31462 Federal Register / Vol. 76, No. 105 / Wednesday, June 1, 2011 / Rules and Regulations 

(OPERATIONS) LIMITED, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; e-mail 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) 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. 

(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 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 May 13, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–12585 Filed 5–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1044; Directorate 

Identifier 2010–NM–033–AD; Amendment 

39–16704; AD 2011–11–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–10–10, DC–10– 

10F, DC–10–15, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, DC– 

10–40F; Model MD–10–10F, MD–10– 

30F, MD–11, and MD–11F Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires an inspection to 

determine if a certain fuel pump 

housing electrical connector is installed. 

The existing AD also requires a revision 

to the FAA-approved airplane flight 

manual (AFM) to advise the flightcrew 

of the appropriate procedures for 

disabling certain fuel pump electrical 

circuits following failure of a fuel pump 

housing electrical connector if 

applicable. The existing AD also 

requires the deactivation of certain fuel 

tanks or fuel pumps and the installation 

of placards if applicable. The existing 

AD allows the optional replacement of 

the fuel pump housing electrical 

connectors with new, improved parts, 

which would terminate the AFM 

revisions, deactivation of certain fuel 

tanks and fuel pumps, and placard 

installation. This new AD instead 

requires replacing the fuel pump 

housing electrical connector assembly 

with a new part and doing repetitive 

inspections for continuity, resistance, 

and insulation resistance, and doing 

corrective actions if necessary. This AD 

was prompted by reports of failures of 

a certain fuel pump housing electrical 

connector. We are issuing this AD to 

detect and correct insulation resistance 

degradation and arcing in the potted 

backside of the electrical connector 

assembly of the fuel boost/transfer 

pump housing, which could 

compromise its performance and cause 

an ignition source in the fuel tank, 

resulting in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD is effective July 6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 6, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.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: 

Philip Kush, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5263; fax: 562–627– 

5210.; e-mail: philip.kush@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

directive (AD) 2007–15–05, amendment 

39–15134 (72 FR 40216, July 24, 2007). 

That AD applies to the specified 

products. The NPRM published in the 

Federal Register on November 5, 2010 

(75 FR 68246). That NPRM proposed to 

require replacing the fuel pump housing 

electrical assembly with a new part and 

doing repetitive inspections for 

continuity, resistance, and insulation 

resistance, and doing 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. 

Request for Addition of Part Number 

FedEx requested that we add, in the 

header above the Summary and 

paragraphs (c), (e), and (f) of the 

proposed AD, the part number of the 

fuel pump housing electrical connector 

assembly requiring replacement. FedEx 

stated that the change will clarify the 

AD and avoid unnecessary work and 

cost to the operators. 

We partially agree with the 

commenter. We disagree with adding 

the part number of the fuel pump 

housing electrical connector assembly 

requiring replacement to the header 

information, paragraph (c), and 

paragraph (f) of this AD because the 

affected part could be rotated onto any 

of the airplanes listed in the 

applicability. However, we agree that 

clarification of paragraph (h) of this AD 

(referred to as paragraph (g) in the 

NPRM) is needed. In order to comply 

with this AD, for all airplanes in the 

applicability it must be determined if 

the fuel pump housing electrical 

connector assembly having part number 

(P/N) 60–84355–1 is installed. We have 

added paragraph (g) to specify the 

inspection to determine the part 

number. We have also added a reference 

of P/N 60–84355–1 to paragraph (h) of 

this AD for clarification. In addition, we 

have added a reference of P/N 60– 

84355–1 to paragraph (e) of this AD for 

clarification. 


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Federal Register / Vol. 76, No. 105 / Wednesday, June 1, 2011 / Rules and Regulations 31463 

Clarification of Paragraph (i) of This 

AD 

We have revised paragraph (i) of this 

AD by replacing the phrase, ‘‘replacing 

the fuel pump electrical connector 

assembly as required by paragraph (g) of 

this AD’’ with the phrase, ‘‘installing the 

fuel pump housing electrical connector 

assembly having P/N 60–84351, in 

accordance with Boeing Alert Service 

Bulletin DC10–28A261 or Boeing Alert 

Service Bulletin MD11–28A143,’’ to 

clarify that P/N 60–84351 must be 

repetitively inspected after installation. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 affects 281 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection ............... Between 20 and 36 

per inspection 

cycle.

$85 $0 ........................... Between $1,700 

and $3,060 per 

inspection cycle.

281 Between $477,700 

and $859,860 per 

inspection cycle. 

Replacement .......... Up to 44 ................. 85 Up to $4,478 .......... Up to $8,218 .......... 281 Up to $2,309,258. 

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 

We have determined that 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 

removing airworthiness directive (AD) 

2007–15–05, Amendment 39–15134 (72 

FR 40216, July 24, 2007), and adding the 

following new AD: 

2011–11–05 The Boeing Company: 

Amendment 39–16704; Docket No. 

FAA–2010–1044; Directorate Identifier 

2010–NM–033–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective July 6, 2011. 

Affected ADs 

(b) This AD supersedes AD 2007–15–05, 

Amendment 39–15134. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model DC–10–10, DC–10–10F, DC– 

10–15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, DC–10–40F, MD–10– 

10F, MD–10–30F, MD–11, and MD–11F 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from reports of failures 

of the fuel pump housing electrical connector 

having P/N 60–84355–1. The Federal 

Aviation Administration is issuing this AD to 

detect and correct insulation resistance 

degradation and arcing in the potted backside 

of the electrical connector assembly of the 

fuel boost/transfer pump housing, which 

could compromise its performance and cause 

an ignition source in the fuel tank, resulting 

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. 

Inspection and Change 

(g) For all airplanes: Within 10 months 

after the effective date of this AD, do an 

inspection of the fuel pump housing 

electrical connector to determine if part 

number (P/N) 60–84355–1 is installed. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number of the fuel pump housing 

electrical connector can be conclusively 

determined from that review. 

(h) If, during the inspection required by 

paragraph (g) of this AD, any airplane is 

determined to have fuel pump housing 

electrical connector assembly having P/N 60– 

84355–1: Within 10 months after the effective 


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31464 Federal Register / Vol. 76, No. 105 / Wednesday, June 1, 2011 / Rules and Regulations 

date of this AD, do the actions in paragraph 

(h)(1) or (h)(2) of this AD, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin DC10–28A261, dated 

December 1, 2009; or Boeing Alert Service 

Bulletin MD11–28A143, dated December 2, 

2009; as applicable. 

(1) Replace the fuel pump housing 

electrical connector assembly having P/N 60– 

84355–1 with new P/N 60–84351; or 

(2) Do the actions required by paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD. 

(i) Using a digital multi-meter, do a 

continuity, resistance, and insulation 

resistance inspection from the terminal strip 

through the fuel boost/transfer pump; and all 

applicable corrective actions specified in 

Boeing Alert Service Bulletin DC10–28A261, 

dated December 1, 2009; or Boeing Alert 

Service Bulletin MD11–28A143, dated 

December 2, 2009; as applicable. Do all 

applicable corrective actions before further 

flight. 

(ii) Within 12 months after accomplishing 

the inspection required by paragraph (h)(2)(i) 

of this AD: Replace the fuel pump housing 

electrical connector assembly having P/N 60– 

84355–1 with a new fuel pump housing 

electrical connector assembly having P/N 60– 

84351. 

(i) Before further flight after installing the 

new fuel pump housing electrical connector 

assembly, insert the applicable interim 

operating procedure regarding abnormal 

operations for failure of the fuel pump 

housing electrical connector into the 

Procedures section of the applicable Boeing 

airplane flight manual, in accordance with 

the applicable service information identified 

in Table 1 of this AD. 

TABLE 1—SERVICE INFORMATION

Bulletin— Date— To the— 

Boeing DC–10 Operations Bulletin 2–001B ................................................................ January 25, 2010 ...... Boeing DC–10 Flight Crew Operating Manual. 

Boeing MD–10 Flight Crew Operations Manual Advisory Bulletin 2–01B .................. January 25, 2010 ...... Boeing MD–10 Flight Crew Operations Manual. 

Boeing MD–11 Flight Crew Operations Manual Advisory Bulletin 2–05C .................. January 25, 2010 ...... Boeing MD–11 Flight Crew Operations Manual. 

Repetitive Inspections for P/N 60–84351 

(j) Within 18 months after installing the 

fuel pump housing electrical connector 

assembly having P/N 60–84351, in 

accordance with Boeing Alert Service 

Bulletin DC10–28A261 or Boeing Alert 

Service Bulletin MD11–28A143: Do a 

continuity, resistance, and insulation 

resistance inspection from the terminal strip 

through the fuel boost/transfer pump, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC10–28A261, dated December 1, 2009; or 

Boeing Alert Service Bulletin MD11–28A143, 

dated December 2, 2009; as applicable. Do all 

applicable corrective actions before further 

flight in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC10–28A261, dated 

December 1, 2009; or Boeing Alert Service 

Bulletin MD11–28A143, dated December 2, 

2009; as applicable. Repeat the inspections 

thereafter at intervals not to exceed 18 

months. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles 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 ACO, send it to ATTN: Philip Kush, 

Aerospace Engineer, Propulsion Branch, 

ANM–140L, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; phone: 562–627–5263; fax: 562–627– 

5210; e-mail: philip.kush@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. 

Material Incorporated by Reference 

(l) You must use the service information 

contained in table 2 of this AD, as applicable, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Document Date 

Boeing Alert Service Bulletin DC10-28A261 ........................................................................................................................... December 1, 2009. 

Boeing Alert Service Bulletin MD11-28A143 ........................................................................................................................... December 2, 2009. 

Boeing DC–10 Operations Bulletin 2-001B to the Boeing DC–10 Flight Crew Operating Manual ........................................ January 25, 2010. 

Boeing MD–10 Flight Crew Operations Manual Advisory Bulletin 2–01B to the Boeing MD–10 Flight Crew Operations 

Manual.

January 25, 2010. 

Boeing MD–11 Flight Crew Operations Manual Advisory Bulletin 2–05C to the Boeing MD–11 Flight Crew Operations 

Manual.

January 25, 2010. 

(The document number of Boeing DC–10 

Operations Bulletin 2–001B is specified only 

on the first page of the document.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in table 2 

of this AD 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, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone: 206–544–5000, extension 2; 

fax: 206–766–5683; e-mail: 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(3) 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. 

(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 May 12, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–12592 Filed 5–31–11; 8:45 am] 

BILLING CODE 4910–13–P 


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