Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes, 33262-33264 [E6-8899]

Download as PDF 33262 Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / Proposed Rules lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Fokker Services B.V.: Docket No. FAA– 2006–24959; Directorate Identifier 2005– NM–258–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 all Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category. Unsafe Condition (d) This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which, if not detected, could result in reduced structural integrity of the wing rear spar. cprice-sewell on PROD1PC66 with PROPOSALS 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. Wing Rear Spar Lower Girder Inspection/ Related Investigative/Corrective Actions (f) Within 4,000 flight hours or 21 months after the effective date of this AD, whichever occurs first: Do a detailed inspection to detect corrosion on the wing rear spar lower girder between wing STA 8700 and wing STA 9200, and do all related investigative and applicable corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100–57–038, dated April 15, 2005, except as provided by paragraphs (g) and (h) of this AD. Do all related investigative and corrective actions before further flight. If any damage found that measures more than or equal to 1.3 millimeters (mm) deep, or if the thickness of the remaining material of the rear spar lower girder is less than or equal to 2.1 mm thick, repair in accordance with a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good VerDate Aug<31>2005 14:58 Jun 07, 2006 Jkt 208001 DEPARTMENT OF TRANSPORTATION (g) If, during the accomplishment of the corrective actions required by paragraph (f) of this AD, the service bulletin specifies contacting the manufacturer for certain repair instructions: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). [Docket No. FAA–2006–24978; Directorate Identifier 2006–NM–108–AD] Reporting Inspection and Damage Results (h) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; fax +31 252 627211; e-mail Technicalservices.FokkerServices@stork.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. Use the reporting forms in Figures 3 and 4 of Fokker Service Bulletin SBF100–57–038, dated April 15, 2005. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, 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 (j) Dutch airworthiness directive NL–2005– 006, dated April 29, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on May 30, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–8897 Filed 6–7–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model 717–200 Airplanes 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 McDonnell Douglas Model 717– 200 airplanes. This proposed AD would require modifying the fuel boost pump container of the center tank. This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion. DATES: We must receive comments on this proposed AD by July 24, 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: William Bond, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; E:\FR\FM\08JNP1.SGM 08JNP1 Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / Proposed Rules telephone (562) 627–5253; 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–2006–24978; Directorate Identifier 2006–NM–108–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. cprice-sewell on PROD1PC66 with PROPOSALS 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 VerDate Aug<31>2005 14:58 Jun 07, 2006 Jkt 208001 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. Investigation by the manufacturer has revealed that during normal operation fuel exits the fuel boost pump container of the center tank, and the motor/ connector end of the fuel pump becomes uncovered by fuel. This condition has been attributed to two open pipe boss assemblies mounted on the container skin, which allows fuel to exit the container. This condition, if not corrected, could result in the fuel pump container vapor area being exposed to electrical arcing during a fuel pump PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 33263 motor case or connector burn through, which could result in a fuel tank explosion. Relevant Service Information We have reviewed Boeing Service Bulletin 717–28–0013, dated July 28, 2004. The service bulletin describes procedures for modifying the fuel boost pump container of the center tank by installing hat and cover assemblies. 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 accomplishing the modification ‘‘at a scheduled maintenance period when manpower, materials, and facilities are available, but not to exceed the next scheduled opening of the right wing fuel tank,’’ we have determined that this imprecise compliance time would not address the identified unsafe condition in a timely manner. In developing an appropriate compliance time for this AD, we considered not only the manufacturer’s recommendation, but also the degree of urgency associated with addressing the subject unsafe condition, the average utilization of the affected fleet, and the time necessary to perform the modifications. In light of all of these factors, we find a compliance time of 78 months for completing the required actions to be warranted, in that it represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. This difference has been coordinated with the airplane manufacturer. Costs of Compliance There are about 145 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. E:\FR\FM\08JNP1.SGM 08JNP1 33264 Federal Register / Vol. 71, No. 110 / Thursday, June 8, 2006 / Proposed Rules ESTIMATED COSTS Work hours Action Modification .................................................................. 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. cprice-sewell on PROD1PC66 with PROPOSALS 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. 14:58 Jun 07, 2006 2 $80 Parts Jkt 208001 Cost per airplane $1,145 Number of U.S.-registered airplanes $1,305 114 Fleet cost $148,770 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (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. PART 39—AIRWORTHINESS DIRECTIVES Issued in Renton, Washington, on May 31, 2006. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–8899 Filed 6–7–06; 8:45 am] 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 BILLING CODE 4910–13–P [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): DEPARTMENT OF TRANSPORTATION McDonnell Douglas: Docket No. FAA–2006– 24978; Directorate Identifier 2006–NM– 108–AD. 14 CFR Part 39 Comments Due Date (a) The FAA must receive comments on this AD action by July 24, 2006. Affected ADs (b) None. Regulatory Findings VerDate Aug<31>2005 Average labor rate per hour Applicability (c) This AD applies to McDonnell Douglas Model 717–200 airplanes, certificated in any category; as identified in Boeing Service Bulletin 717–28–0013, dated July 28, 2004. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion. 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. Modification (f) Within 78 months after the effective date of this AD, modify the fuel boost pump container of the center tank by doing all the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 717– 28–0013, dated July 28, 2004. 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Federal Aviation Administration [Docket No. FAA–2006–24958; Directorate Identifier 2006–NM–075–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Airplanes, Equipped With General Electric CF6–50 Series Engines 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 Airbus Model A300 airplanes. This proposed AD would require modifying the airplane and the engine/ nacelle to install a third line of defense against inadvertent deployment of the thrust reverser in flight. This proposed AD would also require two other actions that must be accomplished before or concurrently with the modification: installing a structural change in the fan cowl to avoid interference; and installing a dedicated, shielded electrical circuit. This proposed AD results from a report that the manufacturer has developed a third line of defense against the inadvertent deployment of the thrust reverser of A300 airplanes that are equipped with General Electric CF6–50 series engines (in accordance with FAA guidelines). We are proposing this AD to prevent inadvertent deployment of the thrust E:\FR\FM\08JNP1.SGM 08JNP1

Agencies

[Federal Register Volume 71, Number 110 (Thursday, June 8, 2006)]
[Proposed Rules]
[Pages 33262-33264]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-8899]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24978; Directorate Identifier 2006-NM-108-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717-200 
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 Model 717-200 airplanes. This proposed AD 
would require modifying the fuel boost pump container of the center 
tank. This proposed AD results from fuel system reviews conducted by 
the manufacturer. We are proposing this AD to prevent exposing the fuel 
pump container vapor area to electrical arcing during a fuel pump motor 
case or connector burn through, which could result in a fuel tank 
explosion.

DATES: We must receive comments on this proposed AD by July 24, 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: William Bond, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;

[[Page 33263]]

telephone (562) 627-5253; 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-
24978; Directorate Identifier 2006-NM-108-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.

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.
    Investigation by the manufacturer has revealed that during normal 
operation fuel exits the fuel boost pump container of the center tank, 
and the motor/connector end of the fuel pump becomes uncovered by fuel. 
This condition has been attributed to two open pipe boss assemblies 
mounted on the container skin, which allows fuel to exit the container. 
This condition, if not corrected, could result in the fuel pump 
container vapor area being exposed to electrical arcing during a fuel 
pump motor case or connector burn through, which could result in a fuel 
tank explosion.

Relevant Service Information

    We have reviewed Boeing Service Bulletin 717-28-0013, dated July 
28, 2004. The service bulletin describes procedures for modifying the 
fuel boost pump container of the center tank by installing hat and 
cover assemblies. 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 accomplishing the 
modification ``at a scheduled maintenance period when manpower, 
materials, and facilities are available, but not to exceed the next 
scheduled opening of the right wing fuel tank,'' we have determined 
that this imprecise compliance time would not address the identified 
unsafe condition in a timely manner. In developing an appropriate 
compliance time for this AD, we considered not only the manufacturer's 
recommendation, but also the degree of urgency associated with 
addressing the subject unsafe condition, the average utilization of the 
affected fleet, and the time necessary to perform the modifications. In 
light of all of these factors, we find a compliance time of 78 months 
for completing the required actions to be warranted, in that it 
represents an appropriate interval of time for affected airplanes to 
continue to operate without compromising safety. This difference has 
been coordinated with the airplane manufacturer.

Costs of Compliance

    There are about 145 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.

[[Page 33264]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
           Action               Work    Average labor    Parts       Cost per       registered      Fleet cost
                               hours    rate per hour                airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Modification................        2             $80     $1,145          $1,305             114        $148,770
----------------------------------------------------------------------------------------------------------------

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-2006-24978; Directorate Identifier 
2006-NM-108-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 24, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model 717-200 
airplanes, certificated in any category; as identified in Boeing 
Service Bulletin 717-28-0013, dated July 28, 2004.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent exposing the fuel 
pump container vapor area to electrical arcing during a fuel pump 
motor case or connector burn through, which could result in a fuel 
tank explosion.

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.

Modification

    (f) Within 78 months after the effective date of this AD, modify 
the fuel boost pump container of the center tank by doing all the 
actions specified in the Accomplishment Instructions of Boeing 
Service Bulletin 717-28-0013, dated July 28, 2004.

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 May 31, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-8899 Filed 6-7-06; 8:45 am]
BILLING CODE 4910-13-P
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