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, 12301-12303 [E8-4475]

Download as PDF Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27339; Directorate Identifier 2006–NM–280–AD] 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 Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: We are revising an earlier proposed airworthiness directive (AD) for certain transport category airplanes identified above. The original NPRM would have required modifying the fuel boost pumps. The original NPRM resulted from a fuel boost pump found with blown thermal fuses and a fractured thrust washer. This action revises the original NPRM by referring to new service information, which would require more work. We are proposing this supplemental NPRM to prevent failure of the fuel boost pumps, which could lead to the potential of ignition sources inside fuel tanks. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this supplemental NPRM by April 1, 2008. You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • 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. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial rwilkins on PROD1PC63 with PROPOSALS ADDRESSES: VerDate Aug<31>2005 17:21 Mar 06, 2008 Jkt 214001 Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California, 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5262; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–27339; Directorate Identifier 2006–NM–280–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued a notice of proposed rulemaking (NPRM) (the ‘‘original NPRM’’) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain 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. That original PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 12301 NPRM was published in the Federal Register on February 26, 2007 (72 FR 8307). That original NPRM proposed to require modifying the fuel boost pumps. Actions Since Original NPRM Was Issued Since we issued the original NPRM, Boeing and Crane Hydro-Aire have revised their service information for modifying certain fuel boost pumps. The original NPRM referred to Boeing Alert Service Bulletin DC10–28A254 and Boeing Alert Service Bulletin MD11–28A134, both dated September 8, 2006, which in turn refer to Crane Hydro-Aire Service Bulletin 60–847– 28–3, dated May 1, 2006, as an additional source of service information for accomplishing the modification. This supplemental NPRM refers to the revised service information, which would require more work. The additional work involves rerouting the stator-to-connector wire leads for fuel boost pumps modified according to the original issue of Crane Hydro-Aire Service Bulletin 60–847–28–3. Relevant Service Information We have reviewed the following service bulletins: • Boeing Alert Service Bulletin DC10–28A254, Revision 1, dated September 12, 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 MD11–28A134, Revision 1, dated September 6, 2007, for Model MD–11 and MD–11F airplanes. Revision 1 of the service bulletins describe procedures for modifying fuel boost pumps, part numbers (P/Ns) 60– 847–1A, –2, and –3, as applicable. The service bulletins also refer to Crane Hydro-Aire Service Bulletin 60–847– 28–3, Revision 1, dated July 2, 2007, as an additional source of service information for modifying the fuel boost pumps. The modification involves upgrading the rotor assembly by replacing the Stellite thrust washer with a stainless steel thrust washer manufactured after a certain date, inspecting the stator assembly wire leads, replacing the stator assembly with a new assembly if necessary, rerouting the stator-to-connector wire leads if necessary, and replacing the washers, screws, and other hardware with new parts. Fuel boost pumps modified according to the original issue of Crane Hydro-Aire Service Bulletin 60–847– 28–3 need to be reworked by rerouting E:\FR\FM\07MRP1.SGM 07MRP1 12302 Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules the stator-to-connector wire leads to prevent damage to the wire leads during pump assembly. Revision 1 of Crane Hydro-Aire Service Bulletin 60–847–28–3 specifies prior accomplishment of Crane HydroAire Service Bulletin 60–847–1A–28–6, dated February 15, 1973, for fuel boost pump P/N 60–847–1A. Crane HydroAire Service Bulletin 60–847–28–3 also specifies prior accomplishment of Crane Hydro-Aire Service Bulletin 60–847–3– 28–13, dated March 17, 1975, for fuel boost pump P/N 60–847–2. rwilkins on PROD1PC63 with PROPOSALS Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the one commenter. Request To Limit the Scope of the Modification Boeing requests that we limit the scope of the proposed modification to replacing the Stellite thrust washer with a steel washer. Boeing suggests that we revise paragraph (g) of the supplemental NPRM to specify that operators must modify the fuel boost pump by replacing the Stellite thrust washer with a steel thrust washer. Boeing also suggests that we delete the sentence regarding the modification details from the ‘‘Relevant Service Information’’ section of the original NPRM and replace it with the following sentences: ‘‘The primary required modification involves upgrading the rotor assembly to include a new thrust washer. The service information also includes instructions for inspecting the stator assembly wire leads, and rerouting the stator-to-connector wire leads with sleeving, if necessary. Washers, screws, and other miscellaneous hardware are also replaced.’’ As justification, Boeing states that modification of the fuel boost pumps is solely driven by the need to replace the Stellite thrust washer, and that this action alone will address the unsafe condition. Boeing also states that the other actions mentioned in the ‘‘Relevant Service Information’’ section of the original NPRM are not related to the unsafe condition. Boeing states that those other actions depend on the serviceability of certain components within the pump assembly, which is determined during pump disassembly and the inspection. Boeing asserts that the related information was included in Crane Hydro-Aire Service Bulletin 60– 847–28–3 to highlight certain component serviceability checks that are done as part of any pump disassembly and should be emphasized as part of the required action. According to Boeing, this is particularly true for VerDate Aug<31>2005 17:21 Mar 06, 2008 Jkt 214001 rerouting the stator-to-connector wire leads, since the connector must be removed and replaced with a new connector in order to reroute the wire leads. Boeing states that if the connector is serviceable, the wire leads do not need to be rerouted. Additionally, replacement of the existing attachment hardware, screws, and washers is a consequence of disassembly/assembly of the pump, as part of thrust washer replacement. We agree that the primary action of the modification is to replace the Stellite thrust washer with a stainless steel thrust washer. We also agree that replacement of the electrical connector of the pump assembly depends upon the inspection results. We have revised the ‘‘Relevant Service Information’’ section of this supplemental NPRM to specify that the modification involves replacing the stator assembly with a new assembly if necessary, and rerouting the stator-toconnector wire leads if necessary. However, we have determined that both the physical integrity of the thrust washer and the critical configuration control of the routing of the stator lead wires must be addressed in order to minimize potential ignition sources associated with failure of a fuel boost pump. This is accomplished by replacing the Stellite thrust washer, inspecting the stator wire leads, and replacing the stator assembly if necessary. Operators must also verify that the stator-to-connector wire leads are properly routed, and reroute the wire leads if necessary. Therefore, we have not revised paragraph (g) of this supplemental NPRM. FAA’s Determination and Proposed Requirements of the Supplemental NPRM We are proposing this supplemental NPRM because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Certain changes described above expand the scope of the original NPRM. As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this supplemental NPRM. Costs of Compliance We estimate that this proposed AD would affect 360 airplanes of U.S. registry. We also estimate that it would take about 3 work-hours per fuel boost pump to comply with this proposed AD. The average labor rate is $80 per workhour. Required parts would cost about $640 per fuel boost pump. Depending on the airplane configuration, there are PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 between 10 and 19 fuel boost pumps per product. Based on these figures, we estimate the cost of this proposed AD to the U.S. operators to be between $3,168,000 and $6,019,200, or between $8,800 and $16,720 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: E:\FR\FM\07MRP1.SGM 07MRP1 Federal Register / Vol. 73, No. 46 / Friday, March 7, 2008 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES information for accomplishing the modification in paragraph (g) of this AD. 1. The authority citation for part 39 continues to read as follows: Modification (g) At the applicable compliance time specified in paragraph (g)(1) or (g)(2) of this AD, modify the fuel boost pumps having part numbers 60–847–1A, –2, and –3, in accordance with the Accomplishment Instructions of the applicable service bulletin. (1) For fuel boost pumps identified as Configuration 1 or 2 in Table 1 of paragraph 1.E. of the applicable service bulletin, do the modification within 120 months after the effective date of this AD. (2) For fuel boost pumps identified as Configuration 3 in Table 1 of paragraph 1.E. of the applicable service bulletin, do the modification within 72 months after the effective date of this AD. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: McDonnell Douglas: Docket No. FAA–2007– 27339; Directorate Identifier 2006–NM– 280–AD. Comments Due Date (a) We must receive comments by April 1, 2008. Affected ADs (b) None. Applicability (c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) 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; as identified in Boeing Alert Service Bulletin DC10–28A254, Revision 1, dated September 12, 2007. (2) McDonnell Douglas Model MD–11 and MD–11F airplanes, as identified in Boeing Alert Service Bulletin MD11–28A134, Revision 1, dated September 6, 2007. Unsafe Condition (d) This AD results from a fuel boost pump found with blown thermal fuses and a fractured thrust washer. We are issuing this AD to prevent failure of the fuel boost pumps, which could lead to the potential of ignition sources inside fuel tanks. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. rwilkins on PROD1PC63 with PROPOSALS Compliance (e) Comply with this AD within the compliance times specified, unless already done. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the following service bulletins, as applicable: (1) For the airplanes identified in paragraph (c)(1) of this AD, Boeing Alert Service Bulletin DC10–28A254, Revision 1, dated September 12, 2007. (2) For the airplanes identified in paragraph (c)(2) of this AD, Boeing Alert Service Bulletin MD11–28A134, Revision 1, dated September 6, 2007. Note 1: Boeing Alert Service Bulletin DC10–28A254, Revision 1, dated September 12, 2007; and Boeing Alert Service Bulletin MD11–28A134, Revision 1, dated September 6, 2007; refer to Crane Hydro-Aire Service Bulletin 60–847–28–3, Revision 1, dated July 2, 2007, as an additional source of service VerDate Aug<31>2005 17:21 Mar 06, 2008 Jkt 214001 Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5262; fax (562) 627–5210; has the authority to approve AMOCs for this AD, if requested using 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. Issued in Renton, Washington, on March 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–4475 Filed 3–6–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0258; Directorate Identifier 2007–SW–22–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Models 206L, L–1, L–3, L–4, and 407 Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 12303 specified Bell Helicopter Textron Canada (BHTC) helicopters. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The Aviation Authority of Canada with whom we have a bilateral agreement states in the MCAI: Horizontal stabilizers part numbers 206– 023–119–167 and 407–023–801–109 may have manufacturing flaws on the inside surface of the upper and/or lower skin at the tailboom attachment inserts. These flaws may result in cracking of the skin and failure of the horizontal stabilizer. The manufacturer’s service information states that in addition to cracks, the horizontal stabilizer may have deformation or debonding around and between the inserts. The proposed AD would require actions that are intended to address all these unsafe conditions. DATES: We must receive comments on this proposed AD by April 7, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • 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. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov, or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. E:\FR\FM\07MRP1.SGM 07MRP1

Agencies

[Federal Register Volume 73, Number 46 (Friday, March 7, 2008)]
[Proposed Rules]
[Pages 12301-12303]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4475]



[[Page 12301]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27339; Directorate Identifier 2006-NM-280-AD]
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), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain transport category airplanes identified above. The 
original NPRM would have required modifying the fuel boost pumps. The 
original NPRM resulted from a fuel boost pump found with blown thermal 
fuses and a fractured thrust washer. This action revises the original 
NPRM by referring to new service information, which would require more 
work. We are proposing this supplemental NPRM to prevent failure of the 
fuel boost pumps, which could lead to the potential of ignition sources 
inside fuel tanks. This condition, in combination with flammable fuel 
vapors, could result in fuel tank explosions and consequent loss of the 
airplane.

DATES: We must receive comments on this supplemental NPRM by April 1, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, 
Long Beach, California, 90846, Attention: Data and Service Management, 
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
27339; Directorate Identifier 2006-NM-280-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued a notice of proposed rulemaking (NPRM) (the ``original 
NPRM'') to amend 14 CFR part 39 to include an airworthiness directive 
(AD) that would apply to certain 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. That original NPRM was published in the Federal 
Register on February 26, 2007 (72 FR 8307). That original NPRM proposed 
to require modifying the fuel boost pumps.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, Boeing and Crane Hydro-Aire have 
revised their service information for modifying certain fuel boost 
pumps. The original NPRM referred to Boeing Alert Service Bulletin 
DC10-28A254 and Boeing Alert Service Bulletin MD11-28A134, both dated 
September 8, 2006, which in turn refer to Crane Hydro-Aire Service 
Bulletin 60-847-28-3, dated May 1, 2006, as an additional source of 
service information for accomplishing the modification. This 
supplemental NPRM refers to the revised service information, which 
would require more work. The additional work involves rerouting the 
stator-to-connector wire leads for fuel boost pumps modified according 
to the original issue of Crane Hydro-Aire Service Bulletin 60-847-28-3.

Relevant Service Information

    We have reviewed the following service bulletins:
     Boeing Alert Service Bulletin DC10-28A254, Revision 1, 
dated September 12, 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 MD11-28A134, Revision 1, 
dated September 6, 2007, for Model MD-11 and MD-11F airplanes.
    Revision 1 of the service bulletins describe procedures for 
modifying fuel boost pumps, part numbers (P/Ns) 60-847-1A, -2, and -3, 
as applicable. The service bulletins also refer to Crane Hydro-Aire 
Service Bulletin 60-847-28-3, Revision 1, dated July 2, 2007, as an 
additional source of service information for modifying the fuel boost 
pumps. The modification involves upgrading the rotor assembly by 
replacing the Stellite thrust washer with a stainless steel thrust 
washer manufactured after a certain date, inspecting the stator 
assembly wire leads, replacing the stator assembly with a new assembly 
if necessary, rerouting the stator-to-connector wire leads if 
necessary, and replacing the washers, screws, and other hardware with 
new parts. Fuel boost pumps modified according to the original issue of 
Crane Hydro-Aire Service Bulletin 60-847-28-3 need to be reworked by 
rerouting

[[Page 12302]]

the stator-to-connector wire leads to prevent damage to the wire leads 
during pump assembly.
    Revision 1 of Crane Hydro-Aire Service Bulletin 60-847-28-3 
specifies prior accomplishment of Crane Hydro-Aire Service Bulletin 60-
847-1A-28-6, dated February 15, 1973, for fuel boost pump P/N 60-847-
1A. Crane Hydro-Aire Service Bulletin 60-847-28-3 also specifies prior 
accomplishment of Crane Hydro-Aire Service Bulletin 60-847-3-28-13, 
dated March 17, 1975, for fuel boost pump P/N 60-847-2.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the one commenter.

Request To Limit the Scope of the Modification

    Boeing requests that we limit the scope of the proposed 
modification to replacing the Stellite thrust washer with a steel 
washer. Boeing suggests that we revise paragraph (g) of the 
supplemental NPRM to specify that operators must modify the fuel boost 
pump by replacing the Stellite thrust washer with a steel thrust 
washer. Boeing also suggests that we delete the sentence regarding the 
modification details from the ``Relevant Service Information'' section 
of the original NPRM and replace it with the following sentences: ``The 
primary required modification involves upgrading the rotor assembly to 
include a new thrust washer. The service information also includes 
instructions for inspecting the stator assembly wire leads, and 
rerouting the stator-to-connector wire leads with sleeving, if 
necessary. Washers, screws, and other miscellaneous hardware are also 
replaced.'' As justification, Boeing states that modification of the 
fuel boost pumps is solely driven by the need to replace the Stellite 
thrust washer, and that this action alone will address the unsafe 
condition. Boeing also states that the other actions mentioned in the 
``Relevant Service Information'' section of the original NPRM are not 
related to the unsafe condition. Boeing states that those other actions 
depend on the serviceability of certain components within the pump 
assembly, which is determined during pump disassembly and the 
inspection. Boeing asserts that the related information was included in 
Crane Hydro-Aire Service Bulletin 60-847-28-3 to highlight certain 
component serviceability checks that are done as part of any pump 
disassembly and should be emphasized as part of the required action. 
According to Boeing, this is particularly true for rerouting the 
stator-to-connector wire leads, since the connector must be removed and 
replaced with a new connector in order to reroute the wire leads. 
Boeing states that if the connector is serviceable, the wire leads do 
not need to be rerouted. Additionally, replacement of the existing 
attachment hardware, screws, and washers is a consequence of 
disassembly/assembly of the pump, as part of thrust washer replacement.
    We agree that the primary action of the modification is to replace 
the Stellite thrust washer with a stainless steel thrust washer. We 
also agree that replacement of the electrical connector of the pump 
assembly depends upon the inspection results. We have revised the 
``Relevant Service Information'' section of this supplemental NPRM to 
specify that the modification involves replacing the stator assembly 
with a new assembly if necessary, and rerouting the stator-to-connector 
wire leads if necessary.
    However, we have determined that both the physical integrity of the 
thrust washer and the critical configuration control of the routing of 
the stator lead wires must be addressed in order to minimize potential 
ignition sources associated with failure of a fuel boost pump. This is 
accomplished by replacing the Stellite thrust washer, inspecting the 
stator wire leads, and replacing the stator assembly if necessary. 
Operators must also verify that the stator-to-connector wire leads are 
properly routed, and reroute the wire leads if necessary. Therefore, we 
have not revised paragraph (g) of this supplemental NPRM.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    We are proposing this supplemental NPRM because we evaluated all 
pertinent information and determined an unsafe condition exists and is 
likely to exist or develop on other products of the same type design. 
Certain changes described above expand the scope of the original NPRM. 
As a result, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for the public to 
comment on this supplemental NPRM.

Costs of Compliance

    We estimate that this proposed AD would affect 360 airplanes of 
U.S. registry. We also estimate that it would take about 3 work-hours 
per fuel boost pump to comply with this proposed AD. The average labor 
rate is $80 per work-hour. Required parts would cost about $640 per 
fuel boost pump. Depending on the airplane configuration, there are 
between 10 and 19 fuel boost pumps per product. Based on these figures, 
we estimate the cost of this proposed AD to the U.S. operators to be 
between $3,168,000 and $6,019,200, or between $8,800 and $16,720 per 
product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 12303]]

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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

McDonnell Douglas: Docket No. FAA-2007-27339; Directorate Identifier 
2006-NM-280-AD.

Comments Due Date

    (a) We must receive comments by April 1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) 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; as identified in Boeing Alert 
Service Bulletin DC10-28A254, Revision 1, dated September 12, 2007.
    (2) McDonnell Douglas Model MD-11 and MD-11F airplanes, as 
identified in Boeing Alert Service Bulletin MD11-28A134, Revision 1, 
dated September 6, 2007.

Unsafe Condition

    (d) This AD results from a fuel boost pump found with blown 
thermal fuses and a fractured thrust washer. We are issuing this AD 
to prevent failure of the fuel boost pumps, which could lead to the 
potential of ignition sources inside fuel tanks. This condition, in 
combination with flammable fuel vapors, could result in fuel tank 
explosions and consequent loss of the airplane.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
following service bulletins, as applicable:
    (1) For the airplanes identified in paragraph (c)(1) of this AD, 
Boeing Alert Service Bulletin DC10-28A254, Revision 1, dated 
September 12, 2007.
    (2) For the airplanes identified in paragraph (c)(2) of this AD, 
Boeing Alert Service Bulletin MD11-28A134, Revision 1, dated 
September 6, 2007.

    Note 1: Boeing Alert Service Bulletin DC10-28A254, Revision 1, 
dated September 12, 2007; and Boeing Alert Service Bulletin MD11-
28A134, Revision 1, dated September 6, 2007; refer to Crane Hydro-
Aire Service Bulletin 60-847-28-3, Revision 1, dated July 2, 2007, 
as an additional source of service information for accomplishing the 
modification in paragraph (g) of this AD.

Modification

    (g) At the applicable compliance time specified in paragraph 
(g)(1) or (g)(2) of this AD, modify the fuel boost pumps having part 
numbers 60-847-1A, -2, and -3, in accordance with the Accomplishment 
Instructions of the applicable service bulletin.
    (1) For fuel boost pumps identified as Configuration 1 or 2 in 
Table 1 of paragraph 1.E. of the applicable service bulletin, do the 
modification within 120 months after the effective date of this AD.
    (2) For fuel boost pumps identified as Configuration 3 in Table 
1 of paragraph 1.E. of the applicable service bulletin, do the 
modification within 72 months after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM-
140L, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; fax (562) 627-5210; has the authority to 
approve AMOCs for this AD, if requested using 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.

    Issued in Renton, Washington, on March 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-4475 Filed 3-6-08; 8:45 am]
BILLING CODE 4910-13-P

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