Airworthiness Directives; The Boeing Company Airplanes, 65611-65613 [2012-26073]

Download as PDF 65611 Rules and Regulations Federal Register Vol. 77, No. 210 Tuesday, October 30, 2012 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0727; Directorate Identifier 2012–NM–012–AD; Amendment 39–17229; AD 2012–21–13] 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 DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD– 88 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 structural integrity of the wing. SUMMARY: This AD is effective December 4, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 4, 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, 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. DATES: 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, 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 45518). 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 45518, 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 45518, 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 45518, August 1, 2012). Costs of Compliance We estimate that this AD affects 502 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Inspection ............... wreier-aviles on DSK7SPTVN1PROD with RULES Action 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. $1,105 .................... Post-repair inspection. We estimate the following costs to do any necessary repairs that would be VerDate Mar<15>2010 13:15 Oct 29, 2012 Jkt 229001 None ....................... required based on the results of the inspection. We have no way of PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Cost on U.S. operators $554,710 per inspection cycle. $554,710. determining the number of aircraft that might need this repair: E:\FR\FM\30OCR1.SGM 30OCR1 65612 Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Splice repair per wing ........................ 93 work-hours × $85 per hour = $7,905 ........................................................ We have received no definitive data that would enable us to provide cost estimates for the on-condition actions for 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. wreier-aviles on DSK7SPTVN1PROD 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), (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. VerDate Mar<15>2010 13:15 Oct 29, 2012 Jkt 229001 Parts cost $17,759 Cost per product $25,664 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–57A243, dated December 20, 2011. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 29,000 flight cycles. PART 39—AIRWORTHINESS DIRECTIVES (h) Splice Repair 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] (i) Post-Repair Inspection 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–21–13 The Boeing Company: Amendment 39–17229; Docket No. FAA–2012–0727; Directorate Identifier 2012–NM–012–AD. (a) Effective Date This AD is effective December 4, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD–88 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin MD80–57A243, dated December 20, 2011. (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 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 19,000 total flight cycles, or within 8,710 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, in PO 00000 Frm 00002 Fmt 4700 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 MD80–57A243, dated December 20, 2011. Sfmt 4700 Within 60,000 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 MD80–57A243, dated December 20, 2011. Repeat the inspection thereafter at intervals not to exceed 29,000 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 45, 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– E:\FR\FM\30OCR1.SGM 30OCR1 Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 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 MD80– 57A243, dated December 20, 2011. (ii) Reserved. (3) For The Boeing Company 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 12, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–26073 Filed 10–29–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1104; Directorate Identifier 2012–NM–073–AD; Amendment 39–17226; AD 2012–21–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777–200LR and –300ER series airplanes. This AD requires reviewing the airplane’s maintenance records for each rudder power control unit (PCU) to identify the condition of its related reaction link assembly, and replacing the rudder PCU wreier-aviles on DSK7SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 13:15 Oct 29, 2012 Jkt 229001 and its related reaction link assembly if necessary. This AD was prompted by a report of an abnormal airframe vibration in the aft fuselage during flight. We are issuing this AD to prevent excessive freeplay in the rudder control surface, which could cause rudder vibration, and result in structural damage severe enough to prevent continued safe flight and landing. DATES: This AD is effective November 14, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 14, 2012. We must receive comments on this AD by December 14, 2012. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; 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 street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kenneth Frey, Aerospace Engineer, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 65613 Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917– 6468; fax: (425) 917–6590; email: Kenneth.frey@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We have received a report of an abnormal airframe vibration in the aft fuselage during flight. A subsequent inspection of the rudder PCU installations found that the bushing liners were missing from all six end cap assemblies on the three rudder PCUs. An investigation revealed that the cause of the problem was failure of the bond between the liner and the bushing substrate because of the use of liquid nitrogen during installation of the bushing into the reaction link end cap housing. This condition, if not corrected, could result in excessive freeplay in the rudder control surface, which could cause rudder vibration, and result in structural damage severe enough to prevent continued safe flight and landing. Relevant Service Information We reviewed Boeing Alert Service Bulletin 777–27A0109, dated December 1, 2011. The service information describes procedures, for airplanes having certain line numbers, for reviewing the airplane’s maintenance records for each rudder PCU to identify the condition of its related reaction link assembly, and replacing the rudder PCU and its related reaction link assembly if necessary. FAA’s Determination 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 this same type design. AD Requirements This AD requires accomplishing the actions specified in the service information described previously. FAA’s Justification and Determination of the Effective Date No U.S. airplanes are affected by this AD. Therefore, we find that notice and opportunity for prior public comment are unnecessary 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 was not preceded by notice and an E:\FR\FM\30OCR1.SGM 30OCR1

Agencies

[Federal Register Volume 77, Number 210 (Tuesday, October 30, 2012)]
[Rules and Regulations]
[Pages 65611-65613]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26073]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / 
Rules and Regulations

[[Page 65611]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0727; Directorate Identifier 2012-NM-012-AD; 
Amendment 39-17229; AD 2012-21-13]
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 DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
83), DC-9-87 (MD-87), and MD-88 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 structural integrity of the 
wing.

DATES: This AD is effective December 4, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 4, 
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, 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, 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 
45518). 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 45518, 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 45518, 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 45518, August 1, 2012).

Costs of Compliance

    We estimate that this AD affects 502 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                        Labor cost              Parts cost         Cost per product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection........................  13 work-hours x $85 per    None................  $1,105 per            $554,710 per inspection cycle.
                                     hour = $1,105 per                                inspection cycle.
                                     inspection cycle.
Post-repair inspection............  13 work-hours x $85 per    None................  $1,105..............  $554,710.
                                     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 this repair:

[[Page 65612]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                    Action                                    Labor cost                 Parts cost    product
----------------------------------------------------------------------------------------------------------------
Splice repair per wing........................  93 work-hours x $85 per hour = $7,905.      $17,759      $25,664
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions for 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):

2012-21-13 The Boeing Company: Amendment 39-17229; Docket No. FAA-
2012-0727; Directorate Identifier 2012-NM-012-AD.

(a) Effective Date

    This AD is effective December 4, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model DC-9-81 (MD-81), DC-
9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin MD80-57A243, dated December 20, 2011.

(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 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 19,000 total flight cycles, or within 
8,710 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, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
57A243, dated December 20, 2011. If no cracking is found, repeat the 
inspection thereafter at intervals not to exceed 29,000 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 MD80-57A243, dated December 20, 2011.

(i) Post-Repair Inspection

    Within 60,000 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 MD80-57A243, dated 
December 20, 2011. Repeat the inspection thereafter at intervals not 
to exceed 29,000 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 45, 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-

[[Page 65613]]

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 MD80-57A243, dated December 
20, 2011.
    (ii) Reserved.
    (3) For The Boeing Company 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: https://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. 2012-26073 Filed 10-29-12; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.