Airworthiness Directives; McDonnell Douglas Model DC-9-31, DC-9-32, DC-9-32F, DC-9-33F, DC-9-34, and DC-9-34F Airplanes; and Model DC-9-40 and DC-9-50 Series Airplanes, 19140-19142 [E6-5472]

Download as PDF 19140 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Proposed Rules 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 Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, International Branch, ANM–116, 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. Related Information 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: (h) Brazilian airworthiness directive 2006– 02–01, dated February 24, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on April 5, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–5474 Filed 4–12–06; 8:45 am] Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Modification (f) Within 2,500 flight hours after the effective date of this AD, modify the flap system interface wiring, by accomplishing all of the actions specified in the Accomplishment Instructions of EMBRAER Service Bulletin 145–27–0113, dated December 6, 2005. [Amended] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Federal Aviation Administration 14 CFR Part 39 Empresa Brasileira de Aeronautica S.A. (EMBRAER): Docket No. FAA–2006– 24439; Directorate Identifier 2006-NM– 039–AD. [Docket No. FAA–2006–24430; Directorate Identifier 2006–NM–048–AD] Comments Due Date (a) The FAA must receive comments on this AD action by May 15, 2006. Airworthiness Directives; McDonnell Douglas Model DC–9–31, DC–9–32, DC–9–32F, DC–9–33F, DC–9–34, and DC–9–34F Airplanes; and Model DC–9– 40 and DC–9–50 Series Airplanes Affected ADs (b) None. hsrobinson on PROD1PC68 with PROPOSALS Applicability (c) This AD applies to EMBRAER Model EMB–145XR airplanes, certificated in any category; as identified in EMBRAER Service Bulletin 145–27–0113, dated December 6, 2005. Unsafe Condition (d) This AD results from a finding that the aural and visual warnings, which should be activated when the flaps are set to 22 degrees during takeoff, were not enabled during the manufacture of certain Model EMB–145XR airplanes. We are issuing this AD to prevent overrunning the runway during takeoff. 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. VerDate Aug<31>2005 15:29 Apr 12, 2006 Jkt 208001 RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain transport category airplanes, identified above. This proposed AD would require installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/corrective actions. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 tank, could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by May 30, 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–2006–24430; Directorate Identifier 2006–NM–048–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 E:\FR\FM\13APP1.SGM 13APP1 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Proposed Rules 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. hsrobinson on PROD1PC68 with PROPOSALS 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. VerDate Aug<31>2005 15:29 Apr 12, 2006 Jkt 208001 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. We have received a report indicating that, on certain McDonnell Douglas Model DC–9 airplanes with a 580-gallon forward auxiliary fuel tank, the volute of the fuel boost pump is bonded to the inlet basket assembly but not to the tank structure. At the pump run-out fuel level, the pump, which receives 155VAC power, is uncovered and there is fuel vapor in the area. Installing a new bonding jumper will minimize the possibilities of point-contact arcing or filament heating in the fuel tank which, in the event of a short or ground fault condition, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Service Bulletin DC9–28–214, dated December 16, 2005. The service bulletin describes procedures for installing a bonding jumper from the boost pump volute to the fuel tank structure. The installation includes the related investigative and corrective actions of testing the bonding between the jumper and the pump mounting lug, between the clip and the lower stanchion support stud, and between the jumper and the clip, to verify that the resistance is less than 2.5 milliohms; and reworking, if necessary, until the resistance is less than 2.5 milliohms. 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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 19141 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 the Service Bulletin.’’ Difference Between the Proposed AD and the Service Bulletin Although the service bulletin recommends doing the installation at the next scheduled fuel tank entry, but not to exceed 10 years, we have determined that interval would not address the identified unsafe condition soon enough to ensure an adequate level of safety for the affected fleet. In developing an appropriate compliance time for this AD, we considered the degree of urgency associated with the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to do the installation. In light of all of these factors, we find that a compliance time of 60 months represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. This difference has been coordinated with Boeing. Costs of Compliance There are about 250 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 152 airplanes of U.S. registry. The proposed actions would take about 9 work hours per airplane, at an average labor rate of $80 per work hour. Required parts would cost about $2,385 per airplane. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $471,960, or $3,105 per airplane. 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 E:\FR\FM\13APP1.SGM 13APP1 19142 Federal Register / Vol. 71, No. 71 / Thursday, April 13, 2006 / Proposed Rules 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: DC–9–51 airplanes, certificated in any category; as identified in Boeing Service Bulletin DC9–28–214, dated December 16, 2005. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel tank, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation (f) Within 60 months after the effective date of this AD, install a bonding jumper from the boost pump volute to the fuel tank structure, and do all applicable related investigative and corrective actions before further flight; by doing all the actions specified in the Accomplishment Instructions of Boeing Service Bulletin DC9– 28–214, dated December 16, 2005. Alternative Methods of Compliance (AMOCs) (g)(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 April 4, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–5472 Filed 4–12–06; 8:45 am] BILLING CODE 4910–13–P Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 DEPARTMENT OF TRANSPORTATION [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): hsrobinson on PROD1PC68 with PROPOSALS McDonnell Douglas: Docket No. FAA–2006– 24430; Directorate Identifier 2006–NM– 048–AD. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24440; Directorate Identifier 2006–NM–058–AD] RIN 2120–AA64 Comments Due Date (a) The FAA must receive comments on this AD action by May 30, 2006. Affected ADs (b) None. Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–145XR Airplanes AGENCY: Applicability (c) This AD applies to McDonnell Douglas Model DC–9–31, DC–9–32, DC–9–32F, DC– 9–33F, DC–9–34, DC–9–34F, DC–9–41, and VerDate Aug<31>2005 15:29 Apr 12, 2006 Jkt 208001 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain EMBRAER Model EMB–145XR airplanes. This proposed AD would require replacement of certain segments of the passenger seat tracks with new, improved seat tracks. This proposed AD results from instances where the shear plungers of the passenger seat legs were not adequately fastened. We are proposing this AD to prevent inadequate fastening of the seat leg shear plungers, which could result in failure of the passenger seat tracks during emergency landing conditions and consequent injury to passengers. DATES: We must receive comments on this proposed AD by May 15, 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–2125. 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–2006–24440; Directorate Identifier 2006–NM–058–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 E:\FR\FM\13APP1.SGM 13APP1

Agencies

[Federal Register Volume 71, Number 71 (Thursday, April 13, 2006)]
[Proposed Rules]
[Pages 19140-19142]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-5472]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24430; Directorate Identifier 2006-NM-048-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-31, DC-9-
32, DC-9-32F, DC-9-33F, DC-9-34, and DC-9-34F Airplanes; and Model DC-
9-40 and DC-9-50 Series 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 transport category airplanes, identified above. This 
proposed AD would require installing a bonding jumper from the boost 
pump volute to the fuel tank structure, and related investigative/
corrective actions. This proposed AD results from fuel system reviews 
conducted by the manufacturer. We are proposing this AD to prevent 
point-contact arcing or filament heating in the fuel tank, which, in 
the event of a short or ground fault inside the fuel tank, could result 
in a fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by May 30, 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-
24430; Directorate Identifier 2006-NM-048-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

[[Page 19141]]

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.

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.
    We have received a report indicating that, on certain McDonnell 
Douglas Model DC-9 airplanes with a 580-gallon forward auxiliary fuel 
tank, the volute of the fuel boost pump is bonded to the inlet basket 
assembly but not to the tank structure. At the pump run-out fuel level, 
the pump, which receives 155VAC power, is uncovered and there is fuel 
vapor in the area. Installing a new bonding jumper will minimize the 
possibilities of point-contact arcing or filament heating in the fuel 
tank which, in the event of a short or ground fault condition, could 
result in a fuel tank explosion and consequent loss of the airplane.

Relevant Service Information

    We have reviewed Boeing Service Bulletin DC9-28-214, dated December 
16, 2005. The service bulletin describes procedures for installing a 
bonding jumper from the boost pump volute to the fuel tank structure. 
The installation includes the related investigative and corrective 
actions of testing the bonding between the jumper and the pump mounting 
lug, between the clip and the lower stanchion support stud, and between 
the jumper and the clip, to verify that the resistance is less than 2.5 
milliohms; and reworking, if necessary, until the resistance is less 
than 2.5 milliohms. 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 the Service Bulletin.''

Difference Between the Proposed AD and the Service Bulletin

    Although the service bulletin recommends doing the installation at 
the next scheduled fuel tank entry, but not to exceed 10 years, we have 
determined that interval would not address the identified unsafe 
condition soon enough to ensure an adequate level of safety for the 
affected fleet. In developing an appropriate compliance time for this 
AD, we considered the degree of urgency associated with the subject 
unsafe condition, the average utilization of the affected fleet, and 
the time necessary to do the installation. In light of all of these 
factors, we find that a compliance time of 60 months represents an 
appropriate interval of time for affected airplanes to continue to 
operate without compromising safety. This difference has been 
coordinated with Boeing.

Costs of Compliance

    There are about 250 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 152 airplanes of 
U.S. registry. The proposed actions would take about 9 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost about $2,385 per airplane. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $471,960, or 
$3,105 per airplane.

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

[[Page 19142]]

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-2006-24430; Directorate Identifier 
2006-NM-048-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 30, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-9-31, DC-9-32, 
DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-41, and DC-9-51 
airplanes, certificated in any category; as identified in Boeing 
Service Bulletin DC9-28-214, dated December 16, 2005.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent point-contact arcing 
or filament heating in the fuel tank, which, in the event of a short 
or ground fault inside the fuel tank, could result in a fuel tank 
explosion and consequent loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Installation

    (f) Within 60 months after the effective date of this AD, 
install a bonding jumper from the boost pump volute to the fuel tank 
structure, and do all applicable related investigative and 
corrective actions before further flight; by doing all the actions 
specified in the Accomplishment Instructions of Boeing Service 
Bulletin DC9-28-214, dated December 16, 2005.

Alternative Methods of Compliance (AMOCs)

    (g)(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 April 4, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service. 9
 [FR Doc. E6-5472 Filed 4-12-06; 8:45 am]
BILLING CODE 4910-13-P
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