Airworthiness Directives; McDonnell Douglas Model MD-90-30 Airplanes, 52203-52205 [E8-20494]

Download as PDF Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations balance land for cracks in accordance with Rolls-Royce RB211 Propulsion System Alert Non Modification Service Bulletin RB.211– 72–AF313, dated February 22, 2007 section 3 Accomplishment Instructions. Engines on which cracking is found should be rejected from service. Inspection—In-Shop (2) Applicable to RR Trent 500, 700 and 800 engines at each shop visit in which the engine is sufficiently disassembled to access the IP Compressor Module rear face: Inspect the IP Compressor rotor rear balance land for cracks in accordance with Rolls-Royce RB211 Propulsion System Alert Non Modification Service Bulletin RB.211–72–AF260, Revision 2, dated July 4, 2007; or earlier issue section 3 Accomplishment Instructions. Other FAA AD Provisions (f) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) Refer to EASA Airworthiness Directive 2007–0052, dated February 23, 2007, for related information. (h) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (i) You must use the service information specified in Table 1 of this AD to do the 52203 actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone: 44 (0) 1332–242424; fax: 44 (0) 1332–249936. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 1—MATERIAL INCORPORATED BY REFERENCE Alert Service Bulletin No. RB.211–72–AF260; RB.211–72–AF260; RB.211–72–AF260; RB.211–72–AF313; Total Total Total Total pages—11 pages—11 pages—11 pages—11 Page .................................. .................................. .................................. .................................. Issued in Burlington, Massachusetts, on August 25, 2008. Mark A. Rumizen, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–20212 Filed 9–8–08; 8:45 am] ALL ALL ALL ALL ....................................... ....................................... ....................................... ....................................... This AD is effective September 24, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 24, 2008. We must receive comments on this AD by November 10, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and DATES: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0946; Directorate Identifier 2008–NM–147–AD; Amendment 39–15667; AD 2008–18–10] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model MD–90–30 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. yshivers on PROD1PC62 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD–90–30 airplanes. This AD requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fitting of the left and right engines and corrective actions if necessary. This AD results from reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to 15:16 Sep 08, 2008 Jkt 214001 Original ................................. 1 ............................................ 2 ............................................ Original ................................. detect and correct loose, cracked, or missing fasteners in the engine aft support mount fitting, which could lead to separation of the support fitting from the pylon, which could result in separation of the engine from the airplane. BILLING CODE 4910–13–P VerDate Aug<31>2005 Revision PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 Date October 17, 2006. January 17, 2007. July 4, 2007. February 22, 2007. Service Management, Dept. C1–L5A (D800–0024). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5233; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion We have received reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines on several McDonnell Douglas Model MD–90–30 airplanes. The airplanes had accumulated between 18,767 and 25,400 total flight hours and between 15,841 and 27,000 total flight cycles. A safety assessment of the missing fasteners has concluded that loose or discrepant fasteners in the top E:\FR\FM\09SER1.SGM 09SER1 52204 Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations horizontal row, common with the pylon skin, significantly decrease the margin of safety of the aft mount support installation at the design limit load. Loose, cracked, or missing fasteners in the engine aft mount support fitting could lead to separation of the support fitting from the pylon. This condition, if not corrected, could result in separation of the engine from the airplane. Relevant Service Information We reviewed Boeing Alert Service Bulletin MD90–54A002, dated August 1, 2008. The service bulletin describes procedures for doing a detailed inspection for certain defects of the upper fasteners of the aft mount support fitting of the left and right engines, and corrective action as applicable. The detailed inspection consists of the following actions: (1) A general visual inspection of the upper fasteners for any missing, loose, or damaged fasteners, (2) a gap check between the washers and structure or between the fastener heads and structure, if applicable, and (3) a torque check of the fastener nuts, if applicable. The corrective action includes replacing all fasteners if any defect is found. FAA’s Determination and Requirements of This AD We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the(se) same type design(s). This AD requires accomplishing the actions specified in the service information described previously. yshivers on PROD1PC62 with RULES Interim Action This is considered to be interim action until final action is identified, at which time we might consider further rulemaking. FAA’s Justification and Determination of the Effective Date Loose, cracked, or missing fasteners in the engine aft mount support fitting could lead to separation of the support fitting from the pylon, possibly resulting in separation of the engine from the airplane. Because of our requirement to promote safe flight of civil aircraft and thus, the critical need to assure structural integrity of the engine aft mount support fitting and the short compliance time involved with this action, this AD must be issued immediately. Because an unsafe condition exists that requires the immediate adoption of this AD, we find that notice and opportunity for prior public comment VerDate Aug<31>2005 15:16 Sep 08, 2008 Jkt 214001 hereon are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2008–0946; Directorate Identifier 2008– NM–147–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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 This AD will not have federalism implications under Executive Order 13132. This AD 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. For the reasons discussed above, I certify that this AD: PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 (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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–18–10 McDonnell Douglas: Amendment 39–15667. Docket No. FAA–2008–0946; Directorate Identifier 2008–NM–147–AD. Effective Date (a) This airworthiness directive (AD) is effective September 24, 2008. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model MD–90–30 airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin MD90–54A002, dated August 1, 2008. Unsafe Condition (d) This AD results from reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to detect and correct loose, cracked, or missing fasteners in the engine aft support mount fitting, which could lead to separation of the support fitting from the pylon, which could result in separation of the engine from the airplane. Compliance (e) Comply with this AD within the compliance times specified, unless already done. Detailed Inspection (f) Within 703 flight cycles after the effective date of this AD, do a detailed E:\FR\FM\09SER1.SGM 09SER1 Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations inspection for any defect (missing, loose, or damaged fasteners; incorrect gap between washers and structure or between fastener heads and structure; or incorrect torque of fastener nuts) of the upper fasteners of the aft mount support fitting of the left and right engines, and do all the applicable corrective actions before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A002, dated August 1, 2008. Credit for Actions Done per Multiple Operator Message (MOM) (g) Actions done before the effective date of this AD in accordance with Boeing MOM 1–893882781–2, dated July 25, 2008, are acceptable for compliance with the requirements of paragraph (f) of this AD. yshivers on PROD1PC62 with RULES Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Certification Office (ACO), FAA, ATTN: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627– 5233; fax (562) 627–5210; has the authority to approve AMOCs for this AD, if requested using 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference (i) You must use Boeing Alert Service Bulletin MD90–54A002, dated August 1, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024). (3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal_register/ VerDate Aug<31>2005 15:16 Sep 08, 2008 Jkt 214001 code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 25, 2008. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–20494 Filed 9–8–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0955; Directorate Identifier 2008–CE–040–AD; Amendment 39–15668; AD 2008–19–01] RIN 2120–AA64 Airworthiness Directives; Harco Labs, Inc. Pitot/AOA Probes (Part Numbers 100435–39, 100435–39–001, 100435–40, and 100435–40–001) Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Harco Labs, Inc. part numbers 100435– 39, 100435–39–001, 100435–40, and 100435–40–001 pitot/angle of attack (AOA) probes installed on, but not limited to Eclipse Aviation Inc. Model EA500 airplanes. This AD requires you to incorporate information into the Limitations section of the airplane flight manual (AFM) that will allow operation only under day visual flight rules (VFR) and allow only a VFR flight plan. This AD also requires you to test the pitot/ AOA probes for heater performance and replace the pitot/AOA probe if it fails the heater performance test. This AD results from several reports of airspeed disagree caution indication due to blockage from freezing condensation within the pitot/AOA system. We are issuing this AD to detect and correct improperly performing pitot/AOA probe heaters, which could result in blockage within the pitot/AOA system from condensation freezing with consequent incorrect indication of impact air pressure (airspeed/AOA). This blockage could lead to the stall warning becoming unreliable and the stick pusher, overspeed warning, autopilot, and yaw damper to malfunction. DATES: This AD becomes effective on September 29, 2008. On September 29, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 52205 We must receive any comments on this AD by November 10, 2008. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this AD, contact Harco Labs, Inc. 186 Cedar Street, Branford, Connecticut 06405; telephone: (203) 483–3700; fax: (203) 483–3701, and Eclipse Aviation, 2503 Clark Carr Loop SE, Albuquerque, New Mexico 87106; telephone: (505) 245–7555; fax: (505) 241–8802. To view the comments to this AD, go to https://www.regulations.gov. The docket number is FAA–2008–0955; Directorate Identifier 2008–CE–040–AD. FOR FURTHER INFORMATION CONTACT: Solomon Hecht, Aerospace Engineer, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone: (781) 238–7159; fax: (781) 238–7170. SUPPLEMENTARY INFORMATION: Discussion We received several reports of airspeed disagree caution indication due to blockage within the pitot/AOA system from freezing condensation. We are issuing this AD to detect and correct improperly performing pitot/AOA probe heaters. This condition, if not corrected, could result in a blockage within the pitot/ AOA system from condensation freezing with consequent incorrect indication of impact air pressure (airspeed/AOA). This blockage could lead to the stall warning becoming unreliable and the stick pusher, overspeed warning, autopilot, and yaw damper to malfunction. Relevant Service Information We reviewed Harco Labs, Inc. Service Bulletin SB–34–10–10–001, Revision F, dated August 19, 2008; Harco Pitot AOA Probe Internal Tubing Heater Verification Test Procedure No. P1149, Rev: E, referenced in 8. Appendix A of Harco Labs, Inc. Service Bulletin SB– E:\FR\FM\09SER1.SGM 09SER1

Agencies

[Federal Register Volume 73, Number 175 (Tuesday, September 9, 2008)]
[Rules and Regulations]
[Pages 52203-52205]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-20494]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0946; Directorate Identifier 2008-NM-147-AD; 
Amendment 39-15667; AD 2008-18-10]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-90-30 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
McDonnell Douglas Model MD-90-30 airplanes. This AD requires a detailed 
inspection for certain defects of the upper fasteners of the aft mount 
support fitting of the left and right engines and corrective actions if 
necessary. This AD results from reports of loose, cracked, or missing 
fasteners in the aft mount support fitting of the left and right 
engines. We are issuing this AD to detect and correct loose, cracked, 
or missing fasteners in the engine aft support mount fitting, which 
could lead to separation of the support fitting from the pylon, which 
could result in separation of the engine from the airplane.

DATES: This AD is effective September 24, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
24, 2008.
    We must receive comments on this AD by November 10, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Data and Service Management, 
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5233; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Discussion

    We have received reports of loose, cracked, or missing fasteners in 
the aft mount support fitting of the left and right engines on several 
McDonnell Douglas Model MD-90-30 airplanes. The airplanes had 
accumulated between 18,767 and 25,400 total flight hours and between 
15,841 and 27,000 total flight cycles. A safety assessment of the 
missing fasteners has concluded that loose or discrepant fasteners in 
the top

[[Page 52204]]

horizontal row, common with the pylon skin, significantly decrease the 
margin of safety of the aft mount support installation at the design 
limit load. Loose, cracked, or missing fasteners in the engine aft 
mount support fitting could lead to separation of the support fitting 
from the pylon. This condition, if not corrected, could result in 
separation of the engine from the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin MD90-54A002, dated August 
1, 2008. The service bulletin describes procedures for doing a detailed 
inspection for certain defects of the upper fasteners of the aft mount 
support fitting of the left and right engines, and corrective action as 
applicable. The detailed inspection consists of the following actions: 
(1) A general visual inspection of the upper fasteners for any missing, 
loose, or damaged fasteners, (2) a gap check between the washers and 
structure or between the fastener heads and structure, if applicable, 
and (3) a torque check of the fastener nuts, if applicable. The 
corrective action includes replacing all fasteners if any defect is 
found.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the(se) same type 
design(s). This AD requires accomplishing the actions specified in the 
service information described previously.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time we might consider further rulemaking.

FAA's Justification and Determination of the Effective Date

    Loose, cracked, or missing fasteners in the engine aft mount 
support fitting could lead to separation of the support fitting from 
the pylon, possibly resulting in separation of the engine from the 
airplane. Because of our requirement to promote safe flight of civil 
aircraft and thus, the critical need to assure structural integrity of 
the engine aft mount support fitting and the short compliance time 
involved with this action, this AD must be issued immediately.
    Because an unsafe condition exists that requires the immediate 
adoption of this AD, we find that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2008-0946; Directorate Identifier 2008-NM-147-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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

    This AD will not have federalism implications under Executive Order 
13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new AD:

2008-18-10 McDonnell Douglas: Amendment 39-15667. Docket No. FAA-
2008-0946; Directorate Identifier 2008-NM-147-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective September 24, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model MD-90-30 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin MD90-54A002, dated August 1, 2008.

Unsafe Condition

    (d) This AD results from reports of loose, cracked, or missing 
fasteners in the aft mount support fitting of the left and right 
engines. We are issuing this AD to detect and correct loose, 
cracked, or missing fasteners in the engine aft support mount 
fitting, which could lead to separation of the support fitting from 
the pylon, which could result in separation of the engine from the 
airplane.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Detailed Inspection

    (f) Within 703 flight cycles after the effective date of this 
AD, do a detailed

[[Page 52205]]

inspection for any defect (missing, loose, or damaged fasteners; 
incorrect gap between washers and structure or between fastener 
heads and structure; or incorrect torque of fastener nuts) of the 
upper fasteners of the aft mount support fitting of the left and 
right engines, and do all the applicable corrective actions before 
further flight, by accomplishing all of the applicable actions 
specified in the Accomplishment Instructions of Boeing Alert Service 
Bulletin MD90-54A002, dated August 1, 2008.

Credit for Actions Done per Multiple Operator Message (MOM)

    (g) Actions done before the effective date of this AD in 
accordance with Boeing MOM 1-893882781-2, dated July 25, 2008, are 
acceptable for compliance with the requirements of paragraph (f) of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles Certification Office (ACO), FAA, 
ATTN: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM-120L, 
FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5233; fax (562) 627-5210; has the 
authority to approve AMOCs for this AD, if requested using 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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Los Angeles ACO, to make those findings. For a 
repair method to be approved, the repair must meet the certification 
basis of the airplane, and the approval must specifically refer to 
this AD.

Material Incorporated by Reference

    (i) You must use Boeing Alert Service Bulletin MD90-54A002, 
dated August 1, 2008, to do the actions required by this AD, unless 
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).
    (3) You may review copies of the service information 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on August 25, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-20494 Filed 9-8-08; 8:45 am]
BILLING CODE 4910-13-P

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