Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes, 43022-43024 [05-14392]

Download as PDF 43022 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations (1) For airplanes with 19,000 total flight cycles or less as of the effective date of this AD: Prior to the accumulation of 8,000 total flight cycles or within 2,000 flight cycles after the effective date of this AD, whichever is later, not to exceed 20,000 total flight cycles. (2) For airplanes with more than 19,000 total flight cycles as of the effective date of this AD: Within 1,000 flight cycles after the effective date of this AD. 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 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.’’ Repair (g) If any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, repair the affected stringer in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003. Repair terminates the repetitive inspections required by paragraph (f) of this AD for only the repaired stringer/frame location. Optional Terminating Action (h) Installing new frame clips and new doublers, and repairing as applicable, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003, terminates the repetitive inspections required by this AD. Alternative Methods of Compliance (AMOCs) (i) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 747–53A2484, dated June 26, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. VerDate jul<14>2003 23:50 Jul 25, 2005 Jkt 205001 Issued in Renton, Washington, on July 13, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–14396 Filed 7–25–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2001–NM–359–AD; Amendment 39–14201; AD 2005–15–12] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC– 10A and KDC–10), DC–10–40, DC–10– 40F, MD–10–10F, MD–10–30F, MD–11, and MD–11F Airplanes Federal Aviation Administration, Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC– 10A and KDC–10), DC–10–40, DC–10– 40F, MD–10–10F, MD–10–30F, MD–11, and MD–11F airplanes, that requires performing a functional test of the exterior emergency control handle assemblies of the forward passenger doors, and corrective actions, if necessary. This action is necessary to prevent failure of the forward passenger doors to operate properly in an emergency condition, which could delay an emergency evacuation and possibly result in injury to passengers and flightcrew. This action is intended to address the identified unsafe condition. Effective August 30, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 30, 2005. ADDRESSES: The service information referenced in this AD may be obtained from Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024). This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at DATES: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California. 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, California 90712–4137; telephone (562) 627–5353; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC– 10A and KDC–10), DC–10–40, DC–10– 40F, MD–10–10F, MD–10–30F, MD–11, and MD–11F airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on April 22, 2005 (70 FR 20842). That action proposed to require performing a functional test of the exterior emergency control handle assemblies of the forward passenger doors, and corrective actions, if necessary. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. Request To Change Description of Functional Test Criteria One commenter requests that we revise certain criteria in the functional test description from ‘‘noisy operation or binding’’ to ‘‘binding.’’ The commenter asserts that ‘‘noisy operation’’ is not quantifiable and should not be used to define acceptable parameters of door operation. The commenter states that ‘‘binding’’ is a quantifiable metric that is sufficient to determine satisfactory door operation. We do not agree with this request. Despite the commenter’s assertion, ‘‘noisy operation’’ is a test parameter that is widely used to determine proper operation of mechanisms. If a mechanism is soundless or has a sound that is typical when operating in an acceptable manner, any such mechanism which produces an unusual sound when operated requires investigation to determine if it is in need of repair. In this case, the check for ‘‘noisy operation’’ within the functional test procedure is intended to reveal whether or not a door is approaching a binding condition and requires replacing the steel bearings with E:\FR\FM\26JYR1.SGM 26JYR1 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations bearings made from corrosion-resistant material as specified in the service information. We have not changed the final rule in this regard. Explanation of Change to Table Designation The table in paragraph (c) of the proposed AD was erroneously identified as ‘‘Table 2—Boeing Service Bulletins.’’ In fact, there is only one table in the proposed AD; therefore, we have reidentified this table as ‘‘Table 1— Boeing Service Bulletins’’ in paragraph (c) of the final rule. This change has no effect on the technical content of this AD or on the determination of the cost to the public. Explanation of Change to Service Information Citations The Boeing service information was not cited properly in paragraph (a) of the proposed AD; those citations were incomplete. Therefore, so operators can determine which service bulletin applies to which affected airplanes, we have included complete citations for Boeing Service Bulletin MD11–52–046, Revision 3, dated October 27, 2004; and Boeing Service Bulletin DC10–52–221, Revision 2, dated October 27, 2004; in paragraph (a) of the final rule. Conclusion After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed, except with the changes discussed above. Cost Impact There are approximately 604 airplanes of the affected design in the worldwide fleet. The FAA estimates that 396 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $25,740, or $65 per airplane, per operation. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, VerDate jul<14>2003 23:50 Jul 25, 2005 Jkt 205001 planning time, or time necessitated by other administrative actions. PART 39—AIRWORTHINESS DIRECTIVES Authority for This Rulemaking 43023 I 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 Impact The regulations adopted herein will 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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. Section 39.13 is amended by adding the following new airworthiness directive: I 2005–15–12 McDonnell Douglas: Amendment 39–14201. Docket 2001– NM–359–AD. Applicability: Model MD–11 and MD–11F airplanes; as identified in Boeing Service Bulletin MD11–52–046, Revision 3, dated October 27, 2004; and Model DC–10–10, DC– 10–10F, DC–10–15, DC–10–30, 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 Service Bulletin DC10–52–221, Revision 2, dated October 27, 2004; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the forward passenger doors to operate properly in an emergency condition, which could delay an emergency evacuation and possibly result in injury to passengers and flightcrew, accomplish the following: Functional Test (a) Within 6,000 flight hours or 18 months after the effective date of this AD, whichever occurs later, perform a functional test of the exterior emergency control handle assemblies of the forward passenger doors, by doing all actions specified in Accomplishment Instructions of Boeing Service Bulletin MD11–52–046, Revision 3, dated October 27, 2004 (for Model MD–11 and MD–11F airplanes); or Boeing Service Bulletin DC10– 52–221, Revision 2, dated October 27, 2004 (for Model DC–10–10, DC–10–10F, DC–10– 15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10– 10F, and MD–10–30F airplanes); as applicable. (1) If the functional test reveals no noisy operation or binding: At intervals not to exceed 6,000 flight hours or 18 months, whichever occurs later, repeat the functional test until the terminating action of paragraph (b) of this AD has been accomplished. (2) If any functional test required by this AD reveals noisy operation or binding: Prior to further flight, replace the steel bearings with bearings made from corrosion-resistant material, in accordance with the applicable service bulletin. Optional Terminating Action (b) Accomplishment of the actions required by paragraph (a)(2) of this AD constitutes terminating action for the repetitive tests required by paragraph (a)(1) of this AD. Actions Accomplished per Previous Issues of Service Bulletins (c) Actions accomplished before the effective date of this AD in accordance with the Boeing service bulletins listed in Table 1 of this AD are considered acceptable for E:\FR\FM\26JYR1.SGM 26JYR1 43024 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations compliance with the requirements of paragraph (a) of this AD. TABLE 1.—BOEING SERVICE BULLETINS Boeing service bulletin DC10–52–221 DC10–52–221 MD11–52–046 MD11–52–046 MD11–52–046 .............................................................................................................................................. .............................................................................................................................................. .............................................................................................................................................. .............................................................................................................................................. .............................................................................................................................................. Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION (d) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions must be done in accordance with Boeing Service Bulletin DC10–52–221, Revision 2, dated October 27, 2004; or Boeing Service Bulletin MD11–52–046, Revision 3, dated October 27, 2004, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024). To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Effective Date (f) This amendment becomes effective on August 30, 2005. Issued in Renton, Washington, on July 14, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–14392 Filed 7–25–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 Revision 23:50 Jul 25, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21023; Directorate Identifier 2004–NM–262–AD; Amendment 39–14196; AD 2005–15–07] RIN 2120–AA64 Airworthiness Directives; Airbus Model A320–111 Airplanes and Model A320– 200 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320–111 airplanes and Model A320–200 series airplanes. This AD requires installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent injection of high voltage current into the low voltage wiring that passes through the fuel tanks, which could result in a possible fuel tank explosion. DATES: Effective August 30, 2005. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 30, 2005. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Date of issue Original ............. 01 ..................... Original ............. 01 ..................... 02 ..................... November 5, 2001. May 6, 2002. November 5, 2001. May 6, 2002. October 8, 2002. Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A320– 111 airplanes and Model A320–200 series airplanes. That NPRM was published in the Federal Register on April 21, 2005 (70 FR 20724). That NPRM proposed to require installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the NPRM. Support for the Proposed AD One commenter supports the NPRM. Explanation of Change to Applicability We have revised the applicability of this AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data, including the comment that has been received, and determined that air safety and the public interest require adopting the AD with the change described above. E:\FR\FM\26JYR1.SGM 26JYR1

Agencies

[Federal Register Volume 70, Number 142 (Tuesday, July 26, 2005)]
[Rules and Regulations]
[Pages 43022-43024]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-14392]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-359-AD; Amendment 39-14201; AD 2005-15-12]
RIN 2120-AA64

Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40,
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes

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

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-
10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F,
MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes, that requires
performing a functional test of the exterior emergency control handle
assemblies of the forward passenger doors, and corrective actions, if
necessary. This action is necessary to prevent failure of the forward
passenger doors to operate properly in an emergency condition, which
could delay an emergency evacuation and possibly result in injury to
passengers and flightcrew. This action is intended to address the
identified unsafe condition.

DATES: Effective August 30, 2005.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 30, 2005.

ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024). This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California.

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, California 90712-4137; telephone (562) 627-5353; fax (562)
627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10),
DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes
was published as a supplemental notice of proposed rulemaking (NPRM) in
the Federal Register on April 22, 2005 (70 FR 20842). That action
proposed to require performing a functional test of the exterior
emergency control handle assemblies of the forward passenger doors, and
corrective actions, if necessary.

Comments

Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.

Request To Change Description of Functional Test Criteria

One commenter requests that we revise certain criteria in the
functional test description from ``noisy operation or binding'' to
``binding.'' The commenter asserts that ``noisy operation'' is not
quantifiable and should not be used to define acceptable parameters of
door operation. The commenter states that ``binding'' is a quantifiable
metric that is sufficient to determine satisfactory door operation.
We do not agree with this request. Despite the commenter's
assertion, ``noisy operation'' is a test parameter that is widely used
to determine proper operation of mechanisms. If a mechanism is
soundless or has a sound that is typical when operating in an
acceptable manner, any such mechanism which produces an unusual sound
when operated requires investigation to determine if it is in need of
repair. In this case, the check for ``noisy operation'' within the
functional test procedure is intended to reveal whether or not a door
is approaching a binding condition and requires replacing the steel
bearings with

[[Page 43023]]

bearings made from corrosion-resistant material as specified in the
service information. We have not changed the final rule in this regard.

Explanation of Change to Table Designation

The table in paragraph (c) of the proposed AD was erroneously
identified as ``Table 2--Boeing Service Bulletins.'' In fact, there is
only one table in the proposed AD; therefore, we have reidentified this
table as ``Table 1--Boeing Service Bulletins'' in paragraph (c) of the
final rule. This change has no effect on the technical content of this
AD or on the determination of the cost to the public.

Explanation of Change to Service Information Citations

The Boeing service information was not cited properly in paragraph
(a) of the proposed AD; those citations were incomplete. Therefore, so
operators can determine which service bulletin applies to which
affected airplanes, we have included complete citations for Boeing
Service Bulletin MD11-52-046, Revision 3, dated October 27, 2004; and
Boeing Service Bulletin DC10-52-221, Revision 2, dated October 27,
2004; in paragraph (a) of the final rule.

Conclusion

After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed, except with the
changes discussed above.

Cost Impact

There are approximately 604 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 396 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 1 work
hour per airplane to accomplish the required actions, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$25,740, or $65 per airplane, per operation.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.

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 Impact

The regulations adopted herein will 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness
directive:

2005-15-12 McDonnell Douglas: Amendment 39-14201. Docket 2001-NM-
359-AD.

Applicability: Model MD-11 and MD-11F airplanes; as identified
in Boeing Service Bulletin MD11-52-046, Revision 3, dated October
27, 2004; and Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, 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 Service Bulletin DC10-52-221,
Revision 2, dated October 27, 2004; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the forward passenger doors to operate
properly in an emergency condition, which could delay an emergency
evacuation and possibly result in injury to passengers and
flightcrew, accomplish the following:

Functional Test

(a) Within 6,000 flight hours or 18 months after the effective
date of this AD, whichever occurs later, perform a functional test
of the exterior emergency control handle assemblies of the forward
passenger doors, by doing all actions specified in Accomplishment
Instructions of Boeing Service Bulletin MD11-52-046, Revision 3,
dated October 27, 2004 (for Model MD-11 and MD-11F airplanes); or
Boeing Service Bulletin DC10-52-221, Revision 2, dated October 27,
2004 (for Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F
(KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F
airplanes); as applicable.
(1) If the functional test reveals no noisy operation or
binding: At intervals not to exceed 6,000 flight hours or 18 months,
whichever occurs later, repeat the functional test until the
terminating action of paragraph (b) of this AD has been
accomplished.
(2) If any functional test required by this AD reveals noisy
operation or binding: Prior to further flight, replace the steel
bearings with bearings made from corrosion-resistant material, in
accordance with the applicable service bulletin.

Optional Terminating Action

(b) Accomplishment of the actions required by paragraph (a)(2)
of this AD constitutes terminating action for the repetitive tests
required by paragraph (a)(1) of this AD.

Actions Accomplished per Previous Issues of Service Bulletins

(c) Actions accomplished before the effective date of this AD in
accordance with the Boeing service bulletins listed in Table 1 of
this AD are considered acceptable for

[[Page 43024]]

compliance with the requirements of paragraph (a) of this AD.

Table 1.--Boeing service bulletins
----------------------------------------------------------------------------------------------------------------
Boeing service bulletin Revision Date of issue
----------------------------------------------------------------------------------------------------------------
DC10-52-221............................. Original........................ November 5, 2001.
DC10-52-221............................. 01.............................. May 6, 2002.
MD11-52-046............................. Original........................ November 5, 2001.
MD11-52-046............................. 01.............................. May 6, 2002.
MD11-52-046............................. 02.............................. October 8, 2002.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance

(d) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.

Incorporation by Reference

(e) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Service Bulletin DC10-52-221,
Revision 2, dated October 27, 2004; or Boeing Service Bulletin MD11-
52-046, Revision 3, dated October 27, 2004, as applicable. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. To get copies of this service information, contact Boeing
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Data and Service
Management, Dept. C1-L5A (D800-0024). To inspect copies of this
service information, go to the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or to the FAA, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or to the National Archives and Records
Administration (NARA). For information on the availability of this
material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Effective Date

(f) This amendment becomes effective on August 30, 2005.

Issued in Renton, Washington, on July 14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-14392 Filed 7-25-05; 8:45 am]
BILLING CODE 4910-13-P

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