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 

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 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. 

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

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................... 5 work-hours × $85 per hour = $425 per inspection cycle.$0 $425 per inspection 

cycle.

$283,900 per 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: 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 64085 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair ........................................... Up to 394 work-hours × $85 per hour = $33,490 .............................. Up to $32,440 ..... Up to $65,930. 

Replacement ................................. Up to 394 work-hours × $85 per hour = $33,490 .............................. Up to $60,222 ..... Up to $93,712. 

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): 

2014–21–04 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 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 


asabaliauskas on DSK5VPTVN1PROD with RULES
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. 

(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 

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 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: 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 

Coˆte-Vertu Road West, Dorval, Que ́bec 

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 

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-2014-0287- 

0002. 

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. 


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