Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes, 66653-66655 [2010-26555]

Download as PDF Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations the compliance times specified, unless the actions have already been done. Actions (g) Within 5 years after the effective date of this AD, replace the wing tank main pump pressure switches having P/N HTE69000–1 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–28–3111, Revision 02, dated March 24, 2010. (h) Actions accomplished before the effective date of this AD according to Airbus Mandatory Service Bulletin A330–28–3111, dated August 12, 2009; or Revision 01, dated December 4, 2009; are considered acceptable for compliance with the corresponding actions specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences WReier-Aviles on DSKGBLS3C1PROD with RULES Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (j) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010–0018, dated February 4, 2010; and Airbus Mandatory Service Bulletin A330–28–3111, Revision 02, dated March 24, 2010; for related information. Material Incorporated by Reference (k) You must use Airbus Mandatory Service Bulletin A330–28–3111, Revision 02, VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 dated March 24, 2010, 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 Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; e-mail airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference 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 October 13, 2010. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–26553 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0645; Directorate Identifier 2009–NM–200–AD; Amendment 39–16483; AD 2010–22–04] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Corporation Model MD–90–30 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. This new AD requires repetitive replacement of the upper row of fasteners of the support fittings of the engine aft mount with new fasteners; and repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 66653 engine aft mounts, and replacement of all clearance fit fasteners in the lower row if necessary. This AD was prompted by 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 prevent loose, cracked, or missing fasteners in the engine aft mount support fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane. DATES: This AD is effective December 3, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 3, 2010. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800 0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. 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 address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. 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; e-mail: Roger.Durbin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede airworthiness E:\FR\FM\29OCR1.SGM 29OCR1 66654 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations directive (AD) 2008–18–10, amendment 39–15667 (73 FR 52203, September 9, 2008). That AD applies to the specified products. The NPRM was published in the Federal Register on July 1, 2010 (75 FR 38056). That NPRM proposed to require repetitive replacement of the upper row of fasteners (Row A) of the support fittings of the left and right engine aft mount with new fasteners. That NPRM also proposed to require repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft mounts (that includes a gap check under the head or nut, and a torque check), as necessary for defects of the lower row of fasteners (Row B) of the support fittings of the left and right engine aft mounts, and replacing all clearance fit fasteners in the lower row (Row B) with new fasteners if any defect is found. Defects include missing, loose, and damaged fasteners. on the determination of the cost to the public. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or We estimate that this AD affects 13 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance ESTIMATED COSTS Action Replacement ..................... Inspections ........................ Labor cost Parts cost $152 per replacement ....... 14 work-hour × $85 per hour = $1,190. 4 work-hours × $85 per hour = $340. 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. $1,342 per replacement cycle. $340 per inspection cycle $0 ...................................... (3) Will not affect intrastate aviation in Alaska, and (4) 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. 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: ■ 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. Regulatory Findings WReier-Aviles on DSKGBLS3C1PROD with RULES Cost per product § 39.13 We have determined that 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), ■ VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2008–18–10, Amendment 39–15667 (73 FR 52203, September 9, 2008), and adding the following new AD: 2010–22–04 McDonnell Douglas Corporation: Amendment 39–16483; Docket No. FAA–2010–0645; Directorate Identifier 2009–NM–200–AD. Effective Date (a) This airworthiness directive (AD) is effective December 3, 2010. Affected ADs (b) This AD supersedes AD 2008–18–10, Amendment 39–15667. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Cost on U.S. operators $17,446 per replacement cycle. $4,420 per inspection cycle. Applicability (c) This AD applies to McDonnell Douglas Corporation Model MD–90–30 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. Subject (d) Air Transport Association (ATA) of America Code 54: Nacelles/Pylons. Unsafe Condition (e) This AD results from reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. The Federal Aviation Administration is issuing this AD to prevent loose, cracked, or missing fasteners in the engine aft support mount fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Replacement and Inspection (g) Except as required by paragraph (i) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010: Replace the upper row of fasteners (Row A) of the support fittings of the left and right engine aft mounts with new fasteners, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. Repeat the replacement thereafter at intervals not to exceed 10,000 flight cycles. (h) Concurrently with any replacement required by paragraph (g) of this AD: Perform a general visual inspection for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft E:\FR\FM\29OCR1.SGM 29OCR1 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations mounts, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. Defects include missing, loose, and damaged fasteners. (1) If no defect is found during any general visual inspection required by paragraph (h) of this AD, before further flight, insert a 0.0015-inch feeler gauge between the washer and the structure, or between the fastener head and structure, as applicable, to detect a gap condition, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. A gap condition is a defect identified in any location where the feeler gauge can slip completely between a washer or a fastener head and the structure. (i) If no defect is found during any gap check required by paragraph (h)(1) of this AD, before further flight, apply torque to the fasteners of the lower row (Row B) to determine if there is a defect, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. A defect is any fastener that turns with the application of the specified torque. If any defect is found, before further flight, replace all clearance fit fasteners in the lower row (Row B), in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. (ii) If any defect is found during any gap check required by paragraph (h)(1) of this AD, before further flight, replace all clearance fit fasteners in the lower row (Row B), in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. (2) If any defect is found during any general visual inspection required by paragraph (h) of this AD, before further flight, replace all clearance fit fasteners in the lower row (Row B), in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010. WReier-Aviles on DSKGBLS3C1PROD with RULES Exception to Service Bulletin Compliance Times (i) Where Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010, specifies a compliance time after the original issue date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Credit for Actions Accomplished in Accordance With Previous Service Information (j) Replacements and inspections accomplished before the effective date of this AD in accordance with Boeing Alert Service Bulletin MD90–54A003, Revision 1, dated November 17, 2009, are considered acceptable for compliance with the corresponding actions required by this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if VerDate Mar<15>2010 13:56 Oct 28, 2010 Jkt 223001 requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that 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 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. Related Information (l) For more information about this AD, contact 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; e-mail: Roger.Durbin@faa.gov. Material Incorporated by Reference (m) You must use Boeing Alert Service Bulletin MD90–54A003, Revision 2, dated February 12, 2010, 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, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800 0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, 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 October 13, 2010. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–26555 Filed 10–28–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 66655 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0849; Directorate Identifier 2010–CE–043–AD; Amendment 39–16488; AD 2010–22–09] RIN 2120–AA64 Airworthiness Directives; PILATUS Aircraft Ltd. Model PC–7 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: SUMMARY: This Airworthiness Directive (AD) is prompted due to an occurrence when an aircraft had a partial in-flight separation of the aileron outboard bearing support. The aileron outboard bearing supports are attached with two forward attachment bolts and two aft attachment bolts. The forward attachment bolts are approximately 3.2 mm (0.125 inch) longer than the aft attachment bolts. If the aileron outboard bearing supports have been removed, it is possible that during the reinstallation of the aileron outboard bearing supports, the attachment bolts can be installed in wrong positions. Bolts that are installed in wrong positions can damage the threads in the rear attachment anchor nuts. Such a condition, if left uncorrected, could lead to in-flight separation of the aileron outboard bearing support, and as a consequence, the loss or limited controllability of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 3, 2010. On December 3, 2010, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. For service information identified in this AD, contact Pilatus Aircraft Ltd., E:\FR\FM\29OCR1.SGM 29OCR1

Agencies

[Federal Register Volume 75, Number 209 (Friday, October 29, 2010)]
[Rules and Regulations]
[Pages 66653-66655]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-26555]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0645; Directorate Identifier 2009-NM-200-AD; 
Amendment 39-16483; AD 2010-22-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. That AD currently requires a detailed 
inspection for certain defects of the upper fasteners of the aft mount 
support fittings of the left and right engines, and corrective actions 
if necessary. This new AD requires repetitive replacement of the upper 
row of fasteners of the support fittings of the engine aft mount with 
new fasteners; and repetitive general visual inspections for defects of 
the lower row fasteners (Row B) of the support fittings of the left and 
right engine aft mounts, and replacement of all clearance fit fasteners 
in the lower row if necessary. This AD was prompted by 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 prevent loose, 
cracked, or missing fasteners in the engine aft mount support fittings, 
which could lead to separation of the support fittings from the pylon, 
and could result in separation of the engine from the airplane.

DATES: This AD is effective December 3, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 3, 
2010.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800 0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

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 address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

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; e-mail: 
Roger.Durbin@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede airworthiness

[[Page 66654]]

directive (AD) 2008-18-10, amendment 39-15667 (73 FR 52203, September 
9, 2008). That AD applies to the specified products. The NPRM was 
published in the Federal Register on July 1, 2010 (75 FR 38056). That 
NPRM proposed to require repetitive replacement of the upper row of 
fasteners (Row A) of the support fittings of the left and right engine 
aft mount with new fasteners. That NPRM also proposed to require 
repetitive general visual inspections for defects of the lower row 
fasteners (Row B) of the support fittings of the left and right engine 
aft mounts (that includes a gap check under the head or nut, and a 
torque check), as necessary for defects of the lower row of fasteners 
(Row B) of the support fittings of the left and right engine aft 
mounts, and replacing all clearance fit fasteners in the lower row (Row 
B) with new fasteners if any defect is found. Defects include missing, 
loose, and damaged fasteners.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD affects 13 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Replacement.....................  14 work-hour x $85  $152 per            $1,342 per          $17,446 per
                                   per hour = $1,190.  replacement.        replacement cycle.  replacement
                                                                                               cycle.
Inspections.....................  4 work-hours x $85  $0................  $340 per            $4,420 per
                                   per hour = $340.                        inspection cycle.   inspection cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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 removing airworthiness directive (AD) 
2008-18-10, Amendment 39-15667 (73 FR 52203, September 9, 2008), and 
adding the following new AD:

2010-22-04 McDonnell Douglas Corporation: Amendment 39-16483; Docket 
No. FAA-2010-0645; Directorate Identifier 2009-NM-200-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective December 3, 
2010.

Affected ADs

    (b) This AD supersedes AD 2008-18-10, Amendment 39-15667.

Applicability

    (c) This AD applies to McDonnell Douglas Corporation Model MD-
90-30 airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated 
February 12, 2010.

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Unsafe Condition

    (e) This AD results from reports of loose, cracked, or missing 
fasteners in the aft mount support fitting of the left and right 
engines. The Federal Aviation Administration is issuing this AD to 
prevent loose, cracked, or missing fasteners in the engine aft 
support mount fittings, which could lead to separation of the 
support fittings from the pylon, and could result in separation of 
the engine from the airplane.

Compliance

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

Replacement and Inspection

    (g) Except as required by paragraph (i) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated 
February 12, 2010: Replace the upper row of fasteners (Row A) of the 
support fittings of the left and right engine aft mounts with new 
fasteners, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated 
February 12, 2010. Repeat the replacement thereafter at intervals 
not to exceed 10,000 flight cycles.
    (h) Concurrently with any replacement required by paragraph (g) 
of this AD: Perform a general visual inspection for defects of the 
lower row fasteners (Row B) of the support fittings of the left and 
right engine aft

[[Page 66655]]

mounts, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin MD90-54A003, Revision 2, dated February 12, 
2010. Defects include missing, loose, and damaged fasteners.
    (1) If no defect is found during any general visual inspection 
required by paragraph (h) of this AD, before further flight, insert 
a 0.0015-inch feeler gauge between the washer and the structure, or 
between the fastener head and structure, as applicable, to detect a 
gap condition, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD90-54A003, Revision 2, dated 
February 12, 2010. A gap condition is a defect identified in any 
location where the feeler gauge can slip completely between a washer 
or a fastener head and the structure.
    (i) If no defect is found during any gap check required by 
paragraph (h)(1) of this AD, before further flight, apply torque to 
the fasteners of the lower row (Row B) to determine if there is a 
defect, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin MD90-54A003, Revision 2, dated February 12, 
2010. A defect is any fastener that turns with the application of 
the specified torque. If any defect is found, before further flight, 
replace all clearance fit fasteners in the lower row (Row B), in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD90-54A003, Revision 2, dated February 12, 2010.
    (ii) If any defect is found during any gap check required by 
paragraph (h)(1) of this AD, before further flight, replace all 
clearance fit fasteners in the lower row (Row B), in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
MD90-54A003, Revision 2, dated February 12, 2010.
    (2) If any defect is found during any general visual inspection 
required by paragraph (h) of this AD, before further flight, replace 
all clearance fit fasteners in the lower row (Row B), in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin MD90-54A003, Revision 2, dated February 12, 2010.

Exception to Service Bulletin Compliance Times

    (i) Where Boeing Alert Service Bulletin MD90-54A003, Revision 2, 
dated February 12, 2010, specifies a compliance time after the 
original issue date on the service bulletin, this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (j) Replacements and inspections accomplished before the 
effective date of this AD in accordance with Boeing Alert Service 
Bulletin MD90-54A003, Revision 1, dated November 17, 2009, are 
considered acceptable for compliance with the corresponding actions 
required by this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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 14 CFR 25.571, 
Amendment 45, and the approval must specifically refer to this AD.

Related Information

    (l) For more information about this AD, contact 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; e-mail: Roger.Durbin@faa.gov.

Material Incorporated by Reference

    (m) You must use Boeing Alert Service Bulletin MD90-54A003, 
Revision 2, dated February 12, 2010, 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, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800 0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
1601 Lind Avenue, SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, 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 October 13, 2010.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-26555 Filed 10-28-10; 8:45 am]
BILLING CODE 4910-13-P