Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65891 

–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-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) 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. 

(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. 

(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. 

(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. 

Issued in Renton, Washington, on 

September 24, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[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 

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 


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65892 Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 

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 hours × $85 per 

hour = $12,580 per inspection 

cycle.

$0 Up to $12,580 per inspection 

cycle.

Up to $603,840 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

Action Labor cost Parts cost Cost per 

product 

Replacement ................................................................. 4,000 work-hours × $85 per hour = $340,000 ............. $26,000 $366,000 

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 

■ 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): 

2014–22–05 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 


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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 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-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. 

(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/ibrlocations.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 


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