009. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 

(1) The MCAI specifies that certain 

airplanes do not need to be inspected for the 

part number; however, this AD requires that 

inspections be done on all airplanes to 

determine the part number. 

(2) The MCAI specifies to record the 

number of flight cycles accumulated on each 

affected part. This AD does not require that 

operators record the number of flight cycles. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York, 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–39, dated October 27, 

2009, and the service bulletins listed in Table 

1 of this AD, for related information. 

Material Incorporated by Reference 

(j) You must use the service information 

contained in Table 3 of this AD, 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., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@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. 

TABLE 3—MATERIAL INCORPORATED

BY REFERENCE

Bombardier 

service 

bulletin— 

Revision— Dated— 

600–0742 ........ 02 May 10, 2010. 

601–0597 ........ 02 May 10, 2010. 

604–29–008 .... 02 May 10, 2010. 

605–29–001 .... 02 May 10, 2010. 

Issued in Renton, Washington, on June 17, 

2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–15845 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0906; Directorate 

Identifier 2009–NM–075–AD; Amendment 

39–16343; AD 2010–13–12] 

RIN 2120–AA64 

Airworthiness Directives; 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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 747 series airplanes. This AD 

requires replacing the power control 

relays for the main tank fuel boost 

pumps and jettison pumps, and the 

center tank scavenge pump, as 

applicable, with new relays having a 

ground fault interrupt (GFI) feature. 

This AD also requires revising the 

maintenance program to incorporate 

Airworthiness Limitations (AWLs) 28– 

AWL–23 (for Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–200F, 747–300, 747SP, and 

747SR series airplanes), and AWLs 28– 

AWL–28 and 28–AWL–29 (for Model 

747–400, 747–400D, and 747–400F 

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37998 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 

series airplanes). This AD results from 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent damage to the fuel pumps 

caused by electrical arcing that could 

introduce an ignition source in the fuel 

tank, 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 August 5, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 5, 2010. 

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. 

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 (telephone 800–647–5527) 

is the 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; telephone 

(425) 917–6482; fax (425) 917–6590. 

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 

certain Model 747 series airplanes. That 

NPRM was published in the Federal 

Register on October 13, 2009 (74 FR 

52431). That NPRM proposed to require 

replacing the power control relays for 

the main tank fuel boost pumps and 

jettison pumps, and the center tank 

scavenge pump, as applicable, with new 

relays having a ground fault interrupt 

(GFI) feature. That NPRM also proposed 

to require revising the maintenance 

program to incorporate Airworthiness 

Limitations (AWLs) 28–AWL–23 (for 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SP, and 747SR series 

airplanes), and AWLs 28–AWL–28 and 

28–AWL–29 (for Model 747–400, 747– 

400D, and 747–400F series airplanes). 

Relevant Service Information 

For Model 747–400, 747–400D, and 

747–400F series airplanes, we have 

reviewed Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS— 

FUEL SYSTEMS,’’ of Boeing 747–400 

Maintenance Planning Data (MPD) 

Document, Document D621U400–9, 

Section 9, Revision December 2009. 

This document includes the same 

repetitive inspection (test) to verify 

continued functionality of the GFI 

relays as did Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS— 

FUEL SYSTEMS,’’ of Boeing 747–400 

MPD Document, Document D621U400– 

9, Section 9, Revision April 2008 (which 

we referred to in the NPRM as an 

appropriate source of service 

information for incorporation into the 

maintenance program). Revision 

December 2009 clarifies the effectivity 

for AWL 28–AWL–28. We have revised 

paragraph (h)(1) of this AD to refer to 

Subsection D, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS,’’ of 

Boeing 747–400 MPD Document, 

Document D621U400–9, Section 9, 

Revision December 2009. We have also 

added a new paragraph (j) to this final 

rule to provide credit for operators who 

have revised their maintenance program 

using Revision April 2008, or Revision 

March 2009, of Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS— 

FUEL SYSTEMS,’’ of Boeing 747–400 

MPD Document, Document D621U400– 

9, Section 9. We have also reidentified 

subsequent paragraphs accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered all of the comments received 

from the commenters. 

Request To Extend Compliance Time 

Deutsche Lufthansa AG (Lufthansa) 

requests that we extend the proposed 

compliance time from 60 months to the 

intervals specified in the latest 

approved maintenance review board 

report (MRBR). Further, Lufthansa states 

that it would like to know how the 

proposed compliance time was 

determined. Lufthansa states that it 

assumes that the probability of a failure 

is part of the determination of the 

proposed compliance time of 60 

months. However, Lufthansa further 

asserts that this compliance time is not 

in line with its heavy maintenance 

layover schedule, which is based on the 

latest approved MRBR. 

We do not agree to extend the 

compliance time. In developing an 

appropriate compliance time for this 

AD, we considered not only the safety 

implications, but the manufacturer’s 

recommendations, the availability of 

required parts, and the practical aspect 

of accomplishing the actions within an 

interval of time that corresponds to 

typical scheduled maintenance for 

affected operators. However, under the 

provisions of paragraph (k) of this AD, 

we will consider requests for approval 

of an extension of the compliance time 

if sufficient data are submitted to 

substantiate that the change would 

provide an acceptable level of safety. 

We have not changed the final rule in 

this regard. 

Request To Clarify if Boeing Alert 

Service Bulletin 747–28A2261 

Terminates Requirements of Previous 

AD 

Japan Airlines (JAL) requests that we 

revise the NPRM to clarify whether 

accomplishing the actions specified in 

Boeing Alert Service Bulletin 747– 

28A2261, dated February 19, 2009, 

terminates the requirements of AD 97– 

26–07, Amendment 39–10250 (62 FR 

65352, December 12, 1997). JAL states 

that AD 97–26–07 presently requires 

repetitive inspections of the Number 1 

and Number 4 main fuel tank boost 

pump wiring (which runs through the 

inboard fuel tanks) per Boeing Service 

Bulletin 747–28A2204. JAL asserts that 

the currently required inspection makes 

sure the wiring is not damaged. JAL also 

asserts that, after operators do the 

proposed modification, the GFI relays 

will monitor the electrical faults and 

remove the power from the fuel pump 

immediately to minimize the risk of 

ignition when wires become damaged. 

JAL states that clarifying the NPRM to 

identify Boeing Alert Service Bulletin 

747–28A2261 as terminating action for 

AD 97–26–07 would save operators 

additional work. 

The FAA acknowledges that both AD 

97–26–07 and this AD relate to potential 

electrical system faults in the fuel 

system. However, the FAA does not 

agree that this AD provides terminating 

action for the actions specified in AD 

97–26–07. The Boeing GFI design 

addresses section 25.981(a)(3) of the 

Federal Aviation Regulations (14 CFR 

25.981(a)(3)) single failure requirement 

only. However the probability of the GFI 

having a latent failure condition, which 

would prevent it from detecting a fault 

current and removing power from the 

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Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 37999 

fuel pump, is not shown to be extremely 

remote. The GFI does not have the 

ability to verify that fault protection is 

operational prior to application of 

power to the pump. Potential latent 

failures in the GFI function will be 

detected via a manual BIT test, which 

will be performed by operators at 

minimum 4,000 flight-hour 

maintenance intervals. We have made 

no change to the AD in this regard. 

Request To Revise Description in the 

Relevant Service Information Section 

The Boeing Company (Boeing) 

requests that we revise the Relevant 

Service Information section of the 

NPRM to specify that the replacement 

given in Boeing Alert Service Bulletin 

747–28A2261, dated February 19, 2009, 

‘‘. . . also includes reworking certain 

wiring and doing an operational test of 

the main tank fuel boost pumps, the 

main tank jettison pumps (if applicable) 

and the center tank scavenge pump (if 

installed), and new relays.’’ Boeing 

states that the wording in the NPRM 

specifies conducting only the main tank 

boost pumps and relay operational tests, 

while Boeing Alert Service Bulletin 

747–28A2261, dated February 19, 2009, 

specifies operational checks of the main 

tank fuel boost pumps, the main tank 

jettison pumps, and the center tank fuel 

scavenge pump, as well as tests of the 

GFI relays, following procedures for 

replacing the relays, and making 

relevant wiring changes. 

We partially agree with Boeing. For 

the reasons provided by Boeing, we do 

agree that the suggested wording 

changes to the description of Boeing 

Alert Service Bulletin 747–28A2261, 

dated February 19, 2009, are more 

accurate. However, we do not agree to 

revise this final rule in this regard. 

Normally, the Relevant Service 

Information section of the NPRM is not 

restated in the final rule, unless service 

information that was not described in 

the NPRM is being added in the final 

rule (e.g., new revisions of a document). 

In this case, the Relevant Service 

Information section does appear in this 

final rule to describe a new revision of 

an MPD document being added to this 

final rule. Although the Relevant 

Service Information section does appear 

in this final rule, the description of 

Boeing Alert Service Bulletin 747– 

28A2261, dated February 19, 2009, is 

not restated in that section. We have 

made no change to the final rule in this 

regard. 

Request To Remove Proposed 

Requirement to Incorporate AWLs 

All Nippon Airways (ANA) requests 

that we revise the NPRM to remove 

paragraph (h)(1), which proposed to 

require incorporating AWLs 28–AWL– 

28 and 28–AWL–29 into the 

maintenance program. ANA asserts that 

paragraph (g)(3) of AD 2008–10–06, 

Amendment 39–15512 (73 FR 25990, 

May 8, 2008), already requires 

incorporation of AWLs 28–AWL–24 

through 28–AWL–29. ANA believes that 

the proposed requirement is duplicating 

an existing requirement. 

We do not agree to remove paragraph 

(h)(1) of this AD. We acknowledge that 

paragraph (g)(3) of AD 2008–10–06 does 

specify revising the maintenance 

program to incorporate AWLs 28–AWL– 

24 through 28–AWL–29—as an option. 

AD 2008–10–06 does not require 

incorporation of AWLs 28–AWL–24 

through 28–AWL–29. Therefore, this AD 

does not duplicate a requirement and 

there is no reason to remove the 

requirement from this AD. However, we 

have revised paragraph (h)(1) of this AD 

to clarify that revising the maintenance 

program to include AWLs 28–AWL–28 

and 28–AWL–29 in accordance with 

paragraph (g)(3) of AD 2008–10–06, 

Amendment 39–15512 (73 FR 25990, 

May 8, 2008) ; or AD 2008–10–06 R1, 

Amendment 39–16160 (75 FR 906, 

January 7, 2010); is acceptable for 

compliance with the corresponding 

requirements specified in paragraph 

(h)(1) of this AD. 

Request To Allow Later Revisions of 

Maintenance Planning Data (MPD) 

Document 

United Airlines states that it concurs 

with the contents of the NPRM, but 

requests that we revise paragraph (h)(1) 

of the NPRM to allow use of later 

revisions of Section 9 of the Boeing 

747–400 MPD Document, Document 

D621U400–9, Revision April 2008. 

United Airlines did not provide 

justification for this request. 

We understand United Airlines’ 

request and operator’s desire to have 

some flexibility in AD compliance 

actions. However, we cannot allow use 

of later revisions of Section 9 of the 

Boeing 747–400 MPD Document, 

Document D621U400–9. We cannot use 

the phrase, ‘‘or later FAA-approved 

revisions,’’ in an AD when referring to 

the service document because doing so 

violates Office of the Federal Register 

(OFR) regulations for approval of 

materials ‘‘incorporated by reference’’ in 

rules. In general terms, we are required 

by these OFR regulations to either 

publish the service document contents 

as part of the actual AD language; or 

submit the service document to the OFR 

for approval as ‘‘referenced’’ material, in 

which case we may only refer to such 

material in the text of an AD. The AD 

may refer to the service document only 

if the OFR approved it for 

‘‘incorporation by reference.’’ To allow 

operators to use later revisions of the 

referenced document (issued after 

publication of the AD), either we must 

revise the AD to reference specific later 

revisions, or operators must request 

approval to use later revisions as an 

alternative method of compliance with 

this AD under the provisions of 

paragraph (k) of this AD. However, as 

explained previously, we have revised 

this final rule to refer to Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS— 

FUEL SYSTEMS,’’ of Boeing 747–400 

MPD Document, Document D621U400– 

9, Section 9, Revision December 2009. 

Explanation of Additional Changes 

Made to this AD 

We have revised paragraph (h)(2) of 

this AD to clarify that revising the 

maintenance program to include AWL 

28–AWL–23 in accordance with 

paragraph (g) of AD 2008–10–07, 

Amendment 39–15513 (73 FR 25977, 

May 8, 2008); or AD 2008–10–07 R1, 

Amendment 39–16070 (74 FR 56098, 

October 30, 2009); is acceptable for 

compliance with the corresponding 

requirements specified in paragraph 

(h)(2) of this AD. 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

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 changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 258 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this AD. 

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38000 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 

TABLE—ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement ............. 1 10 to 14 ....... $85 1 $16,800 to $36,200 1 $17,650 to $37,390 258 1 $4,553,700 to 

$9,646,620. 

Revision of Airworthiness Limitations 

section.

1 ..................... 85 None ........................ 85 ............................. 258 $21,930. 

1 Depending on airplane configuration. 

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), and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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 AD: 

2010–13–12 The Boeing Company: 

Amendment 39–16343. Docket No. 

FAA–2009–0906; Directorate Identifier 

2009–NM–075–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective August 5, 2010. 

Affected ADs 

(b) None. 

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 Alert Service Bulletin 747–28A2261, 

dated February 19, 2009. 

Note 1: This AD requires a revision to a 

certain operator maintenance document to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 43.16 

and 91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these limitations, the 

operator may not be able to accomplish the 

actions described in the revisions. In this 

situation, to comply with 14 CFR 43.16 and 

91.403(c), the operator must request approval 

for an alternative method of compliance 

according to paragraph (k) 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 damage to the fuel pumps 

caused by electrical arcing that could 

introduce an ignition source in the fuel tank 

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. 

Replacement 

(g) Within 60 months after the effective 

date of this AD: Replace the power control 

relays for the main tank fuel boost pumps 

and jettison pumps, and the center tank 

scavenge pump, as applicable, with new 

relays having a ground fault interrupt feature, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–28A2261, dated February 19, 2009. 

Maintenance Program Revision 

(h) Concurrently with the actions required 

by paragraph (g) of this AD: Revise the 

maintenance program by incorporating the 

applicable information in paragraphs (h)(1) 

and (h)(2) of this AD. The inspection interval 

for airworthiness limitations (AWLs) 28– 

AWL–23, 28–AWL–28, and 28–AWL–29 

starts on the date the replacement required 

by paragraph (g) of this AD is done. 

(1) For Model 747–400, 747–400D, and 

747–400F series airplanes: Incorporate new 

airworthiness limitations 28–AWL–28 and 

28–AWL–29 of Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS—FUEL 

SYSTEMS,’’ of Boeing 747–400 Maintenance 

Planning Data (MPD) Document, Document 

D621U400–9, Section 9, Revision December 

2009. (These AWLs were first introduced in 

Revision October 2007 of the MPD 

document.) Incorporating AWLs 28–AWL–28 

and 28–AWL–29 in accordance with 

paragraph (g)(3) of AD 2008–10–06, 

Amendment 39–15512; or AD 2008–10–06 

R1, Amendment 39–16160; is acceptable for 

compliance with the corresponding 

requirements specified in this paragraph. 

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

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

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

Incorporate new AWL 28–AWL–23 of 

Subsection D, ‘‘AIRWORTHINESS 

LIMITATIONS—SYSTEMS,’’ of Boeing 747– 

100/200/300/SP Airworthiness Limitations 

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Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Rules and Regulations 38001 

(AWLs) and Certification Maintenance 

Requirements (CMRs), Document D6–13747– 

CMR, Revision March 2008. (This AWL was 

first introduced in Revision September 2007 

of the AWLs/CMRs document.) Incorporating 

AWL 28–AWL–23 in accordance with 

paragraph (g) of AD 2008–10–07, 

Amendment 39–15513; or AD 2008–10–07 

R1, Amendment 39–16070; is acceptable for 

compliance with the corresponding 

requirements specified in this paragraph. 

No Alternative Inspection or Inspection 

Intervals 

(i) After accomplishing the actions 

required by paragraph (h) of this AD, no 

alternative inspections or inspection 

intervals may be used, unless the inspections 

or intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

Credit for Actions Done Using Previous 

Service Information 

(j) Incorporating new AWLs 28–AWL–28 

and 28–AWL–29 of Subsection D, 

‘‘AIRWORTHINESS LIMITATIONS—FUEL 

SYSTEMS,’’ of Boeing 747–400 Maintenance 

Planning Data (MPD) Document, Document 

D621U400–9, Section 9, Revision April 2008; 

or Revision March 2009; before the effective 

date of this AD is acceptable for compliance 

with the requirements of paragraph (h)(1) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to Attn: 

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. Information may be e-mailed 

to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(l) You must use the service information 

contained in Table 1 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Alert Service Bulletin 747-28A2261 .................................................................................. Original ....................... February 19, 2009 

Subsection D, ‘‘AIRWORTHINESS LIMITATIONS—SYSTEMS,’’ of Boeing 747-100/200/300/ 

SP Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), 

Document D6-13747–CMR.

March 2008 ................. March 2008 

Subsection D, ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEMS,’’ of Section 9 of the 

Boeing 747-400 Maintenance Planning Data (MPD) Document, Document D621U400–9.

December 2009 .......... December 2009 

(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 June 10, 

2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–15651 Filed 6–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0981; Directorate 

Identifier 2008–NM–073–AD; Amendment 

39–16352; AD 2010–14–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747 

airplanes. That AD currently requires 

repetitive inspections of the body 

station (BS) 2598 bulkhead, and 

corrective actions if necessary. That AD 

also currently requires a terminating 

modification for certain repetitive 

inspections and a post-modification 

inspection of the modified area. This 

new AD continues to require those 

actions using revised service 

information. For certain airplanes, this 

AD requires new repetitive inspections, 

an interim modification, and postinterim modification inspections. For 

certain airplanes, this AD requires 

replacing any previously repaired aft 

inner chord and reinstalling the 

terminating modification. For airplanes 

that are converted to the Model 747–400 

large cargo freighter (LCF) configuration, 

this new AD reduces the threshold and 

repeat intervals of certain postmodification inspections. For all 

airplanes, this new AD also requires 

certain inspections of the upper aft 

outer chords and diagonal brace 

attachment fittings, flanges, and rods to 

continue after the terminating 

modification. This AD results from 

reports of cracked aft inner chords on 

airplanes after certain requirements of 

the existing AD were done. We are 

issuing this AD to prevent fatigue 

cracking of the BS 2598 bulkhead 

structure, which could result in 

inability of the structure to carry 

horizontal stabilizer flight loads, and 

loss of controllability of the airplane. 

DATES: This AD becomes effective 

August 5, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 5, 2010. 

On April 13, 2006 (71 FR 12125, 

March 9, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in the AD. 

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