40216 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 

Because of rapid improvements in 

airplane technology, the applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for these design features. These special 

conditions for the 787 contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

On January 15, 2002, the FAA issued 

14 CFR 25.795(a) (Amendment 25–106), 

which specifies that the flightdeck door 

of a transport airplane be designed to 

resist forcible intrusion by unauthorized 

persons and penetration by small arms 

fire and fragmentation devices. At the 

time it was written, the regulation was 

limited to the flightdeck door to 

expedite a rapid retrofit of the existing 

airplanes required by operating rules to 

have a flightdeck door. 

In addition to a reinforced flightdeck 

door, the 787 will have a flightdeck 

bulkhead which is reinforced to resist 

intrusion and ballistic penetration. The 

regulations do not adequately address 

the certification requirements for such a 

bulkhead, and appropriate certification 

standards are necessary. These special 

conditions require that the reinforced 

flightdeck bulkhead meet the same 

standards as those specified in 

§ 25.795(a) for flightdeck doors. These 

special conditions contain the minimum 

standards that the Administrator 

considers necessary to ensure that safety 

standards are maintained after the 

aircraft enters into service. 

On December 21, 2006, the FAA 

issued a notice of proposed rulemaking 

that proposes amending § 25.795(a) to 

require that a flightdeck bulkhead—and 

any other accessible barrier separating 

the flightcrew compartment from 

occupied areas—also be designed to 

resist intrusion or penetration. The 

methods of compliance described in the 

preamble of that notice and associated 

draft advisory material could be used to 

show compliance with these special 

conditions. For the 787, the reinforced 

bulkhead may be comprised of 

components such as the walls of 

adjacent lavatories, galleys, or crew rest 

areas. Those components are covered by 

these special conditions. 

Discussion of Comments 

Notice of Proposed Special 

Conditions No. 25–07–08–SC for the 

787 was published in the Federal 

Register on April 12, 2007 (72 FR 

18412). One comment was received, 

from Air Line Pilots Association, 

International (ALPA). 

ALPA Comment: ALPA recommended 

that the requirements of these special 

conditions apply to future versions of 

the 787, including possible freighter 

configurations. 

FAA Response: These special 

conditions apply to airplanes that 

incorporate a reinforced bulkhead. They 

are not limited to any particular type of 

operation, nor do they impose 

operational requirements. Thus, if a 

future freighter version did incorporate 

a reinforced bulkhead, these special 

conditions would apply. These special 

conditions are adopted as proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the 787. 

Should Boeing apply at a later date for 

a change to the type certificate to 

include another model on the same type 

certificate incorporating the same novel 

or unusual design features, these special 

conditions would apply to that model as 

well. 

Conclusion 

This action affects only certain novel 

or unusual design features of the 787. It 

is not a rule of general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

■ The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for the Boeing Model 787–8 

airplane. 

In addition to the requirements of 14 

CFR 25.795(a) governing protection of 

the flightdeck door, the following 

special conditions apply. 

The reinforced bulkhead, including 

components that comprise the bulkhead, 

separating the flightcrew compartment from 

occupied areas must be designed to meet the 

following standards: 

It must resist forcible intrusion by 

unauthorized persons and be capable of 

withstanding impacts of 300 Joules (221.3 

foot-pounds) at critical locations on the 

bulkhead as well as a 1113 Newton (250 

pound) constant tensile load on accessible 

handholds. 

It must resist penetration by small arms fire 

and fragmentation devices to a level 

equivalent to level IIIa of the National 

Institute of Justice Standard (NIJ) 0101.04. 

Issued in Renton, Washington, on July 12, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–14333 Filed 7–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28749; Directorate 

Identifier 2007–NM–079–AD; Amendment 

39–15134; AD 2007–15–05] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–10–10 and DC–10–

10F Airplanes, Model DC–10–15 

Airplanes, Model DC–10–30 and DC–

10–30F (KC–10A and KDC–10) 

Airplanes, Model DC–10–40 and DC–

10–40F Airplanes, Model MD–10–10F 

and MD–10–30F Airplanes, and Model 

MD–11 and MD–11F Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

transport category airplanes identified 

above. This AD requires an inspection 

to determine if a certain fuel pump 

housing electrical connector is installed. 

This 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. This 

AD also requires the deactivation of 

certain fuel tanks or fuel pumps and the 

installation of placards if applicable. 

This 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 AD results 

from a report of two failures of the fuel 

pump housing electrical connector. We 

are issuing this AD to prevent continued 

arcing following a short circuit of the 

fuel pump housing electrical connector, 

which could damage the conduit that 

protects the power lead inside the fuel 

tank; this condition could create an 

ignition source inside the fuel tank, 

which, in combination with flammable 

fuel vapors, could result in a fuel tank 


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Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 40217 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

August 8, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 8, 2007. 

On December 5, 2000 (65 FR 69658, 

November 20, 2000), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

We must receive comments on this 

AD by September 24, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room W12–140 on 

the ground floor of the West Building, 

1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Contact Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1–L5A 

(D800–0024), for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Philip C. Kush, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5263; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report indicating 

that the fuel pump housing electrical 

connector, part number (P/N) 60–84355, 

failed on two McDonnell Douglas MD–

11 airplanes. The airplanes had 

accumulated 3,000 and 3,600 flight 

hours since installation of the electrical 

connector in accordance with Boeing 

Alert Service Bulletin MD11–28A113. 

The failures were attributed to arcing 

between the contacts in the potted 

backside of the electrical connector. 

Subsequent x-ray inspections of the 

electrical connectors revealed soldering 

problems with the connector contacts. 

Continued arcing following a short 

circuit of the fuel pump housing 

electrical connector could damage the 

conduit that protects the power lead 

inside the fuel tank. This condition, if 

not corrected, could create an ignition 

source inside the fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

Fuel pump housing electrical 

connector, P/N 60–84355, has also been 

installed on McDonnell Douglas Model 

DC–10–10 and DC–10–10F airplanes, 

Model DC–10–15 airplanes, Model DC–

10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, Model DC–10–40 

and DC–10–40F airplanes, and Model 

MD–10–10F and MD–10–30F airplanes, 

in accordance with Boeing Alert Service 

Bulletin DC10–28A229. Therefore, all of 

these models may be subject to the same 

unsafe condition. 

Other Relevant Rulemaking 

On November 1, 2000, we issued AD 

2000–22–21, amendment 39–11969 (65 

FR 69658, November 20, 2000), for all 

McDonnell Douglas DC–10, MD–10, and 

MD–11 series airplanes. That AD 

requires revising the airplane flight 

manual (AFM) to ensure that the 

flightcrew is advised of appropriate 

procedures for disabling certain fuel 

pump electrical circuits following 

failure of a fuel pump electrical 

connector. For certain airplanes, that 

AD also requires revising the AFM to 

prohibit resetting of tripped fuel pump 

circuit breakers. We approved 

installation of fuel pump housing 

electrical connector, P/N 60–84355, in 

accordance with Boeing Alert Service 

Bulletin DC10–28A229 or MD11–

28A113, as applicable, as an alternative 

method of compliance (AMOC) for AD 

2000–22–21. That AMOC allowed 

removal of certain interim operating 

procedures from the Procedures section 

of the FAA-approved AFM, which is 

required by paragraph (a) of AD 2000–

22–21. This AD reintroduces that 

requirement, since we have determined 

that an unsafe condition exists on 

airplanes equipped with electrical 

connector P/N 60–84355. 

On June 25, 2002, we issued AD 

2002–13–10, amendment 39–12798 (67 

FR 45053, July 8, 2002), for certain 

McDonnell Douglas Model DC–10–10, 

–10F, –15, –30, –30F, –30F (KC–10A 

and KDC–10), –40, and –40F airplanes; 

Model MD–10–10F and –30F airplanes; 

and Model MD–11 and –11F airplanes. 

That AD requires repetitive tests for 

electrical continuity and resistance and 

repetitive inspections to detect 

discrepancies of the fuel boost/transfer 

pump connectors; and corrective 

actions, if necessary. Accomplishing the 

optional replacement of all electrical 

connectors in accordance with 

paragraph (k) or (l) of this AD, as 

applicable, terminates the requirements 

of AD 2002–13–10. 

On April 4, 2003, we issued AD 2003–

07–14, amendment 39–13110 (68 FR 

17544, April 10, 2003), for a certain 

McDonnell Douglas Model DC–10–30 

airplane. That AD requires repetitive 

tests for electrical continuity and 

resistance and repetitive inspections to 

detect discrepancies of the fuel boost/ 

transfer pump connectors; and 

corrective actions, if necessary. 

Accomplishing the optional 

replacement of all electrical connectors 

in accordance with paragraph (k) of this 

AD terminates the requirements of AD 

2003–07–14. 

Relevant Service Information 

We have reviewed the following 

service bulletins: 

• Boeing Alert Service Bulletin 

DC10–28A259, dated March 20, 2007, 

for Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, 

Model DC–10–30 and DC–10–30F (KC–

10A and KDC–10) airplanes, Model DC–

10–40 and DC–10–40F airplanes, and 

Model MD–10–10F and MD–10–30F 

airplanes. 

• Boeing Alert Service Bulletin 

MD11–28A138, Revision 1, dated March 

26, 2007, for Model MD–11 and MD–

11F airplanes. 

Boeing Alert Service Bulletins DC10–

28A259 and MD11–28A138 describe 

procedures for deactivating certain fuel 

tanks or fuel pumps, as applicable. The 

service bulletins also describe 

procedures for installing a placard on or 

adjacent to the flight engineer’s fuel 

control panel or adjacent to display 

units 1 and 6, as applicable. The service 

bulletins also describe procedures for 

replacing fuel pump housing electrical 

connectors, P/N 60–84355, with new, 

improved electrical connectors, P/N 60–

84355–1, and removing the placards 

after installing the new, improved 

electrical connectors. 

We have also reviewed Boeing Flight 

Operations Bulletin DC–10–00–01A, 

MD–11–00–03A, and MD–10–00–02A, 

dated September 20, 2000, for Model 

DC–10–10 and DC–10–10F airplanes, 

Model DC–10–15 airplanes, Model DC–

10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, and Model DC–10–

40 and DC–10–40F airplanes, Model 

MD–11 and MD–11F airplanes, and 

Model MD–10–10F and MD–10–30F 


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airplanes. Boeing Flight Operations 

Bulletin DC–10–00–01A, MD–11–00–

03A, and MD–10–00–02A provides 

instructions for revising the Procedures 

section of the FAA-approved AFM by 

inserting certain Interim Operating 

Procedures (IOPs). The IOPs advise the 

flightcrew of proper procedures for 

disabling certain fuel pump electrical 

circuits following failure of a fuel pump 

housing electrical connector. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to prevent continued arcing 

following a short circuit of the fuel 

pump housing electrical connector, 

which could damage the conduit that 

protects the power lead inside the fuel 

tank; this condition could create an 

ignition source inside the fuel tank, 

which, in combination with flammable 

fuel vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. This AD requires an inspection 

to determine if fuel pump housing 

electrical connector, P/N 60–84355, is 

installed. If that electrical connector is 

installed, this AD requires the following 

additional actions: 

• Revising the Procedures section of 

the FAA-approved 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. 

• Deactivating certain fuel tanks or 

fuel pumps, as applicable. 

• Installing placards on or adjacent to 

the flight engineer’s fuel control panel 

or adjacent to display units 1 and 6, as 

applicable. 

This AD also 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. 

Differences Between the AD and Boeing 

Alert Service Bulletin DC10–28A259 

The Accomplishment Instructions of 

Boeing Alert Service Bulletin DC10–

28A259 is divided into work packages 

for airplanes identified as Groups 1, 2, 

3, 4, and 5. This AD does not require 

any action for Group 5 airplanes. Also, 

this AD does not require accomplishing 

Work Package 2 for Groups 1, 2, and 3 

airplanes and does not require 

accomplishing Work Package 5 for 

Group 4 airplanes; these work packages 

describe procedures for replacing the 

affected electrical connectors on tanks 1, 

2, and 3. 

Differences Between the AD and Boeing 

Alert Service Bulletin MD11–28A138 

The Accomplishment Instructions of 

Boeing Alert Service Bulletin MD11–

28A138 is divided into work packages 

for airplanes identified as Groups 1 and 

2. This AD does not require 

accomplishing Work Package 5 for 

Group 1 airplanes and does not require 

accomplishing Work Package 6 for 

Group 2 airplanes; these work packages 

describe procedures for replacing the 

affected electrical connectors on main 

tanks 1 and 3. 

The compliance tables in paragraph 

1.E. of Boeing Alert Service Bulletin 

MD11–28A138 recommend a 

compliance time of 10 days for 

accomplishing the following actions: (1) 

Work Package 1—Option 1—Part 1—

Tank 2 (Placards Installation) for Group 

1 airplanes, (2) Work Package 1—Option 

1—Part 1—Forward Auxiliary Tank 

(Deactivation) for Group 2 airplanes, 

and (3) Work Package 2—Option 1—Part 

1—Tank 2 (Placards Installation) for 

Group 2 airplanes. This AD, however, 

would require accomplishing those 

actions within 14 days after the effective 

date of this AD. We have coordinated 

this difference with Boeing. 

Clarification of Boeing Alert Service 

Bulletin DC10–28A259 

The compliance table for Group 4 

airplanes in paragraph 1.E. of Boeing 

Alert Service Bulletin DC10–28A259 

identifies 5 work packages, one of 

which is ‘‘Work Package 3—Upper and 

Lower Center Wing Tanks.’’ However, 

the procedures for Work Package 3 are 

described under the headings, ‘‘Work 

Package 1—Option 1—Part 1—Upper 

and Lower Center Wing Fuel Tanks 

(Deactivation)’’ and ‘‘Work Package 1—

Option 1—Part 2 or Option 2—Upper 

and Lower Center Wing Fuel Tank 

(Connector Replacement)’’ in the 

Accomplishment Instructions of the 

service bulletin. In this AD, we have 

referenced the headings for Work 

Package 3 exactly as they appear in the 

Accomplishment Instructions of the 

service bulletin. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

replacement of all affected electrical 

connectors, which will constitute 

terminating action for the AFM 

revisions, deactivation of certain fuel 

tanks and fuel pumps, and placard 

installation required by this AD action. 

However, the planned compliance time 

for the replacement of all affected 

connectors would allow enough time to 

provide notice and opportunity for prior 

public comment on the merits of the 

modification. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–28749; Directorate Identifier 

2007–NM–079–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located on ground 

floor of the West Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


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Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 40219 

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 the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2007–15–05 McDonnell Douglas: 

Amendment 39–15134. Docket No. 

FAA–2007–28749; Directorate Identifier 

2007–NM–079–AD. 

Effective Date 

(a) This AD becomes effective August 8, 

2007. 

Affected ADs 

(b) Accomplishing paragraph (k) or (l) of 

this AD, as applicable, terminates the 

requirements of AD 2002–13–10, amendment 

39–12798, the requirements of AD 2003–07–

14, amendment 39–13110, and the 

requirements of paragraph (a) of AD 2000–

22–21, amendment 39–11969. 

Applicability 

(c) This AD applies to all McDonnell 

Douglas Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, Model 

DC–10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, Model DC–10–40 and 

DC–10–40F airplanes, Model MD–10–10F 

and MD–10–30F airplanes, and Model MD–

11 and MD–11F airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report of two 

failures of the fuel pump housing electrical 

connectors. We are issuing this AD to prevent 

continued arcing following a short circuit of 

the fuel pump housing electrical connector, 

which could damage the conduit that 

protects the power lead inside the fuel tank; 

this condition could create an ignition source 

inside the fuel tank, which, in combination 

with flammable fuel vapors, could result in 

a fuel tank explosion and consequent loss of 

the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Service Bulletin References 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the following service 

bulletins, as applicable: 

(1) For Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, Model 

DC–10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, Model DC–10–40 and 

DC–10–40F airplanes, and Model MD–10–

10F and MD–10–30F airplanes: Boeing Alert 

Service Bulletin DC10–28A259, dated March 

20, 2007; and 

(2) For Model MD–11 and MD–11F 

airplanes: Boeing Alert Service Bulletin 

MD11–28A138, Revision 1, dated March 26, 

2007. 

Inspection To Determine Part Number (P/N) 

(g) For all airplanes: Within 14 days after 

the effective date of this AD, inspect the fuel 

pump housing electrical connector to 

determine if P/N 60–84355 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. If P/N 60–

84355 is installed, accomplish the applicable 

actions specified in paragraphs (h), (i), and (j) 

of this AD. 

Airplane Flight Manual (AFM) Revision of 

Procedures Section 

(h) For all airplanes equipped with fuel 

pump housing electrical connector P/N 60–

84355: Within 14 days after the effective date 

of this AD, insert the applicable Interim 

Operating Procedures regarding abnormal 

operations for failure of the fuel pump 

housing electrical connector into the 

Procedures section of the FAA-approved 

AFM, in accordance with Boeing Flight 

Operations Bulletin DC–10–00–01A, MD–11–

00–03A, and MD–10–00–02A, dated 

September 20, 2000. Accomplishing the 

applicable actions specified in paragraph (k) 

or (l) of this AD, as applicable, terminates the 

requirements of this paragraph and the 

corresponding requirements specified in 

paragraph (i) or (j) of this AD, as applicable. 

Deactivation of Fuel Tanks and Placard 

Installation for DC–10/MD–10 Airplanes 

(i) For Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, Model 

DC–10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, Model DC–10–40 and 

DC–10–40F airplanes, and Model MD–10–

10F and MD–10–30F airplanes identified in 

the applicable service bulletin as Group 1, 2, 

3, or 4 airplanes and equipped with fuel 

pump housing electrical connector P/N 60–

84355: At the applicable time specified in 

Table 1 of this AD, deactivate the applicable 

fuel tank(s) and applicable fuel pumps and 

install a placard at the applicable location 

specified in Table 1 of this AD, in accordance 

with the applicable work package of the 

Accomplishment Instructions of the 

applicable service bulletin. For the placard 

installation required by this paragraph, 

alternative placard location and wording may 

be used if approved by an appropriate FAA 

Principal Operations Inspector. 

Accomplishing the applicable actions 

specified in paragraph (k) of this AD 

terminates the corresponding requirements of 

this paragraph and the AFM revision 

required by paragraph (h) of this AD. 


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TABLE 1.—REQUIREMENTS FOR MODEL DC–10 AND MODEL MD–10 AIRPLANES

Airplanes Compliance time Deactivated fuel tank(s) or 

fuel pump Placard location Work package 

Group 1 ............................. Within 90 days after the 

effective date of this AD.

Auxiliary fuel tank .............. On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 1—Part 1— 

Option 1—Aux Fuel 

Tank (Deactivation). 

Group 2: Model DC–10–10 

and DC–10–10F airplanes, Model DC–10– 

15 airplanes, Model DC– 

10–30 and DC–10–30F 

(KC–10A and KDC–10) 

airplanes, and Model 

DC–10–40 and DC–10– 

40F airplanes.

Within 90 days after the 

effective date of this AD.

Upper and lower auxiliary 

fuel tanks.

On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 1—Option 

1—Part 1—Upper and 

Lower Aux Fuel Tanks 

(Deactivation) (DC–10/ 

KDC–10). 

Group 2: Model MD–10– 

10F and MD–10–30F 

airplanes.

Within 90 days after the 

effective date of this AD.

Upper and lower auxiliary 

fuel tanks.

Adjacent to display units 1 

and 6.

Work Package 1—Option 

1—Part 1—Upper and 

Lower Aux Fuel Tanks 

(Deactivation) (MD–10). 

Group 3 ............................. Within 90 days after the 

effective date of this AD.

Upper, lower, and aft fuel 

tanks.

On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 1—Option 

1—Part 1—Upper, 

Lower and Aft Aux Fuel 

Tanks (Deactivation). 

Group 4 ............................. Within 14 days after the 

effective date of this AD.

Fuel pump for aft fuselage 

tank.

On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 1—Option 

1—Part 1—Aft Fuselage 

Fuel Pump (Deactivation). 

Within 14 days after the 

effective date of this AD.

Fuel pumps for wing tip 

tanks 1 and 3.

On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 2—Option 

1—Part 1—Wing Tip 

Tank 1 and 3 Pumps 

(Deactivation). 

Within 90 days after the 

effective date of this AD.

Upper and lower center 

wing tanks.

On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 1—Option 

1—Part 1—Upper and 

Lower Center Wing Fuel 

Tanks (Deactivation). 

Within 90 days after the 

effective date of this AD.

Fuel pump for forward fuselage tank.On or adjacent to the flight 

engineer’s fuel control 

panel.

Work Package 4—Option 

1—Part 1—Fwd Fuselage Fuel Pump (Deactivation). 

Deactivation of Fuel Tanks and Placard 

Installation for MD–11/–11F Airplanes 

(j) For Model MD–11 and MD–11F 

airplanes identified in the applicable service 

bulletin as Group 1 and 2 airplanes and 

equipped with fuel pump housing electrical 

connector P/N 60–84355: At the applicable 

time specified in Table 2 of this AD, 

deactivate the applicable fuel tanks specified 

in Table 2 of this AD and install a placard 

adjacent to display units 1 and 6, in 

accordance with the applicable work package 

of the Accomplishment Instructions of the 

applicable service bulletin. For the placard 

installation required by this paragraph, 

alternative placard location and wording may 

be used if approved by an appropriate FAA 

Principal Operations Inspector. 

Accomplishing the applicable actions 

specified in paragraph (l) of this AD 

terminates the corresponding requirements of 

this paragraph and the AFM revision 

required by paragraph (h) of this AD. 

TABLE 2.—REQUIREMENTS FOR MODEL MD–11 AND MD–11F AIRPLANES

Airplanes Compliance time Deactivated fuel tanks Work package 

Group 1 .......................................... Within 14 days after the effective 

date of this AD.

Not applicable ............................... Work Package 1—Option 1—Part 

1—Tank 2 (Placards Installation). 

Within 90 days after the effective 

date of this AD.

Tail tank ........................................ Work Package 2—Option 1—Part 

1—Tail Tank (Deactivation). 

Within 90 days after the effective 

date of this AD.

Not applicable ............................... Work Package 3—Option 1—Part 

1—Upper Auxiliary Tank (Placards Installation). 

Within 90 days after the effective 

date of this AD.

Lower auxiliary tank ...................... Work Package 4—Option 1—Part 

1—Lower Auxiliary Tank (Deactivation). 

Group 2 .......................................... Within 14 days after the effective 

date of this AD.

Forward auxiliary tank .................. Work Package 1—Option 1—Part 

1—Forward Auxiliary Tank (Deactivation). 

Within 14 days after the effective 

date of this AD.

Not applicable ............................... Work Package 2—Option 1—Part 

1—Tank 2 (Placards Installation). 

Within 90 days after the effective 

date of this AD.

Tail tank ........................................ Work Package 3—Option 1—Part 

1—Tail Tank (Deactivation). 


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TABLE 2.—REQUIREMENTS FOR MODEL MD–11 AND MD–11F AIRPLANES—Continued 

Airplanes Compliance time Deactivated fuel tanks Work package 

Within 90 days after the effective 

date of this AD.

Not applicable ............................... Work Package 4—Option 1—Part 

1—Upper Auxiliary Tank (Placards Installation). 

Within 90 days after the effective 

date of this AD.

Lower auxiliary tank ...................... Work Package 5—Option 1—Part 

1—Lower Auxiliary Tank (Deactivation). 

Optional Terminating Action for DC–10/MD–

10 Airplanes 

(k) For Model DC–10–10 and DC–10–10F 

airplanes, Model DC–10–15 airplanes, Model 

DC–10–30 and DC–10–30F (KC–10A and 

KDC–10) airplanes, Model DC–10–40 and 

DC–10–40F airplanes, and Model MD–10–

10F and MD–10–30F airplanes identified in 

the applicable service bulletin as Group 1, 2, 

3, or 4 airplanes and equipped with fuel 

pump housing electrical connector P/N 60–

84355: As an option, replace all fuel pump 

housing electrical connectors, P/N 60–84355, 

with new, improved electrical connectors, P/ 

N 60–84355–1, and remove the applicable 

placards, in accordance with the applicable 

work package(s) of the Accomplishment 

Instructions of the applicable service bulletin 

as specified in Table 3 of this AD. 

Accomplishing the applicable actions 

specified in this paragraph terminates the 

corresponding requirements of paragraph (i) 

of this AD and the AFM revision required by 

paragraph (h) of this AD. 

TABLE 3.—OPTIONAL WORK PACKAGES FOR MODEL DC–10 AND MODEL MD–10 AIRPLANES

Airplanes Work package 

Group 1 ..................................................................................................... Work Package 1—Option 1—Part 2 or Option 2—Aux Fuel Tank (Connector Replacement). 

Group 2: Model DC–10–10 and DC–10–10F airplanes, Model DC–10–

15 airplanes, Model DC–10–30 and DC–10–30F (KC–10A and KDC–

10) airplanes, and Model DC–10–40 and DC–10–40F airplanes.

Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower 

Aux Fuel Tanks (DC–10/KDC–10) (Connector Replacement). 

Group 2: Model MD–10–10F and MD–10–30F airplanes ........................ Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower 

Aux Fuel Tanks (MD–10) (Connector Replacement). 

Group 3 ..................................................................................................... Work Package 1—Option 1—Part 2 or Option 2—Upper, Lower and Aft 

Aux Fuel Tanks (Connector Replacement). 

Group 4 ..................................................................................................... Work Package 1—Option 1—Part 2 or Option 2—Aft Fuselage Fuel 

Pump (Connector Replacement). 

Work Package 2—Option 1—Part 2 or Option 2—Wing Tip Tanks 1 

and 3 (Connector Replacement). 

Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower 

Center Wing Fuel Tanks (Connector Replacement). 

Work Package 4—Option 1—Part 2 or Option 2—Fwd Fuselage Fuel 

Pump (Connector Replacement). 

Optional Terminating Action for MD–11/–

11F Airplanes 

(l) For Model MD–11 and MD–11F 

airplanes identified in the applicable service 

bulletin as Group 1 and 2 airplanes and 

equipped with fuel pump housing electrical 

connector P/N 60–84355: As an option, 

replace all fuel pump housing electrical 

connectors, P/N 60–84355, with new, 

improved electrical connectors, P/N 60–

84355–1, and remove the applicable 

placards, in accordance with the applicable 

work packages of the Accomplishment 

Instructions of the applicable service bulletin 

as specified in Table 4 of this AD. 

Accomplishing the applicable actions 

specified in this paragraph terminates the 

corresponding requirements of paragraph (j) 

of this AD and the AFM revision required by 

paragraph (h) of this AD. 

TABLE 4.—OPTIONAL WORK PACKAGES FOR MODEL MD–11 AND MD–11F AIRPLANES

Airplanes Work package 

Group 1 ................................ Work Package 1—Option 1—Part 2 or Option 2—Tank 2 (Connector Replacement). 

Work Package 2—Option 1—Part 2 or Option 2—Tail Tank (Connector Replacement). 

Work Package 3—Option 1—Part 2 or Option 2—Upper Auxiliary Tank (Connector Replacement). 

Work Package 4—Option 1—Part 2 or Option 2—Lower Auxiliary Tank (Connector Replacement). 

Group 2 ................................ Work Package 1—Option 1—Part 2 or Option 2—Forward Auxiliary Tank (Connector Replacement). 

Work Package 2—Option 1 Part 2 or Option 2—Tank 2 (Connector Replacement). 

Work Package 3—Option 1—Part 2 or Option 2—Tail Tank (Connector Replacement). 

Work Package 4—Option 1—Part 2 or Option 2—Upper Auxiliary Tank (Connector Replacement). 

Work Package 5—Option 1—Part 2 or Option 2—Lower Auxiliary Tank (Connector Replacement). 

Parts Installation 

(m) For all airplanes: As of the effective 

date of this AD, no person may install a fuel 

pump housing electrical connector, P/N 60–

84355, on any airplane. 

Terminating Action for AD 2002–13–10 

(n) Replacing all fuel pump housing 

electrical connectors, P/N 60–84355, with 

new, improved parts in accordance with 

paragraph (k) or (l) of this AD, as applicable, 

terminates the requirements of AD 2002–13–

10. 

Terminating Action for AD 2003–07–14 

(o) Replacing all fuel pump housing 

electrical connectors, P/N 60–84355, with 


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40222 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 

new, improved parts in accordance with 

paragraph (k) of this AD terminates the 

requirements of AD 2003–07–14. 

Terminating Action for Paragraph (a) of AD 

2000–22–21 

(p) Replacing all fuel pump housing 

electrical connectors, P/N 60–84355, with 

new, improved parts in accordance with 

paragraph (k) or (l) of this AD, as applicable, 

terminates the requirements of paragraph (a) 

of AD 2000–22–21. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Material Incorporated by Reference 

(r) You must use the service information 

identified in Table 5 of this AD to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. 

TABLE 5.—MATERIAL INCORPORATED BY REFERENCE

Service information Revision level Date 

Boeing Alert Service Bulletin DC10–28A259 .......................................... Original .......................................... March 20, 2007. 

Boeing Alert Service Bulletin MD11–28A138 ......................................... 1 ..................................................... March 26, 2007. 

Boeing Flight Operations Bulletin DC–10–00–01A, MD–11–00–03A, 

and MD–10–00–02A.

Original .......................................... September 20, 2000. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin DC10–28A259, 

dated March 20, 2007; and Boeing Alert 

Service Bulletin MD11–28A138, Revision 1, 

dated March 26, 2007; in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) On December 5, 2000 (65 FR 69658, 

November 20, 2000), the Director of the 

Federal Register approved the incorporation 

by reference of Boeing Flight Operations 

Bulletin DC–10–00–01A, MD–11–00–03A, 

and MD–10–00–02A, dated September 20, 

2000. 

(3) Contact Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024), for a copy of this 

service information. You may review copies 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on July 13, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–14043 Filed 7–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27268; Directorate 

Identifier 2006–NM–190–AD; Amendment 

39–15135; AD 2007–15–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 airplanes. This AD requires 

revising the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. This 

AD results from fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

August 28, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 28, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building, 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647–

5527) is located on the ground floor of 

the West Building at the street address 

stated in the ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all Airbus Model A318, A319, 

A320, and A321 airplanes. That NPRM 

was published in the Federal Register 

on February 22, 2007 (72 FR 7936). That 

NPRM proposed to require revising the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment 

received. The commenter, Airbus, 

supports the NPRM. 


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