Airworthiness Directives; McDonnell Douglas Model MD-11, MD-11F, DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes, 29447-29449 [E7-10215]

Download as PDF Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules for a location to examine the regulatory evaluation. Costs of Compliance There are about 757 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 575 airplanes of U.S. registry. The proposed actions would take about 10 work hours per airplane, at an average labor rate of $80 per work hour. Required parts would cost about $400 per airplane. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $690,000, or $1,200 per airplane. List of Subjects in 14 CFR Part 39 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. rwilkins on PROD1PC63 with PROPOSALS the service information described previously. 1. The authority citation for part 39 continues to read as follows: 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 VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 29447 Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Wichita 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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on May 22, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10216 Filed 5–25–07; 8:45 am] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): BILLING CODE 4910–13–P Raytheon Aircraft Company (Formerly Beech): Docket No. FAA–2007–28308; Directorate Identifier 2007–NM–016–AD. Federal Aviation Administration Comments Due Date [Docket No. FAA–2007–28301; Directorate Identifier 2007–NM–061–AD] (a) The FAA must receive comments on this AD action by July 13, 2007. DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 RIN 2120–AA64 Affected ADs (b) None. Applicability (c) This AD applies to Raytheon (Beech) Model 400, 400A, and 400T series airplanes, certificated in any category; as identified in Raytheon Service Bulletin SB 54–3788, dated December, 2006. Unsafe Condition (d) This AD results from several reports of loose attachment fasteners found on the engine cowling panels, and subsequently the panels either peeling back or separating from the airplane during flight. We are issuing this AD to prevent failure of the attachment fasteners on the engine cowling panels, which could result in separation of a panel from the airplane, and consequent damage to airplane structure. These conditions could adversely affect continued safe flight and landing of the airplane, or cause injury to people or damage to property on the ground. 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 200 flight hours after the effective date of this AD: Modify the attachment fasteners on the engine cowling panels by doing all the actions in accordance with the Accomplishment Instructions of Raytheon Service Bulletin SB 54–3788, dated December, 2006. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Airworthiness Directives; McDonnell Douglas Model MD–11, MD–11F, DC– 10–10, DC–10–10F, DC–10–15, DC–10– 30 and DC–10–30F (KC–10A and KDC– 10), DC–10–40, DC–10–40F, MD–10– 10F, and MD–10–30F 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 all McDonnell Douglas Model MD–11 and MD–11F airplanes and certain Model DC–10–10, DC–10–10F, DC–10–15, DC– 10–30 and DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD– 10–10F, and MD–10–30F airplanes. This proposed AD would require rerouting system 3 hydraulic piping, installing new pipe assemblies and unions, and installing redesigned support brackets for the system 3 hydraulic piping. This proposed AD results from a report of damage to the hydraulic system that occurred when pieces of a ruptured tire from the left main landing gear penetrated the wing trailing edge access panel during takeoff. We are proposing this AD to prevent damage to the system 3 hydraulic piping, which could result in loss of the hydraulic system. E:\FR\FM\29MYP1.SGM 29MYP1 29448 Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules We must receive comments on this proposed AD by July 13, 2007. 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, CA 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024), for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin Safety/Mechanical and Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; telephone (562) 627– 5353; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: DATES: 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–2007–28301; Directorate Identifier 2007–NM–061–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 We have received a report of damage to the hydraulic system that occurred when pieces of a ruptured tire from the left main landing gear (MLG) penetrated the wing trailing edge access panel during takeoff. During the incident, hydraulic piping routed in the wing trailing edge was damaged, which resulted in the loss of two of the three hydraulic systems. Boeing’s analysis of the hydraulic piping for systems 1, 2, and 3, in the area above the left and right wing MLG tires, revealed the need to enhance the protection of the system 3 hydraulic pipes. Rerouting and installing thicker-walled system 3 hydraulic piping in the wing trailing edge areas will enhance the protection of the hydraulic pipes in the event of an MLG tireburst. If not corrected, damage to the system 3 hydraulic piping could result in possible loss of the hydraulic system. Relevant Service Information We have reviewed Boeing Alert Service Bulletin DC10–29A147, dated February 9, 2007; and Boeing Alert Service Bulletin MD11–29A068, Revision 1, dated February 9, 2007. The service bulletins describe procedures for rerouting system 3 hydraulic piping, installing new pipe assemblies and unions, and installing redesigned support brackets for the system 3 hydraulic piping. 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. Costs of Compliance There are about 430 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. ESTIMATED COSTS Work hours Average labor rate per hour rwilkins on PROD1PC63 with PROPOSALS 60 ........................................... $80 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, VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 Number of U.S.-registered airplanes Parts Cost per airplane $14,020 to $14,620 ................ $18,820 to $19,420 ................ 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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 260 Fleet cost $4,893,200 to $5,049,200. 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 E:\FR\FM\29MYP1.SGM 29MYP1 Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / Proposed Rules 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. § 39.13 [Amended] rwilkins on PROD1PC63 with PROPOSALS 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): McDonnell Douglas: Docket No. FAA–2007– 28301; Directorate Identifier 2007–NM– 061–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 13, 2007. Affected ADs (b) None. VerDate Aug<31>2005 18:04 May 25, 2007 Jkt 211001 Applicability 29449 Issued in Renton, Washington, on May 21, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10215 Filed 5–25–07; 8:45 am] (c) This AD applies to the following McDonnell Douglas airplanes, certificated in any category: (1) All Model MD–11 and MD–11F airplanes. (2) DC–10–10, DC–10–10F, DC–10–15, DC– 10–30 and DC–10–30F (KC–10A and KDC– 10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes; as identified in Boeing Alert Service Bulletin DC10–29A147, dated February 9, 2007. BILLING CODE 4910–13–P Unsafe Condition 14 CFR Part 39 (d) This AD results from a report of damage to the hydraulic system that occurred when pieces of a ruptured tire from the left main landing gear penetrated the wing trailing edge access panel during takeoff. We are issuing this AD to prevent damage to the system 3 hydraulic piping, which could result in loss of the hydraulic system. [Docket No. FAA–2007–28300; Directorate Identifier 2006–NM–292–AD] 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 24 months after the effective date of this AD, reroute system hydraulic piping, install new pipe assemblies and unions, and install redesigned support brackets for system 3 hydraulic piping. Do these actions in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin MD11–29A068, Revision 1, dated February 9, 2007 (for Model MD–11 and MD–11F airplanes), or McDonnell Douglas Service Bulletin DC10– 29A147, dated February 9, 2007 (for Model DC–10–10, DC–10–10F, DC–10–15, DC–10– 30 and DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes). (g) Accomplishment before the effective date of this AD of the modification required by paragraph (f) of this AD in accordance with McDonnell Douglas Alert Service Bulletin MD11–29A068, dated January 23, 2007, is acceptable for compliance with the requirements of paragraph (f) of this AD. 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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The Chromic Acid Anodising (CAA) Lead Fleet Program was established in 1989 to observe corrosion/debonding behaviour of CAA-treated panels. CAA lead fleet includes the inspection of lap joints, circumferential joints, stringers and doublers on selected aircraft. The findings in combination with analytical corrosion investigations have been analysed by the TC (type certificate) holder and an appropriate inspection program for debonding has been developed. This airworthiness directive requires inspection of the concerned areas to detect any corrosion and/or debonding which could affect the structural integrity. * * * The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by June 28, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. E:\FR\FM\29MYP1.SGM 29MYP1

Agencies

[Federal Register Volume 72, Number 102 (Tuesday, May 29, 2007)]
[Proposed Rules]
[Pages 29447-29449]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10215]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28301; Directorate Identifier 2007-NM-061-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11, MD-11F, 
DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-
10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 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 all McDonnell Douglas Model MD-11 and MD-11F airplanes and certain 
Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and 
KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes. This 
proposed AD would require rerouting system 3 hydraulic piping, 
installing new pipe assemblies and unions, and installing redesigned 
support brackets for the system 3 hydraulic piping. This proposed AD 
results from a report of damage to the hydraulic system that occurred 
when pieces of a ruptured tire from the left main landing gear 
penetrated the wing trailing edge access panel during takeoff. We are 
proposing this AD to prevent damage to the system 3 hydraulic piping, 
which could result in loss of the hydraulic system.

[[Page 29448]]


DATES: We must receive comments on this proposed AD by July 13, 2007.

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, CA 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024), for the service information 
identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin 
Safety/Mechanical and Environmental Systems Branch, ANM-150L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, CA 90712-4137; telephone (562) 627-5353; 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-2007-
28301; Directorate Identifier 2007-NM-061-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

    We have received a report of damage to the hydraulic system that 
occurred when pieces of a ruptured tire from the left main landing gear 
(MLG) penetrated the wing trailing edge access panel during takeoff. 
During the incident, hydraulic piping routed in the wing trailing edge 
was damaged, which resulted in the loss of two of the three hydraulic 
systems. Boeing's analysis of the hydraulic piping for systems 1, 2, 
and 3, in the area above the left and right wing MLG tires, revealed 
the need to enhance the protection of the system 3 hydraulic pipes. 
Rerouting and installing thicker-walled system 3 hydraulic piping in 
the wing trailing edge areas will enhance the protection of the 
hydraulic pipes in the event of an MLG tireburst. If not corrected, 
damage to the system 3 hydraulic piping could result in possible loss 
of the hydraulic system.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC10-29A147, dated 
February 9, 2007; and Boeing Alert Service Bulletin MD11-29A068, 
Revision 1, dated February 9, 2007. The service bulletins describe 
procedures for rerouting system 3 hydraulic piping, installing new pipe 
assemblies and unions, and installing redesigned support brackets for 
the system 3 hydraulic piping. 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.

Costs of Compliance

    There are about 430 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.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                               Number of
                                 Average                         Cost per        U.S.-
          Work hours            labor rate       Parts           airplane      registered        Fleet cost
                                 per hour                                      airplanes
----------------------------------------------------------------------------------------------------------------
60...........................          $80  $14,020 to       $18,820 to               260  $4,893,200 to
                                             $14,620.         $19,420.                      $5,049,200.
----------------------------------------------------------------------------------------------------------------

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

[[Page 29449]]

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-2007-28301; Directorate Identifier 
2007-NM-061-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 13, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following McDonnell Douglas 
airplanes, certificated in any category:
    (1) All Model MD-11 and MD-11F airplanes.
    (2) DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-
10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 
airplanes; as identified in Boeing Alert Service Bulletin DC10-
29A147, dated February 9, 2007.

Unsafe Condition

    (d) This AD results from a report of damage to the hydraulic 
system that occurred when pieces of a ruptured tire from the left 
main landing gear penetrated the wing trailing edge access panel 
during takeoff. We are issuing this AD to prevent damage to the 
system 3 hydraulic piping, which could result in loss of the 
hydraulic system.

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 24 months after the effective date of this AD, 
reroute system hydraulic piping, install new pipe assemblies and 
unions, and install redesigned support brackets for system 3 
hydraulic piping. Do these actions in accordance with the 
Accomplishment Instructions of McDonnell Douglas Service Bulletin 
MD11-29A068, Revision 1, dated February 9, 2007 (for Model MD-11 and 
MD-11F airplanes), or McDonnell Douglas Service Bulletin DC10-
29A147, dated February 9, 2007 (for Model DC-10-10, DC-10-10F, DC-
10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-
40F, MD-10-10F, and MD-10-30F airplanes).
    (g) Accomplishment before the effective date of this AD of the 
modification required by paragraph (f) of this AD in accordance with 
McDonnell Douglas Alert Service Bulletin MD11-29A068, dated January 
23, 2007, is acceptable for compliance with the requirements of 
paragraph (f) of this AD.

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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on May 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10215 Filed 5-25-07; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.