Airworthiness Directives; the Boeing Company Airplanes, 64084-64086 [2014-25019]

Download as PDF 64084 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations Issued in Renton, Washington, on October 13, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–25013 Filed 10–27–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0451; Directorate Identifier 2013–NM–122–AD; Amendment 39–17996; AD 2014–21–04] 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 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 cracks emanating from the aftmost barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (ETHF) inspections for cracks in the areas around the two aft-most barrel nut holes of the upper rear spar caps, and corrective actions if necessary; and repetitive ETHF inspections for cracks in the areas around the two aft-most barrel nut holes of any repaired or replaced upper rear spar cap, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrity of the airplane. DATES: This AD is effective December 2, 2014. SUMMARY: The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 2, 2014. 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 view this referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0451; 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 Docket 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: George Garrido, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5357; fax: 562–627–5210; email: george.garrido@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all 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. The NPRM published in the Federal Register on July 18, 2014 (79 FR 41946). The NPRM was prompted by reports of cracks emanating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. The NPRM proposed to require repetitive ETHF inspections for cracks in the areas around the two aft-most barrel nut holes of the upper rear spar caps, and corrective actions if necessary; and repetitive ETHF inspections for cracks in the areas around the two aftmost barrel nut holes of any repaired or replaced upper rear spar cap, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supported the NPRM (79 FR 41946, July 18, 2014). Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this 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 (79 FR 41946, July 18, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 41946, July 18, 2014). Costs of Compliance We estimate that this AD affects 668 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS asabaliauskas on DSK5VPTVN1PROD with RULES Action Labor cost Inspection ...................... 5 work-hours × $85 per hour = $425 per inspection cycle. We estimate the following costs to do any necessary repairs and replacements that would be required based on the VerDate Sep<11>2014 18:35 Oct 27, 2014 Jkt 235001 Parts cost $0 results of the inspection. We have no way of determining the number of PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Cost per product $425 per inspection cycle. Cost on U.S. operators $283,900 per inspection cycle. aircraft that might need these repairs and replacements: E:\FR\FM\28OCR1.SGM 28OCR1 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 64085 ON-CONDITION COSTS Action Labor cost Parts cost Repair ........................................... Replacement ................................. Up to 394 work-hours × $85 per hour = $33,490 .............................. Up to 394 work-hours × $85 per hour = $33,490 .............................. Up to $32,440 ..... Up to $60,222 ..... 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. asabaliauskas on DSK5VPTVN1PROD with RULES 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: VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 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): ■ 2014–21–04 The Boeing Company: Amendment 39–17996 ; Docket No. FAA–2014–0451; Directorate Identifier 2013–NM–122–AD. (a) Effective Date This AD is effective December 2, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all 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. (d) Subject Air Transport Association (ATA) Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of cracks emanating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection At the applicable compliance time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013; except as provided by paragraph (i) of this AD: Do a high frequency eddy current inspection (ETHF) for cracks in the areas around the two aft-most barrel nut holes of the left and right upper rear spar caps, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013. Thereafter, repeat the ETHF inspection at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD80–55A070, PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 Cost per product Up to $65,930. Up to $93,712. Revision 1, dated December 17, 2013; except as provided by paragraph (i) of this AD. If any cracking is found during any inspection, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013. (h) Post-Repair/Replacement Actions For airplanes on which a splice repair or replacement was done, as specified in Boeing Alert Service Bulletin MD80–55A070: At the applicable compliance time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013, do a ETHF inspection for cracks at the two aftmost barrel nut holes of any repaired or replaced upper rear spar cap, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013. Thereafter, repeat the ETHF inspection at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013. If any cracking is found during any inspection, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013. (i) Exception to the Service Information Specifications Where Boeing Alert Service Bulletin MD80–55A070, Revision 1, dated December 17, 2013, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (j) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin MD80–55A070, dated May 22, 2013, which is not incorporated by reference in this AD. (k) 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 paragraph (l)(1) of this AD. Information may E:\FR\FM\28OCR1.SGM 28OCR1 64086 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations be emailed to: 9-ANM-LAACO-AMOCREQUESTS@faa.gov. (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. (l) Related Information (1) For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712– 4137; phone: 562–627–5357; fax: 562–627– 5210; email: george.garrido@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (m) 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– 55A070, Revision 1, dated December 17, 2013. (ii) Reserved. (3) For Boeing 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 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 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 13, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–25019 Filed 10–27–14; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:44 Oct 27, 2014 Jkt 235001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0287; Directorate Identifier 2013–NM–247–AD; Amendment 39–18000; AD 2014–21–07] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600–2D24 (Regional Jet Series 900) airplanes, and Model CL–600–2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that certain parts of the aft baggage door did not conform to the design specifications and were of degraded strength. This AD requires repetitive inspections for cracking and deformations of certain stop fittings and striker plates of the aft baggage bay door; and replacement, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking and deformations of certain stop fittings and striker plates, which could result in the opening of the aft baggage bay door and rapid decompression or reduced controllability of the airplane. DATES: This AD becomes effective December 2, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 2, 2014. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0287; or in person at the Docket 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. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the SUMMARY: PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7331; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600– 2D24 (Regional Jet Series 900) airplanes, and Model CL–600–2E25 (Regional Jet Series 1000) airplanes. The NPRM published in the Federal Register on May 29, 2014 (79 FR 30751). Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–37, dated November 28, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Bombardier, Inc. Model CL– 600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600–2D24 (Regional Jet Series 900) airplanes, and Model CL–600–2E25 (Regional Jet Series 1000) airplanes. The MCAI states: During the manufacturing process, it was found that certain aft baggage bay door stop fittings and striker plates did not conform to the design specifications due to a quality control problem. This quality escape could degrade the strength of the affected aft baggage bay door stop fittings and striker plates. Failure of the aft baggage bay door stop fittings or striker plates may result in the opening of the aft baggage bay door and consequent rapid decompression of the aeroplane during flight. This [Canadian] AD mandates the initial and repetitive inspections of each aft baggage bay door stop fitting and striker plate until the terminating action [stop fitting/striker plate replacement] is accomplished. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-02870002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 30751, May 29, 2014) or on the determination of the cost to the public. E:\FR\FM\28OCR1.SGM 28OCR1

Agencies

[Federal Register Volume 79, Number 208 (Tuesday, October 28, 2014)]
[Rules and Regulations]
[Pages 64084-64086]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25019]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0451; Directorate Identifier 2013-NM-122-AD; 
Amendment 39-17996; AD 2014-21-04]
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 all 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 cracks emanating from the aft-most barrel nut holes of the left and 
right upper rear spar caps of the horizontal stabilizer. This AD 
requires repetitive high frequency eddy current (ETHF) inspections for 
cracks in the areas around the two aft-most barrel nut holes of the 
upper rear spar caps, and corrective actions if necessary; and 
repetitive ETHF inspections for cracks in the areas around the two aft-
most barrel nut holes of any repaired or replaced upper rear spar cap, 
and corrective actions if necessary. We are issuing this AD to detect 
and correct cracks in the horizontal stabilizer, which could propagate 
until an upper rear spar cap severs, and result in failure of the 
horizontal stabilizer upper center or aft skin panel and adversely 
affect the structural integrity of the airplane.

DATES: This AD is effective December 2, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 2, 
2014.

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 view this referenced 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.
Examining the AD Docket
    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0451; 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 Docket 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: George Garrido, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5357; fax: 562-627-5210; email: george.garrido@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all 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. The NPRM published in the Federal Register on 
July 18, 2014 (79 FR 41946). The NPRM was prompted by reports of cracks 
emanating from the aft-most barrel nut holes of the left and right 
upper rear spar caps of the horizontal stabilizer. The NPRM proposed to 
require repetitive ETHF inspections for cracks in the areas around the 
two aft-most barrel nut holes of the upper rear spar caps, and 
corrective actions if necessary; and repetitive ETHF inspections for 
cracks in the areas around the two aft-most barrel nut holes of any 
repaired or replaced upper rear spar cap, and corrective actions if 
necessary. We are issuing this AD to detect and correct cracks in the 
horizontal stabilizer, which could propagate until an upper rear spar 
cap severs, and result in failure of the horizontal stabilizer upper 
center or aft skin panel and adversely affect the structural integrity 
of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing supported the 
NPRM (79 FR 41946, July 18, 2014).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this 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 (79 FR 41946, July 18, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 41946, July 18, 2014).

Costs of Compliance

    We estimate that this AD affects 668 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
----------------------------------------------------------------------------------------------------------------
Inspection.......................  5 work-hours x $85             $0  $425 per inspection   $283,900 per
                                    per hour = $425 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs and 
replacements 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 and replacements:

[[Page 64085]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
             Action                      Labor cost                 Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
Repair..........................  Up to 394                 Up to $32,440............  Up to $65,930.
                                   work[dash]hours x $85
                                   per hour = $33,490.
Replacement.....................  Up to 394                 Up to $60,222............  Up to $93,712.
                                   work[dash]hours x $85
                                   per hour = $33,490.
----------------------------------------------------------------------------------------------------------------

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):

2014-21-04 The Boeing Company: Amendment 39-17996 ; Docket No. FAA-
2014-0451; Directorate Identifier 2013-NM-122-AD.

(a) Effective Date

    This AD is effective December 2, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all 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.

(d) Subject

    Air Transport Association (ATA) Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of cracks emanating from the 
aft-most barrel nut holes of the left and right upper rear spar caps 
of the horizontal stabilizer. We are issuing this AD to detect and 
correct cracks in the horizontal stabilizer, which could propagate 
until an upper rear spar cap severs, and result in failure of the 
horizontal stabilizer upper center or aft skin panel and adversely 
affect the structural integrity of the airplane.

(f) Compliance

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

(g) Inspection

    At the applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070, 
Revision 1, dated December 17, 2013; except as provided by paragraph 
(i) of this AD: Do a high frequency eddy current inspection (ETHF) 
for cracks in the areas around the two aft-most barrel nut holes of 
the left and right upper rear spar caps, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
55A070, Revision 1, dated December 17, 2013. Thereafter, repeat the 
ETHF inspection at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070, 
Revision 1, dated December 17, 2013; except as provided by paragraph 
(i) of this AD. If any cracking is found during any inspection, 
before further flight, do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD80-55A070, Revision 1, dated December 17, 2013.

(h) Post-Repair/Replacement Actions

    For airplanes on which a splice repair or replacement was done, 
as specified in Boeing Alert Service Bulletin MD80-55A070: At the 
applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A070, 
Revision 1, dated December 17, 2013, do a ETHF inspection for cracks 
at the two aft-most barrel nut holes of any repaired or replaced 
upper rear spar cap, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin MD80-55A070, Revision 
1, dated December 17, 2013. Thereafter, repeat the ETHF inspection 
at the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin MD80-55A070, Revision 1, dated 
December 17, 2013. If any cracking is found during any inspection, 
before further flight, do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD80-55A070, Revision 1, dated December 17, 2013.

(i) Exception to the Service Information Specifications

    Where Boeing Alert Service Bulletin MD80-55A070, Revision 1, 
dated December 17, 2013, specifies a compliance time ``after the 
original issue date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin MD80-
55A070, dated May 22, 2013, which is not incorporated by reference 
in this AD.

(k) 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 paragraph (l)(1) of this AD. 
Information may

[[Page 64086]]

be emailed to: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
    (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.

(l) Related Information

    (1) For more information about this AD, contact George Garrido, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
CA 90712-4137; phone: 562-627-5357; fax: 562-627-5210; email: 
george.garrido@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 MD80-55A070, Revision 1, dated 
December 17, 2013.
    (ii) Reserved.
    (3) For Boeing 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 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 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 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-25019 Filed 10-27-14; 8:45 am]
BILLING CODE 4910-13-P