AD 2007-15-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | McDonnell Douglas | DC-10-10 DC-10-10F | 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 |
Unsafe Condition
could result in a fuel tank explosion and consequent loss of the airplane.
Federal Register Abstract
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 explosion and consequent loss of the airplane.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 72, Number 141 (Tuesday, July 24, 2007)]
[Rules and Regulations]
[Pages 40216-40222]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E7-14043]
-----------------------------------------------------------------------
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
[[Page 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.
<bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow
the instructions for sending your comments electronically.
<bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your
comments electronically.
<bullet> 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.
<bullet> Fax: (202) 493-2251.
<bullet> 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:
<bullet> 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.
<bullet> 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
[[Page 40218]]
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:
<bullet> 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.
<bullet> Deactivating certain fuel tanks or fuel pumps, as
applicable.
<bullet> 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.
Examining the Docket
You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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,
[[Page 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
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 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.
[[Page 40220]]
Table 1.--Requirements for Model DC-10 and Model MD-10 Airplanes
----------------------------------------------------------------------------------------------------------------
Deactivated fuel
Airplanes Compliance time tank(s) or fuel Placard location Work package
pump
----------------------------------------------------------------------------------------------------------------
Group 1......................... Within 90 days Auxiliary fuel On or adjacent to Work Package 1--
after the tank. the flight Part 1--Option 1--
effective date of engineer's fuel Aux Fuel Tank
this AD. control panel. (Deactivation).
Group 2: Model DC-10-10 and DC- Within 90 days Upper and lower On or adjacent to Work Package 1--
10-10F airplanes, Model DC-10- after the auxiliary fuel the flight Option 1--Part 1--
15 airplanes, Model DC-10-30 effective date of tanks. engineer's fuel Upper and Lower
and DC-10-30F (KC-10A and KDC- this AD. control panel. Aux Fuel Tanks
10) airplanes, and Model DC-10- (Deactivation)
40 and DC-10-40F airplanes. (DC-10/KDC-10).
Group 2: Model MD-10-10F and MD- Within 90 days Upper and lower Adjacent to Work Package 1--
10-30F airplanes. after the auxiliary fuel display units 1 Option 1--Part 1--
effective date of tanks. and 6. Upper and Lower
this AD. Aux Fuel Tanks
(Deactivation)
(MD-10).
Group 3......................... Within 90 days Upper, lower, and On or adjacent to Work Package 1--
after the aft fuel tanks. the flight Option 1--Part 1--
effective date of engineer's fuel Upper, Lower and
this AD. control panel. Aft Aux Fuel
Tanks
(Deactivation).
Group 4......................... Within 14 days Fuel pump for aft On or adjacent to Work Package 1--
after the fuselage tank. the flight Option 1--Part 1--
effective date of engineer's fuel Aft Fuselage Fuel
this AD. control panel. Pump
(Deactivation).
Within 14 days Fuel pumps for On or adjacent to Work Package 2--
after the wing tip tanks 1 the flight Option 1--Part 1--
effective date of and 3. engineer's fuel Wing Tip Tank 1
this AD. control panel. and 3 Pumps
(Deactivation).
Within 90 days Upper and lower On or adjacent to Work Package 1--
after the center wing tanks. the flight Option 1--Part 1--
effective date of engineer's fuel Upper and Lower
this AD. control panel. Center Wing Fuel
Tanks
(Deactivation).
Within 90 days Fuel pump for On or adjacent to Work Package 4--
after the forward fuselage the flight Option 1--Part 1--
effective date of tank. engineer's fuel Fwd Fuselage Fuel
this AD. control panel. 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 Not applicable......... Work Package 1--Option
the effective date of 1--Part 1--Tank 2
this AD. (Placards
Installation).
Within 90 days after Tail tank.............. Work Package 2--Option
the effective date of 1--Part 1--Tail Tank
this AD. (Deactivation).
Within 90 days after Not applicable......... Work Package 3--Option
the effective date of 1--Part 1--Upper
this AD. Auxiliary Tank
(Placards
Installation).
Within 90 days after Lower auxiliary tank... Work Package 4--Option
the effective date of 1--Part 1--Lower
this AD. Auxiliary Tank
(Deactivation).
Group 2.............................. Within 14 days after Forward auxiliary tank. Work Package 1--Option
the effective date of 1--Part 1--Forward
this AD. Auxiliary Tank
(Deactivation).
Within 14 days after Not applicable......... Work Package 2--Option
the effective date of 1--Part 1--Tank 2
this AD. (Placards
Installation).
Within 90 days after Tail tank.............. Work Package 3--Option
the effective date of 1--Part 1--Tail Tank
this AD. (Deactivation).
[[Page 40221]]
Within 90 days after Not applicable......... Work Package 4--Option
the effective date of 1--Part 1--Upper
this AD. Auxiliary Tank
(Placards
Installation).
Within 90 days after Lower auxiliary tank... Work Package 5--Option
the effective date of 1--Part 1--Lower
this AD. 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 Work Package 1--Option 1--Part
airplanes, Model DC-10-15 airplanes, 2 or Option 2--Upper and Lower
Model DC-10-30 and DC-10-30F (KC-10A Aux Fuel Tanks (DC-10/KDC-10)
and KDC-10) airplanes, and Model DC-10- (Connector Replacement).
40 and DC-10-40F airplanes.
Group 2: Model MD-10-10F and MD-10-30F Work Package 1--Option 1--Part
airplanes. 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
[[Page 40222]]
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 Original.......... March 20, 2007.
DC10-28A259.
Boeing Alert Service Bulletin 1................. March 26, 2007.
MD11-28A138.
Boeing Flight Operations Original.......... September 20,
Bulletin DC-10-00-01A, MD-11-00- 2000.
03A, and MD-10-00-02A.
------------------------------------------------------------------------
(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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
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
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
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