Airworthiness Directives; The Boeing Company Airplanes, 65891-65893 [2014-26331]

Download as PDF Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations –212, –213, –311, –312, and –313 airplanes), which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A340–56–5002, dated May 4, 2010 (for Model A340–541 and –642 airplanes), which is not incorporated by reference in this AD. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. rmajette on DSK2TPTVN1PROD with RULES (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0256, dated October 21, 2013, for related information. You may examine the MCAI in the AD docket on the Internet at http://www. regulations.gov/#!documentDetail;D=FAA2014-0192-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. VerDate Sep<11>2014 15:26 Nov 05, 2014 Jkt 235001 (iii) Airbus Service Bulletin A340–56– 5002, Revision 02, including Appendixes 01 and 02, dated August 1, 2013. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.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. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 4, 1996 (61 FR 39860, July 31, 1996). 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. Issued in Renton, Washington, on September 24, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2014–24964 Filed 11–5–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0232; Directorate Identifier 2013–NM–100–AD; Amendment 39–18010; AD 2014–22–05] 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–9–10, DC–9–20, DC–9–30, DC–9–40, and DC– 9–50 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the improved ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct fatigue cracking of the bulkhead dome tees, which could result in reduced structural integrity and rapid decompression of the airplane. DATES: This AD is effective December 11, 2014. SUMMARY: (p) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A330–56–3009, Revision 03, including Appendixes 01 and 02, dated August 1, 2013. (ii) Airbus Service Bulletin A340–56–4008, Revision 02, including Appendix 01 and 02, dated August 1, 2013. 65891 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0232; 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5348; fax: 562–627–5210; email: eric.schrieber@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 certain The Boeing Company Model DC–9–10, DC–9–20, DC–9–30, DC–9–40, and DC–9–50 series airplanes. The NPRM published in the Federal Register on April 17, 2014 (79 FR 21655). The NPRM was prompted by an evaluation by the DAH indicating that the bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to WFD. The NPRM proposed to require repetitive inspections of the improved ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct E:\FR\FM\06NOR1.SGM 06NOR1 65892 Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 21655, April 17, 2014). Conclusion We reviewed the relevant data 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 21655, April 17, 2014) for correcting the unsafe condition; and fatigue cracking of the bulkhead dome tees, which could result in reduced structural integrity and rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 21655, April 17, 2014) or on the determination of the cost to the public. Costs of Compliance We estimate that this AD affects 48 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection ................................... Up to 148 work hours × $85 per hour = $12,580 per inspection cycle. We estimate the following costs to do any necessary replacements that would Parts cost Cost on U.S. operators Cost per product $0 Up to $12,580 per inspection cycle. be required based on the results of the inspection. We have no way of Up to $603,840 per inspection cycle. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement ................................................................. 4,000 work-hours × $85 per hour = $340,000 ............. 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. rmajette on DSK2TPTVN1PROD with RULES 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. 15:26 Nov 05, 2014 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 Regulatory Findings VerDate Sep<11>2014 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. Jkt 235001 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): ■ PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Parts cost $26,000 Cost per product $366,000 2014–22–05 The Boeing Company: Amendment 39–18010; Docket No. FAA–2014–0232; Directorate Identifier 2013–NM–100–AD. (a) Effective Date This AD is effective December 11, 2014. (b) Affected ADs This AD affects certain requirements of AD 96–16–04, Amendment 39–9704 (61 FR 39860, July 31, 1996). (c) Applicability This AD applies to The Boeing Company Model DC–9–11, DC–9–12, DC–9–13, DC–9– 14, DC–9–15, and DC–9–15F airplanes; Model DC–9–21 airplanes; Model DC–9–31, DC–9–32, DC–9–32 (VC–9C), DC–9–32F, DC– 9–33F, DC–9–34, DC–9–34F, and DC–9–32F (C–9A, C–9B) airplanes; Model DC–9–41 airplanes; and Model DC–9–51 airplanes; certificated in any category; equipped with a ventral aft pressure bulkhead. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the improved (shot-peened) ventral aft pressure bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the improved (shot-peened) ventral aft pressure bulkhead dome tees connecting the bulkhead web to the fuselage, which could result in reduced structural E:\FR\FM\06NOR1.SGM 06NOR1 Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations integrity and rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purposes of this AD, the term ‘‘original tee section’’ refers to the original (non-peened) ventral aft pressure bulkhead web to fuselage skin attach tee sections. (2) For the purposes of this AD, the term ‘‘improved tee section’’ refers to improved (shot peened) ventral aft pressure bulkhead web to fuselage skin attach tee sections. (h) Inspections For airplanes on which an improved tee section having P/N 5910130–389, 5910130– 391, 5910130–392, 5910130–393, 5910130– 394, 5910130–387, SR09530001–19, SR09530001–21, SR09530001–22, SR09530001–23, SR09530001–24, SR09530001–25, SR09530001–29, SR09530001–30, SR09530001–31, SR09530001–32, SR09530001–33, SR09530001–35, SR09530056–3, SR09530056–5, SR09530056–6, SR09530056–7, SR09530056–8, SR09530056–9, SR09530056–19, SR09530056–21, SR09530056–22, SR09530056–23, SR09530056–24, or SR09530056–25, is installed: At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, do general visual and low frequency eddy current inspections (Option I), or high and low frequency eddy current inspections (Option II), for cracking of the improved tee sections, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53–232, Revision 2, dated April 28, 1995. rmajette on DSK2TPTVN1PROD with RULES (i) Compliance Times (1) For Option I and Option II inspections specified in paragraph (h) of this AD: If the time of installation of an improved tee section having a part number listed in paragraph (h) of this AD, is known, do the initial inspection required by paragraph (h) of this AD within 70,000 flight cycles after installation of the improved tee section, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (2) For Option I and Option II inspections specified in paragraph (h) of this AD: If the time of installation of an improved tee section having a part number listed in paragraph (h) of this AD, is not known, do the initial inspection required by paragraph (h) of this AD before the accumulation of 105,000 total flight cycles on the airplane or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (j) Repetitive Inspections If no cracking is found during the inspection required by paragraph (h) of this AD: Do the actions specified in paragraph (j)(1) or (j)(2) of this AD, as applicable, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53–232, Revision 2, dated April 28, 1995. VerDate Sep<11>2014 15:26 Nov 05, 2014 Jkt 235001 65893 (1) For Option I: If Option I was used for the inspection required by paragraph (h) of this AD, repeat the inspections specified in paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of this AD at the intervals specified in paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of this AD. (i) Repeat the low frequency eddy current inspection for cracking of side areas above the floor between longerons L7 and L17 on the fuselage, at intervals not to exceed 1,500 flight cycles. (ii) Repeat the general visual inspection for cracking of the top and lower areas from longeron L7 left side to longeron L7 right side, and lower fuselage longeron L17 to longeron L20 on the left and right sides, at intervals not to exceed 1,500 flight cycles. (iii) Repeat the general visual inspection for cracking of the bottom areas from longeron L20 left side to longeron L20 right side, at intervals not to exceed 3,500 flight cycles. (2) For Option II: If Option II was used for the inspection required by paragraph (h) of this AD, repeat the high and low frequency eddy current inspection for cracking around the entire periphery of the fuselage on the forward side of the bulkhead, at intervals not to exceed 2,500 flight cycles. paragraph (m) of this AD. Information may 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. (k) Corrective Actions and Post-Replacement Inspections If any cracking is found during any inspection required by paragraph (h) or (j) of this AD: Before further pressurized flight, replace each cracked tee section with an airworthy tee section having a part number listed in paragraph (h) of this AD, or with an original tee section having P/N 5910130–47, 5910130–51, 5910130–53, 5910130–54, 5910130–55, or 5910130–56, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53–232, Revision 2, dated April 28, 1995. (1) If the tee section is replaced with an improved tee section listed in paragraph (h) of this AD, prior to the accumulation of 70,000 flight cycles after installation, inspect the tee section in accordance with paragraph (h) of this AD and do all applicable corrective actions and repetitive inspections in accordance with and at the times specified in paragraphs (j) and (k) of this AD. (2) If the tee section is replaced with an original tee section listed in paragraph (k) of this AD, prior to the accumulation of 35,000 flight cycles after installation, inspect the tee section in accordance with paragraph (h) of this AD and do all applicable corrective actions and repetitive inspections in accordance with and at the times specified in paragraphs (j) and (k) of this AD. (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. (3) The following service information was approved for IBR on September 4, 1996 (61 FR 39860, July 31, 1996). (i) McDonnell Douglas Alert Service Bulletin A53–232, Revision 2, dated April 28, 1995. (ii) Reserved. (4) 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. (5) You may view this service information 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. (6) 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. (l) 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 PO 00000 Frm 00021 Fmt 4700 Sfmt 9990 (m) Related Information For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712– 4137; phone: 562–627–5348; fax: 562–627– 5210; email: eric.schrieber@faa.gov. (n) Material Incorporated by Reference Issued in Renton, Washington, on October 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26331 Filed 11–5–14; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\06NOR1.SGM 06NOR1

Agencies

[Federal Register Volume 79, Number 215 (Thursday, November 6, 2014)]
[Rules and Regulations]
[Pages 65891-65893]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26331]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0232; Directorate Identifier 2013-NM-100-AD; 
Amendment 39-18010; AD 2014-22-05]
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-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-
50 series airplanes. This AD was prompted by an evaluation by the 
design approval holder (DAH) indicating that the bulkhead dome tees, 
which connect the bulkhead web to the fuselage, are subject to 
widespread fatigue damage (WFD). This AD requires repetitive 
inspections of the improved ventral aft pressure bulkhead tees, and 
replacement if necessary. We are issuing this AD to detect and correct 
fatigue cracking of the bulkhead dome tees, which could result in 
reduced structural integrity and rapid decompression of the airplane.

DATES: This AD is effective December 11, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 4, 
1996 (61 FR 39860, July 31, 1996).

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-
0232; 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: Eric Schrieber, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5348; fax: 562-627-5210; email: eric.schrieber@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 certain The Boeing Company 
Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. 
The NPRM published in the Federal Register on April 17, 2014 (79 FR 
21655). The NPRM was prompted by an evaluation by the DAH indicating 
that the bulkhead dome tees, which connect the bulkhead web to the 
fuselage, are subject to WFD. The NPRM proposed to require repetitive 
inspections of the improved ventral aft pressure bulkhead tees, and 
replacement if necessary. We are issuing this AD to detect and correct

[[Page 65892]]

fatigue cracking of the bulkhead dome tees, which could result in 
reduced structural integrity and rapid decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 21655, April 17, 
2014) 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 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 21655, April 17, 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 21655, April 17, 2014).

Costs of Compliance

    We estimate that this AD affects 48 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....................  Up to 148 work                 $0  Up to $12,580     Up to $603,840 per
                                 hours x $85 per                    per inspection    inspection cycle.
                                 hour = $12,580                     cycle.
                                 per inspection
                                 cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary 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 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement...................................  4,000 work-hours x $85 per hour          $26,000        $366,000
                                                 = $340,000.
----------------------------------------------------------------------------------------------------------------

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):

2014-22-05 The Boeing Company: Amendment 39-18010; Docket No. FAA-
2014-0232; Directorate Identifier 2013-NM-100-AD.

(a) Effective Date

    This AD is effective December 11, 2014.

(b) Affected ADs

    This AD affects certain requirements of AD 96-16-04, Amendment 
39-9704 (61 FR 39860, July 31, 1996).

(c) Applicability

    This AD applies to The Boeing Company Model DC-9-11, DC-9-12, 
DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 
airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-
33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model 
DC-9-41 airplanes; and Model DC-9-51 airplanes; certificated in any 
category; equipped with a ventral aft pressure bulkhead.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the improved (shot-peened) ventral aft 
pressure bulkhead dome tees, which connect the bulkhead web to the 
fuselage, are subject to widespread fatigue damage (WFD). We are 
issuing this AD to detect and correct fatigue cracking of the 
improved (shot-peened) ventral aft pressure bulkhead dome tees 
connecting the bulkhead web to the fuselage, which could result in 
reduced structural

[[Page 65893]]

integrity and rapid decompression of the airplane.

(f) Compliance

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

(g) Definitions

    (1) For the purposes of this AD, the term ``original tee 
section'' refers to the original (non-peened) ventral aft pressure 
bulkhead web to fuselage skin attach tee sections.
    (2) For the purposes of this AD, the term ``improved tee 
section'' refers to improved (shot peened) ventral aft pressure 
bulkhead web to fuselage skin attach tee sections.

(h) Inspections

    For airplanes on which an improved tee section having P/N 
5910130-389, 5910130-391, 5910130-392, 5910130-393, 5910130-394, 
5910130-387, SR09530001-19, SR09530001-21, SR09530001-22, 
SR09530001-23, SR09530001-24, SR09530001-25, SR09530001-29, 
SR09530001-30, SR09530001-31, SR09530001-32, SR09530001-33, 
SR09530001-35, SR09530056-3, SR09530056-5, SR09530056-6, SR09530056-
7, SR09530056-8, SR09530056-9, SR09530056-19, SR09530056-21, 
SR09530056-22, SR09530056-23, SR09530056-24, or SR09530056-25, is 
installed: At the applicable time specified in paragraph (i)(1) or 
(i)(2) of this AD, do general visual and low frequency eddy current 
inspections (Option I), or high and low frequency eddy current 
inspections (Option II), for cracking of the improved tee sections, 
in accordance with the Accomplishment Instructions of McDonnell 
Douglas Alert Service Bulletin A53-232, Revision 2, dated April 28, 
1995.

(i) Compliance Times

    (1) For Option I and Option II inspections specified in 
paragraph (h) of this AD: If the time of installation of an improved 
tee section having a part number listed in paragraph (h) of this AD, 
is known, do the initial inspection required by paragraph (h) of 
this AD within 70,000 flight cycles after installation of the 
improved tee section, or within 1,500 flight cycles after the 
effective date of this AD, whichever occurs later.
    (2) For Option I and Option II inspections specified in 
paragraph (h) of this AD: If the time of installation of an improved 
tee section having a part number listed in paragraph (h) of this AD, 
is not known, do the initial inspection required by paragraph (h) of 
this AD before the accumulation of 105,000 total flight cycles on 
the airplane or within 1,500 flight cycles after the effective date 
of this AD, whichever occurs later.

(j) Repetitive Inspections

    If no cracking is found during the inspection required by 
paragraph (h) of this AD: Do the actions specified in paragraph 
(j)(1) or (j)(2) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin A53-232, Revision 2, dated April 28, 1995.
    (1) For Option I: If Option I was used for the inspection 
required by paragraph (h) of this AD, repeat the inspections 
specified in paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of 
this AD at the intervals specified in paragraphs (j)(1)(i), 
(j)(1)(ii), and (j)(1)(iii) of this AD.
    (i) Repeat the low frequency eddy current inspection for 
cracking of side areas above the floor between longerons L7 and L17 
on the fuselage, at intervals not to exceed 1,500 flight cycles.
    (ii) Repeat the general visual inspection for cracking of the 
top and lower areas from longeron L7 left side to longeron L7 right 
side, and lower fuselage longeron L17 to longeron L20 on the left 
and right sides, at intervals not to exceed 1,500 flight cycles.
    (iii) Repeat the general visual inspection for cracking of the 
bottom areas from longeron L20 left side to longeron L20 right side, 
at intervals not to exceed 3,500 flight cycles.
    (2) For Option II: If Option II was used for the inspection 
required by paragraph (h) of this AD, repeat the high and low 
frequency eddy current inspection for cracking around the entire 
periphery of the fuselage on the forward side of the bulkhead, at 
intervals not to exceed 2,500 flight cycles.

(k) Corrective Actions and Post-Replacement Inspections

    If any cracking is found during any inspection required by 
paragraph (h) or (j) of this AD: Before further pressurized flight, 
replace each cracked tee section with an airworthy tee section 
having a part number listed in paragraph (h) of this AD, or with an 
original tee section having P/N 5910130-47, 5910130-51, 5910130-53, 
5910130-54, 5910130-55, or 5910130-56, in accordance with the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin A53-232, Revision 2, dated April 28, 1995.
    (1) If the tee section is replaced with an improved tee section 
listed in paragraph (h) of this AD, prior to the accumulation of 
70,000 flight cycles after installation, inspect the tee section in 
accordance with paragraph (h) of this AD and do all applicable 
corrective actions and repetitive inspections in accordance with and 
at the times specified in paragraphs (j) and (k) of this AD.
    (2) If the tee section is replaced with an original tee section 
listed in paragraph (k) of this AD, prior to the accumulation of 
35,000 flight cycles after installation, inspect the tee section in 
accordance with paragraph (h) of this AD and do all applicable 
corrective actions and repetitive inspections in accordance with and 
at the times specified in paragraphs (j) and (k) of this AD.

(l) 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 (m) of this AD. 
Information may 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.

(m) Related Information

    For more information about this AD, contact Eric Schrieber, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: 
eric.schrieber@faa.gov.

(n) 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.
    (3) The following service information was approved for IBR on 
September 4, 1996 (61 FR 39860, July 31, 1996).
    (i) McDonnell Douglas Alert Service Bulletin A53-232, Revision 
2, dated April 28, 1995.
    (ii) Reserved.
    (4) 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.
    (5) You may view this service information 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.
    (6) 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 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26331 Filed 11-5-14; 8:45 am]
BILLING CODE 4910-13-P