[Federal Register Volume 68, Number 153 (Friday, August 8, 2003)]
[Rules and Regulations]
[Pages 47204-47207]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-19682]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-144-AD; Amendment 39-13254; AD 2003-16-02]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-
10-40F, MD-10-10F, and MD-10-30F Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas transport category airplanes 
listed above. This action requires inspecting the fuel boost/transfer 
pumps or reviewing the airplane maintenance records to determine the 
part number of the fuel boost/transfer pumps, and follow-on actions if 
necessary. This action is necessary to prevent heated localized 
temperatures within the fuel boost/transfer pumps due to frictional 
heating, which could result in a potential source of ignition in a fuel 
tank and consequent fire or explosion. This action is intended to 
address the identified unsafe condition.

DATES: Effective August 25, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 25, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before October 7, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-144-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-144-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must

[[Page 47205]]

be formatted in Microsoft Word 97 or 2000 or ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). This information may be examined 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

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: The FAA has received two reports of evidence 
of heat damage to the reprime impeller area found during a visual 
inspection of the fuel pumps on certain Boeing Model 747 series 
airplanes. The heat discoloration of the damaged parts indicates that 
the fuel pumps were exposed to high temperatures due to frictional 
heating between pump components. Such conditions within the pumps can 
create a potential ignition source and auto-ignition of vapors could 
occur, which could result in fire or explosion in a fuel tank.
    A review of design data by the manufacturer revealed that a fuel 
boost/transfer pump having Hydro-Aire part number (P/N) 60-847-1A has 
less internal fuel retention capability than other fuel boost/transfer 
pumps. It was determined that the smaller fuel retention capability of 
the Hydro-Aire fuel pumps may intensify the frictional heating. 
Replacement of the Hydro-Aire fuel pumps with the improved pumps will 
minimize the risk of a potential ignition source in the fuel tank.

Similar Models

    The fuel boost/transfer pumps of the reprime impeller area of the 
Hydro-Aire P/N 60-847-1A on McDonnell Douglas Model DC-10-10, DC-10-
10F, DC-10-15, DC-10-30, DC-10-30F (KC10A and KDC-10), DC-10-40, DC-10-
40F, MD-10-10F, and MD-10-30F airplanes are similar to those on Boeing 
Model 737-600, -700, -700C, -800, and -900 series airplanes, Model 747 
series airplanes, and Model 757 series airplanes. Therefore, all of 
these models may be subject to the same unsafe condition.

Other Relevant Rulemaking

    The FAA has previously issued the following two ADs that concern 
the fuel boost/transfer pumps on Boeing Model 737-600, -700, -700C, -
800, and -900 series airplanes, Model 747 series airplanes, and Model 
757 series airplanes:
    1. AD 2002-24-51, amendment 39-12992 (68 FR 10, January 2, 2003), 
applicable all Boeing Model 737-600, -700, -700C, -800, and -900 series 
airplanes, Model 747 series airplanes, and Model 757 series airplanes, 
requires revising the Airplane Flight Manual (AFM) to require the 
flightcrew to maintain certain minimum fuel levels in the center fuel 
tanks, and, for certain airplanes, to prohibit the use of the 
horizontal stabilizer fuel tank and certain center auxiliary fuel 
tanks.
    2. AD 2002-24-52, amendment 39-12993 (68 FR 14, January 2, 2003), 
applicable to all Boeing Model 747-400, -400D, and -400F series 
airplanes, requires revising the AFM to require the flightcrew to 
maintain certain minimum fuel levels in the center fuel tanks, and to 
prohibit the use of the horizontal stabilizer fuel tank. That AD also 
removes the reference to placards that was specified in the operating 
limiations required by AD 2002-24-51.
    This AD will not affect the current requirements of any of those 
previously issued ADs.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
(ASB) DC10-28A241, dated April 24, 2003, which describes, among other 
things, the following:
    [sbull] Condition 1--Procedures for reviewing the airplane 
maintenance records to determine if any fuel boost/transfer pump having 
P/N 60-847-1A is installed. If the records show that none of the pumps 
have P/N 60-847-1A, no further action is necessary.
    [sbull] Condition 2--Procedures for a visual inspection to 
determine if a pump having P/N 60-847-1A is installed. If the 
inspection shows that no pump having P/N 60-847-1A is installed, no 
further action is necessary.
    [sbull] Condition 3, Option 1a.--Procedures to replace the pump 
with a new pump, if the records or visual inspection verify that a pump 
having P/N 60-847-1A is installed and replacement pumps are available.
    [sbull] Condition 3, Option 2a.--Procedures to deactivate any pump 
having P/N 60-847-1A if replacement pumps are not available.
    [sbull] Condition 3, Option 2b.--Procedures to relocate pumps 
having P/N 60-847-1A, if replacement pumps are not available.
    In addition, Appendix A, Recommended Operating Limitations, of the 
ASB describes certain operating procedures, limitations, and related 
maintenance actions intended to prevent fuel vapors from coming into 
contact with a possible ignition source in the fuel tanks.
    The accomplishment of certain actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD requires accomplishment of certain 
actions specified in the service bulletin described previously, except 
as discussed below.

Differences Between This AD and the Service Bulletin

    The service bulletin recommends a review of the airplane 
maintenance records to determine if a certain P/N for the fuel boost/
transfer pump is installed. This AD requires a general visual 
inspection to determine the P/N. In lieu of the inspection, a review of 
the airplane maintenance records is acceptable if the P/N of the pump 
can be positively determined from that review.
    While Option 2.b. of the service bulletin recommends replacement of 
all relocated pumps within 18 months after issue date of the service 
bulletin, this AD requires only the relocation of the pumps, or 
deactivation of the pumps having P/N 60-847-1A per the McDonnell 
Douglas DC-10 Minimum Equipment List.
    Appendix A of the service bulletin contains operating limitations 
and related maintenance actions for fuel boost/transfer pumps having P/
N 60-847-1A that are installed in all locations except those boost 
pumps located in the aft position of the main tanks. This AD does not 
specify implementation of the operating limitations and related 
maintenance actions for boost pumps in the aft position of the main 
tanks since these pumps are always covered with fuel during takeoff, 
which prevents heated localized temperatures from occurring within the 
fuel boost/transfer pump due to frictional heating.

[[Page 47206]]

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in each 
individual AD.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-144-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-16-02 McDonnell Douglas: Amendment 39-13254. Docket 2003-NM-
144-AD.

    Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, 
DC-10-30F (KC10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and 
MD-10-30F airplanes; as listed in Boeing Alert Service Bulletin 
(ASB) DC10-28A241, dated April 24, 2003; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent heated localized temperatures within the fuel boost/
transfer pumps due to frictional heating, which could result in a 
potential source of ignition in a fuel tank and consequent fire or 
explosion, accomplish the following:

Inspection/Records Review/Follow-on Actions

    (a) Within 90 days after the effective date of this AD: Do a 
general visual inspection of the fuel boost/transfer pumps to 
determine if Hydro-Aire part number (P/N) 60-847-1A is installed. 
Instead of inspecting the pumps, a review of the airplane 
maintenance records is acceptable if the P/N of the pumps can be 
positively determined from that review. Do the actions per the Work 
Instructions of Boeing Alert Service Bulletin DC10-28A241, dated 
April 24, 2003.
    (1) If the inspection and/or records verify that no pump having 
P/N 60-847-1A is installed, no further action is required by this 
paragraph.
    (2) If the inspection and/or records verify that a pump having 
P/N 60-847-1A is installed, do the applicable actions specified in 
paragraph (b) of this AD.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (b) With the exception of fuel boost pumps having P/N 60-847-1A 
that are located in the aft position of the main tanks: Do the 
applicable actions specified in paragraph (b)(1) or (b)(2) of this 
AD, at the applicable times specified, per the Work Instructions of 
Boeing Alert Service Bulletin DC10-28A241, dated April 24, 2003.
    (1) If replacement pumps having either P/N 60-847-2 or P/N 60-
847-3 are available, within 90 days after the effective date of this 
AD, replace the pumps per Option 1 of Condition 3 of the ASB. With 
the exception of paragraph (c) of this AD, this constitutes 
terminating action for the requirements of this AD.
    (2) If replacement pumps are not available, do the actions 
specified in paragraph (b)(2)(i), (b)(2)(ii), or (b)(2)(iii) of this 
AD within 90 days after the effective date of this AD.

[[Page 47207]]

    (i) Deactivate pumps having P/N 60-847-1A per the McDonnell 
Douglas DC-10 Minimum Equipment List (MEL) and replace the pump with 
a pump having P/N 60-847-2 or 60-847-3 within the time limitations 
specified in the MEL, per Option 2a. of Condition 3 of the ASB.
    (ii) Relocate the pumps per Option 2b. of Condition 3 of the 
ASB. Or,
    (iii) Insert Appendix A of the ASB into the Limitations Section 
of the Airplane Flight Manual.

    Note 2: Fuel boost pumps having P/N 60-847-1A that are located 
in the aft position of the main tanks are always covered with fuel 
during takeoff; therefore, operating the airplane per the operations 
limitations specified in Appendix A of Boeing Alert Service Bulletin 
DC10-28A241, dated April 24, 2003, is unnecessary.

Parts Installation

    (c) As of the effective date of this AD, no person shall replace 
a fuel boost/transfer pump on any airplane with a fuel boost/
transfer pump having Hydro-Aire P/N 60-847-1A, unless that pump is 
installed in the aft position of the main tanks. A fuel boost/
transfer pump having Hydro-Aire P/N 60-847-1A that is removed for 
inspection per paragraph (a) of this AD may be reinstalled until 
paragraph (b) of this AD is complied with.

Alternative Methods of Compliance

    (d) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (e) Unless otherwise specified in this AD, the actions shall be 
done per Boeing Alert Service Bulletin DC10-28A241, dated April 24, 
2003. This incorporation by reference was approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

Effective Date

    (f) This amendment becomes effective on August 25, 2003.

    Issued in Renton, Washington, on July 29, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-19682 Filed 8-7-03; 8:45 am]
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