Airworthiness Directives; The Boeing Company Airplanes, 65803-65805 [2012-26187]

Download as PDF Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations to the International Branch, send it to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1175; fax (425) 227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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. mstockstill on DSK4VPTVN1PROD with RULES (j) Related Information (1) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011– 0220, dated November 11, 2011; and BAE SYSTEMS (OPERATIONS) LIMITED Modification Service Bulletin SB.29–048– 30676A, Revision 2, dated December 23, 2010; for related information. (2) For service information identified in this AD, contact BAE SYSTEMS (OPERATIONS) LIMITED, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) BAE SYSTEMS (OPERATIONS) LIMITED Modification Service Bulletin SB.29–048–30676A, Revision 2, dated December 23, 2010. (ii) Reserved. (3) For service information identified in this AD, contact BAE SYSTEMS (OPERATIONS) LIMITED, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 14, 2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–26185 Filed 10–30–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0728; Directorate Identifier 2012–NM–050–AD; Amendment 39–17234; AD 2012–21–18] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD–90–30 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of the structural integrity of the wing. DATES: This AD is effective December 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 5, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206– 766–5683; 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. SUMMARY: PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 65803 Examining the AD Docket You may examine the AD docket on the Internet at http://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, Airframe Branch, ANM– 120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: (562) 627–5233; fax: (562) 627–5210; email: roger.durbin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on August 1, 2012 (77 FR 45515). That NPRM proposed to require repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supports the NPRM (77 FR 45515, August 1, 2012). Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed—except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 45515, August 1, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 45515, August 1, 2012). Costs of Compliance We estimate that this AD affects 52 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\31OCR1.SGM 31OCR1 65804 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ................................ 13 work-hours × $85 per hour = $1,105 per inspection cycle. 13 work-hours × $85 per hour = $1,105. None ........... $1,105 per inspection cycle ... $57,460 per inspection cycle None ........... $1,105 ..................................... $57,460. Post-repair inspection ............. We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of Cost on U.S. operators determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Splice repair per wing ............................................... 93 work-hours × $85 per hour = $7,905 .................. $28,126 $36,031 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions of the post-repair inspection specified in 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. mstockstill on DSK4VPTVN1PROD with RULES 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), VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 (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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–21–18 The Boeing Company: Amendment 39–17234; Docket No. FAA–2012–0728; Directorate Identifier 2012–NM–050–AD. (a) Effective Date This AD is effective December 5, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model MD–90–30 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin MD90–57A030, dated February 14, 2012. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before the accumulation of 14,000 total flight cycles, or within 9,470 flight cycles after the effective date of this AD: Whichever occurs later, do an in-tank eddy current high frequency (ETHF) inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000 of the left and right wings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–57A030, dated February 14, 2012. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 31,000 flight cycles. (h) Splice Repair If any cracking is found during any inspection required by paragraph (g) of this AD: Before further flight, do a splice repair, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–57A030, dated February 14, 2012. (i) Post-Repair Inspection Within 42,000 flight cycles after doing the splice repair specified in paragraph (h) of this AD: Do an ETHF inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–57A030, dated February 14, 2012. Repeat the inspection thereafter at intervals E:\FR\FM\31OCR1.SGM 31OCR1 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations not to exceed 31,000 flight cycles. If any crack is found: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Issued in Renton, Washington, on October 12, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (j) Alternative Methods of Compliance (AMOCs) (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 appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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 54, and the approval must specifically refer to this AD. [FR Doc. 2012–26187 Filed 10–30–12; 8:45 am] mstockstill on DSK4VPTVN1PROD with RULES (k) Related Information For more information about this AD, contact Roger Durbin, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712– 4137; phone: (562) 627–5233; fax: (562) 627– 5210; email: roger.durbin@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin MD90– 57A030, dated February 14, 2012. (ii) Reserved. (3) For The Boeing Company Airplanes service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544– 5000, extension 2; fax 206–766–5683; Internet https://www.myboeingfleet.com. (4) You may view this service information at 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. (5) You may view this 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: http://www.archives. gov/federal-register/cfr/ibr-locations.html. VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0652; Directorate Identifier 2010–NM–045–AD; Amendment 39–17240; AD 2012–22–04] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD–90–30 airplanes. This AD was prompted by reports of cracks of the wing rear spar lower cap at the outboard flap, inboard drive hinge at station Xrs=164.000. This AD requires repetitive eddy current high frequency (ETHF) inspections for cracking on the aft side of the left and right wing rear spar lower caps at station Xrs=164.000, further ETHF inspections if cracks are found, and repair if necessary; and repetitive postrepair inspections, and repair if necessary. We are issuing this AD to detect and correct cracking of the left and right rear spar lower caps, which could result in fuel leaks and damage to the wing skin or other structure, and consequent loss of the structural integrity of the wing. DATES: This AD is effective December 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 5, 2012. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206– 766–5683; 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. SUMMARY: PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 65805 Examining the AD Docket You may examine the AD docket on the Internet at http:// 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, Airframe Branch, ANM– 120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: (562) 627–5233; Fax: (562) 627–5210; email: roger.durbin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That SNPRM published in the Federal Register on July 24, 2012 (77 FR 43178). The original NPRM (76 FR 40288, July 8, 2011) proposed to require repetitive eddy current high frequency (ETHF) inspections for cracking on the aft side of the left and right wing rear spar lower caps at station Xrs=164.000, further ETHF inspections if cracks are found, and repair if necessary. The original NPRM also proposed to require repetitive post-repair inspections and repair if necessary. The SNPRM proposed to continue to have the same requirements as the original NPRM, but also added new repetitive post-repair inspections, and corrective action if necessary. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM (77 FR 43178, July 24, 2012) 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—except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM (77 FR E:\FR\FM\31OCR1.SGM 31OCR1

Agencies

[Federal Register Volume 77, Number 211 (Wednesday, October 31, 2012)]
[Rules and Regulations]
[Pages 65803-65805]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26187]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0728; Directorate Identifier 2012-NM-050-AD; 
Amendment 39-17234; AD 2012-21-18]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model MD-90-30 airplanes. This AD was prompted by 
reports of fatigue cracks found in Stringer 11 at the outboard flap, 
inboard drive hinge at Station Xrs=164.000. This AD requires repetitive 
inspections for cracks in Stringer 11, and a splice repair if 
necessary; and repetitive post-repair inspections, and repair if 
necessary. We are issuing this AD to detect and correct such cracking, 
which could result in the wing structure not supporting the limit load 
condition, which could lead to loss of the structural integrity of the 
wing.

DATES: This AD is effective December 5, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 5, 
2012.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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 http://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, Airframe Branch, ANM-
120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 
Paramount Boulevard, Lakewood, California 90712-4137; phone: (562) 627-
5233; fax: (562) 627-5210; email: roger.durbin@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on August 1, 2012 (77 FR 
45515). That NPRM proposed to require repetitive inspections for cracks 
in Stringer 11, and a splice repair if necessary; and repetitive post-
repair inspections, and repair if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing supports the 
NPRM (77 FR 45515, August 1, 2012).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed--except for minor editorial changes. We have determined 
that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 45515, August 1, 2012) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 45515, August 1, 2012).

Costs of Compliance

    We estimate that this AD affects 52 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 65804]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                  Labor cost           Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  13 work-hours x     None...............  $1,105 per          $57,460 per
                                  $85 per hour =                           inspection cycle.   inspection cycle
                                  $1,105 per
                                  inspection cycle.
Post-repair inspection.........  13 work-hours x     None...............  $1,105............  $57,460.
                                  $85 per hour =
                                  $1,105.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                   Action                              Labor cost               Parts cost      Cost per product
----------------------------------------------------------------------------------------------------------------
Splice repair per wing.....................  93 work-hours x $85 per hour            $28,126            $36,031
                                              = $7,905.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions of the post-repair 
inspection specified in 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),
    (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

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 airworthiness 
directive (AD):

2012-21-18 The Boeing Company: Amendment 39-17234; Docket No. FAA-
2012-0728; Directorate Identifier 2012-NM-050-AD.

(a) Effective Date

    This AD is effective December 5, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model MD-90-30 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin MD90-57A030, dated February 14, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracks found in 
Stringer 11 at the outboard flap, inboard drive hinge at Station 
Xrs=164.000. We are issuing this AD to detect and correct such 
cracking, which could result in the wing structure not supporting 
the limit load condition, which could lead to loss of the structural 
integrity of the wing.

(f) Compliance

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

(g) Repetitive Inspections

    Before the accumulation of 14,000 total flight cycles, or within 
9,470 flight cycles after the effective date of this AD: Whichever 
occurs later, do an in-tank eddy current high frequency (ETHF) 
inspection for cracks in Stringer 11 at the outboard flap, inboard 
drive hinge at Station Xrs=164.000 of the left and right wings, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD90-57A030, dated February 14, 2012. If no 
cracking is found, repeat the inspection thereafter at intervals not 
to exceed 31,000 flight cycles.

(h) Splice Repair

    If any cracking is found during any inspection required by 
paragraph (g) of this AD: Before further flight, do a splice repair, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD90-57A030, dated February 14, 2012.

(i) Post-Repair Inspection

    Within 42,000 flight cycles after doing the splice repair 
specified in paragraph (h) of this AD: Do an ETHF inspection for 
cracks in Stringer 11 at the outboard flap, inboard drive hinge at 
Station Xrs=164.000, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin MD90-57A030, dated 
February 14, 2012. Repeat the inspection thereafter at intervals

[[Page 65805]]

not to exceed 31,000 flight cycles. If any crack is found: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD.

(j) Alternative Methods of Compliance (AMOCs)

    (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 appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
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 54, and the approval must specifically refer to 
this AD.

(k) Related Information

    For more information about this AD, contact Roger Durbin, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-
4137; phone: (562) 627-5233; fax: (562) 627-5210; email: 
roger.durbin@faa.gov.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin MD90-57A030, dated February 
14, 2012.
    (ii) Reserved.
    (3) For The Boeing Company Airplanes service information 
identified in this AD, contact Boeing Commercial Airplanes, 
Attention: Data & Services Management, 3855 Lakewood Boulevard, MC 
D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, 
extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at 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.
    (5) You may view this 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 12, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-26187 Filed 10-30-12; 8:45 am]
BILLING CODE 4910-13-P