Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F (KDC-10), DC-10-40, and DC-10-40F Airplanes, 30086-30088 [E6-8010]

Download as PDF 30086 Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules (g) If Lycoming Engines manufactured new, rebuilt, overhauled, or repaired your engine, or replaced the crankshaft in your engine before March 1, 1997, and you haven’t had the crankshaft replaced, no further action is required. (h) If Table 1, Table 2, Table 3, or Table 4 of Lycoming MSB No. 569A, dated April 11, 2006, lists your engine serial number (SN), and Table 5 of MSB No. 569A, dated April 11, 2006, does not list your crankshaft SN, no further action is required. Engines Not Exempted From the AD (i) If Table 1, Table 2, Table 3, or Table 4 of Lycoming MSB No. 569A, dated April 11, 2006, lists your engine SN, and Table 5 of MSB No. 569A, dated April 11, 2006, lists your crankshaft SN, replace the affected crankshaft with a crankshaft that is not listed in Table 5 of MSB No. 569A at either of the following: (1) The next engine overhaul as specified in Lycoming Engines Service Instruction No. 1009AR, dated June 22, 2004; or (2) The next separation of the crankcase, whichever is earlier. (j) If Table 1, Table 2, Table 3, or Table 4 of Lycoming MSB No. 569A, dated April 11, 2006, does not list your engine SN, and Table 5 of MSB No. 569A does list your crankshaft SN (an affected crankshaft was installed as a replacement), replace the affected crankshaft with a crankshaft that is not listed in Table 5 of MSB No. 569A at either of the following: (1) The next engine overhaul as specified in Lycoming Engines Service Instruction No. 1009AR, dated June 22, 2004; or (2) The next separation of the crankcase, whichever is earlier. Prohibition Against Installing Certain Crankshafts (k) After the effective date of this AD, do not install any crankshaft that has a SN listed in Table 5 of Lycoming MSB No. 569A, dated April 11, 2006, into any engine. Alternative Methods of Compliance (l) The Manager, New York Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (m) None. jlentini on PROD1PC65 with PROPOSAL Issued in Burlington, Massachusetts, on May 19, 2006. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–4850 Filed 5–24–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:43 May 24, 2006 Jkt 208001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24864; Directorate Identifier 2006–NM–072–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), for the service information identified in this proposed AD. Airworthiness Directives; McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–30, DC–10–30F (KDC–10), DC– 10–40, and DC–10–40F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). 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: RIN 2120–AA64 AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain McDonnell Douglas airplanes, identified above. This proposed AD would require reducing the length of the sump drain collar and replacing the fuel tank sump drain lockring for fuel tanks 1, 2, and 3; and reducing the length of the drain outlet barrel for the auxiliary fuel tank, if applicable. For airplanes with an auxiliary fuel tank, this proposed AD also would require relocating the sump drain outlet to allow draining the sumps without opening the doors of the main landing gear wheel well. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a lightning strike, which, in combination with flammable fuel vapors, could result in arcing in the fuel tank, fuel tank explosions, and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by July 10, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24864; Directorate Identifier 2006–NM–072–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed 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 DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif 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. E:\FR\FM\25MYP1.SGM 25MYP1 30087 Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (67 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Review of the lightning protection for the valve installation for the sump drain of the fuel tanks showed that the drain valves must be insulated. If the fuel level is below the drain valve body, and there is a lightning strike, electrical current could travel from the airplane skin up the sump drain collar into the valve housing. This condition, in combination with a lightning strike and flammable fuel vapors, could result in arcing in the fuel tank, fuel tank explosions, and consequent loss of the airplane. Relevant Service Information We have reviewed McDonnell Douglas DC–10 Service Bulletin 28–61, dated January 17, 1978. The service bulletin describes procedures for reducing the length of the sump drain collar and replacing the fuel tank sump drain lockring for fuel tanks 1, 2, and 3 with an improved lockring; and reducing the length of the drain outlet barrel for the auxiliary fuel tank, if applicable. McDonnell Douglas DC–10 Service Bulletin 28–61 specifies that for certain airplanes, before or concurrently with the modification of the sump drain outlets described above, the sump drain outlet for the auxiliary tank must be relocated to allow draining the sumps without opening the doors of the main landing gear wheel well. The procedures for doing this action are described in McDonnell Douglas DC–10 Bulletin 28–19, Revision 1, dated October 15, 1973. This action applies only to those airplanes identified as Group II in McDonnell Douglas DC–10 Service Bulletin 28–61, that are also contained in the effectivity of McDonnell Douglas DC–10 Bulletin 28– 19, Revision 1. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between the Proposed AD and Service Bulletin 28–61.’’ Difference Between the Proposed AD and Service Bulletin 28–61 McDonnell Douglas DC–10 Service Bulletin 28–61 recommends doing the modification at the operator’s convenience, which would not ensure an adequate level of safety for the affected fleet. In developing an appropriate compliance time for this AD, we considered the manufacturer’s recommendation, the degree of urgency associated with the subject unsafe condition, and the average utilization of the affected fleet. In light of all of these factors, we find that a compliance time of 60 months after the effective date of this AD represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. This difference has been coordinated with Boeing, and Boeing concurred. Costs of Compliance There are about 135 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The labor rate is $80 per work hour. ESTIMATED COSTS jlentini on PROD1PC65 with PROPOSAL Work hours Parts For all airplanes: Reduce the length of the sump drain collar and replace the fuel tank sump drain for fuel tanks 1, 2, and 3. For airplanes with an auxiliary fuel tank: Reduce the length of the drain outlet barrel for the auxiliary fuel tank. 3 to 15 $720 to $4,858 ........... $960 to $6,058 109 ................... $104,640 to $660,322. 6 to 15 $0 to $720 .................. $480 to $1,920 Up to 109 .......... $52,320 to $209,280. VerDate Aug<31>2005 15:43 May 24, 2006 Jkt 208001 PO 00000 Frm 00019 Fmt 4702 Cost per airplane Number of U.S.registered airplanes Action Sfmt 4702 E:\FR\FM\25MYP1.SGM 25MYP1 Fleet cost 30088 Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules ESTIMATED COSTS—Continued Cost per airplane Number of U.S.registered airplanes $80 to $480 ...... Up to 109 ......... Action Work hours Prior requirement for certain airplanes ............ 1 to 6 ... Authority for This Rulemaking List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 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. jlentini on PROD1PC65 with PROPOSAL Regulatory Findings We have 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 that the 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. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 15:43 May 24, 2006 Jkt 208001 Parts The manufacturer states that it will supply required parts to the operators at no cost. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA–2006– 24864; Directorate Identifier 2006–NM– 072–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 10, 2006. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–30, DC–10–30F (KDC–10), DC–10–40, and DC– 10–40F airplanes, certificated in any category; as identified in McDonnell Douglas DC–10 Service Bulletin 28–61, dated January 17, 1978. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a lightning strike, which, in combination with flammable fuel vapors, could result in arcing in the fuel tank, fuel tank explosions, and consequent loss of the airplane. sump drain collar and replace the fuel tank sump drain lockring for fuel tanks 1, 2, and 3; and reduce the length of the drain outlet barrel for the auxiliary fuel tank, as applicable; by doing all the applicable actions in accordance with the Accomplishment Instructions of McDonnell Douglas DC–10 Service Bulletin 28–61, dated January 17, 1978. (g) For airplanes identified as Group II airplanes in McDonnell Douglas DC–10 Service Bulletin 28–61, dated January 17, 1978, that are also contained in the effectivity of McDonnell Douglas DC–10 Bulletin 28–19, Revision 1, dated October 15, 1973: Before the actions in paragraph (f) of this AD, relocate the sump drain outlet for the auxiliary tank in accordance with the Accomplishment Instructions of McDonnell Douglas DC–10 Bulletin 28–19, Revision 1, dated October 15, 1973. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on May 17, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–8010 Filed 5–24–06; 8:45 am] BILLING CODE 4910–13–P 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. Corrective Actions (f) Within 60 months after the effective date of this AD: Reduce the length of the PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 $8,720 to $52,320. Prior Requirement PART 39—AIRWORTHINESS DIRECTIVES § 39.13 Fleet cost E:\FR\FM\25MYP1.SGM 25MYP1

Agencies

[Federal Register Volume 71, Number 101 (Thursday, May 25, 2006)]
[Proposed Rules]
[Pages 30086-30088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-8010]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24864; Directorate Identifier 2006-NM-072-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas airplanes, identified above. This 
proposed AD would require reducing the length of the sump drain collar 
and replacing the fuel tank sump drain lockring for fuel tanks 1, 2, 
and 3; and reducing the length of the drain outlet barrel for the 
auxiliary fuel tank, if applicable. For airplanes with an auxiliary 
fuel tank, this proposed AD also would require relocating the sump 
drain outlet to allow draining the sumps without opening the doors of 
the main landing gear wheel well. This proposed AD results from fuel 
system reviews conducted by the manufacturer. We are proposing this AD 
to reduce the potential of ignition sources inside fuel tanks in the 
event of a lightning strike, which, in combination with flammable fuel 
vapors, could result in arcing in the fuel tank, fuel tank explosions, 
and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by July 10, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., 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 the service 
information identified in this proposed AD.

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 submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24864; Directorate Identifier 2006-NM-072-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed 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 DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif 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.

[[Page 30087]]

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    Review of the lightning protection for the valve installation for 
the sump drain of the fuel tanks showed that the drain valves must be 
insulated. If the fuel level is below the drain valve body, and there 
is a lightning strike, electrical current could travel from the 
airplane skin up the sump drain collar into the valve housing. This 
condition, in combination with a lightning strike and flammable fuel 
vapors, could result in arcing in the fuel tank, fuel tank explosions, 
and consequent loss of the airplane.

Relevant Service Information

    We have reviewed McDonnell Douglas DC-10 Service Bulletin 28-61, 
dated January 17, 1978. The service bulletin describes procedures for 
reducing the length of the sump drain collar and replacing the fuel 
tank sump drain lockring for fuel tanks 1, 2, and 3 with an improved 
lockring; and reducing the length of the drain outlet barrel for the 
auxiliary fuel tank, if applicable.
    McDonnell Douglas DC-10 Service Bulletin 28-61 specifies that for 
certain airplanes, before or concurrently with the modification of the 
sump drain outlets described above, the sump drain outlet for the 
auxiliary tank must be relocated to allow draining the sumps without 
opening the doors of the main landing gear wheel well. The procedures 
for doing this action are described in McDonnell Douglas DC-10 Bulletin 
28-19, Revision 1, dated October 15, 1973. This action applies only to 
those airplanes identified as Group II in McDonnell Douglas DC-10 
Service Bulletin 28-61, that are also contained in the effectivity of 
McDonnell Douglas DC-10 Bulletin 28-19, Revision 1.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Bulletin 28-61.''

Difference Between the Proposed AD and Service Bulletin 28-61

    McDonnell Douglas DC-10 Service Bulletin 28-61 recommends doing the 
modification at the operator's convenience, which would not ensure an 
adequate level of safety for the affected fleet. In developing an 
appropriate compliance time for this AD, we considered the 
manufacturer's recommendation, the degree of urgency associated with 
the subject unsafe condition, and the average utilization of the 
affected fleet. In light of all of these factors, we find that a 
compliance time of 60 months after the effective date of this AD 
represents an appropriate interval of time for affected airplanes to 
continue to operate without compromising safety. This difference has 
been coordinated with Boeing, and Boeing concurred.

Costs of Compliance

    There are about 135 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The labor rate is $80 
per work hour.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                      Number of U.S.-
             Action                 Work hours           Parts            Cost per  airplane       registered  airplanes             Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
For all airplanes: Reduce the     3 to 15.......  $720 to $4,858.....  $960 to $6,058..........  109.....................  $104,640 to $660,322.
 length of the sump drain collar
 and replace the fuel tank sump
 drain for fuel tanks 1, 2, and
 3.
For airplanes with an auxiliary   6 to 15.......  $0 to $720.........  $480 to $1,920..........  Up to 109...............  $52,320 to $209,280.
 fuel tank: Reduce the length of
 the drain outlet barrel for the
 auxiliary fuel tank.

[[Page 30088]]

 
Prior requirement for certain     1 to 6........  The manufacturer     $80 to $480.............  Up to 109...............  $8,720 to $52,320.
 airplanes.                                        states that it
                                                   will supply
                                                   required parts to
                                                   the operators at
                                                   no cost.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this 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 that the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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, 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:

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2006-24864; Directorate Identifier 
2006-NM-072-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 10, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-10-10, DC-10-
10F, DC-10-30, DC-10-30F (KDC-10), DC-10-40, and DC-10-40F 
airplanes, certificated in any category; as identified in McDonnell 
Douglas DC-10 Service Bulletin 28-61, dated January 17, 1978.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to reduce the potential of 
ignition sources inside fuel tanks in the event of a lightning 
strike, which, in combination with flammable fuel vapors, could 
result in arcing in the fuel tank, fuel tank explosions, 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.

Corrective Actions

    (f) Within 60 months after the effective date of this AD: Reduce 
the length of the sump drain collar and replace the fuel tank sump 
drain lockring for fuel tanks 1, 2, and 3; and reduce the length of 
the drain outlet barrel for the auxiliary fuel tank, as applicable; 
by doing all the applicable actions in accordance with the 
Accomplishment Instructions of McDonnell Douglas DC-10 Service 
Bulletin 28-61, dated January 17, 1978.

Prior Requirement

    (g) For airplanes identified as Group II airplanes in McDonnell 
Douglas DC-10 Service Bulletin 28-61, dated January 17, 1978, that 
are also contained in the effectivity of McDonnell Douglas DC-10 
Bulletin 28-19, Revision 1, dated October 15, 1973: Before the 
actions in paragraph (f) of this AD, relocate the sump drain outlet 
for the auxiliary tank in accordance with the Accomplishment 
Instructions of McDonnell Douglas DC-10 Bulletin 28-19, Revision 1, 
dated October 15, 1973.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on May 17, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-8010 Filed 5-24-06; 8:45 am]
BILLING CODE 4910-13-P
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