Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43611 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 July 15, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17316 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0253; Directorate 

Identifier 2013–NM–257–AD; Amendment 

39–17908; AD 2014–15–06] 

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 747–100B 

SUD, 747–200B, 747–300, 747–400, and 

747–400D series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the upper deck tension 

ties are subject to widespread fatigue 

damage (WFD). This AD requires 

repetitive inspections for cracking in the 

upper deck tension ties, and related 

investigative and corrective actions if 

necessary; tension tie replacement; and 

post-replacement repetitive inspections 

for cracking in the upper deck tension 

ties, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the upper deck 

tension ties. Severed or disconnected 

tension ties at multiple locations could 

result in rapid decompression and loss 

of structural integrity of the airplane. 

DATES: This AD is effective September 2, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 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– 

0253; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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 747–100B SUD, 747–200B, 747– 

300, 747–400, 747–400D series 

airplanes. The NPRM published in the 

Federal Register on April 23, 2014 (79 

FR 22596). The NPRM was prompted by 

an evaluation by the DAH indicating 

that the upper deck tension ties are 

subject to WFD. The NPRM proposed to 

require repetitive inspections for 

cracking in the upper deck tension ties, 

and related investigative and corrective 

actions if necessary; tension tie 

replacement; and post-replacement 

repetitive inspections for cracking in the 

upper deck tension ties, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper deck tension ties. Severed or 

disconnected tension ties at multiple 

locations could result in rapid 

decompression and loss of structural 

integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The Boeing Company supported the 

NPRM (79 FR 22596, April 23, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 

22596, April 23, 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 22596, 

April 23, 2014). 

Costs of Compliance 

We estimate that this AD affects 76 

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 

Inspections (pre-modification 

and post-modification).

Up to 164 work-hours × $85 

per hour = $13,940 per inspection cycle.

$0 Up to $13,940 per inspection 

cycle.

Up to $1,059,440 per inspection cycle. 


pmangrum on DSK3VPTVN1PROD with RULES
43612 Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 

ESTIMATED COSTS—Continued 

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

Modification ............................ 366 work-hours × $85 per 

hour = $31,110.

0 $31,110 .................................. $2,364,360. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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): 

2014–15–06 The Boeing Company: 

Amendment 39–17908; Docket No. 

FAA–2014–0253; Directorate Identifier 

2013–NM–257–AD. 

(a) Effective Date 

This AD is effective September 2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100B SUD, 747–200B, 747–300, 

747–400, and 747–400D series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–53A2866, 

dated December 4, 2013. 

(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 upper deck tension ties are subject 

to widespread fatigue damage (WFD). We are 

issuing this AD to detect and correct fatigue 

cracking of the upper deck tension ties. 

Severed or disconnected tension ties at 

multiple locations could result in rapid 

decompression and loss of structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections, Related Investigative 

Actions, and Corrective Actions 

For airplanes identified as Group 1, 

Configuration 2; and Group 2; in Boeing Alert 

Service Bulletin 747–53A2866, dated 

December 4, 2013: Before the accumulation 

of 10,000 flight cycles after conversion to 

special freighter or Boeing converted 

freighter configuration, or within 2,000 flight 

cycles after the effective date of this AD, 

whichever occurs later, do the actions 

specified in paragraph (g)(1) or (g)(2) of this 

AD, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2866, dated December 4, 2013, 

except as provided by paragraph (h) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspection of the forward and aft 

tension tie channels thereafter at the 

applicable time and intervals specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2866, dated 

December 4, 2013. 

(1) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels. 

(2) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels, and 

do a surface high frequency eddy current 

(HFEC) inspection for cracks around 

fasteners in the tension tie channels. 

(h) Exceptions to Service Information 

Specifications 

If, during accomplishment of the related 

investigative action or inspections required 

by this AD, any cracking is found, and 

Boeing Alert Service Bulletin 747–53A2866, 

dated December 4, 2013, specifies to contact 

Boeing for repair instructions: Before further 

flight, do the repair using a method approved 

in accordance with the procedures specified 

in paragraph (k) of this AD. 

(i) Tension Tie Replacement 

After the accumulation of 13,000 total 

flight cycles; but before the accumulation of 

22,000 flight cycles after conversion to 

special freighter or Boeing converted 

freighter configuration, or within 2,000 flight 

cycles after the effective date of this AD, 

whichever occurs later: Do the tension tie 

replacement, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2866, dated 

December 4, 2013, except as provided by 

paragraph (h) of this AD. Accomplishment of 

the actions required by this paragraph 

terminates the inspection requirements of 

paragraph (g) of this AD. 

(j) Post-tension Tie Replacement Inspections, 

Related Investigative Actions, and 

Corrective Actions 

After accomplishing the actions required 

by paragraph (i) of this AD: At the applicable 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2866, dated December 4, 

2013, do the actions specified in paragraph 

(j)(1) or (j)(2) of this AD; and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43613 

Instructions of Boeing Alert Service Bulletin 

747–53A2866, dated December 4, 2013, 

except as provided by paragraph (h) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the applicable inspection of the 

forward and aft tension tie channels 

thereafter at the applicable time and intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2866, 

dated December 4, 2013. 

(1) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels. 

(2) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels, and 

do a surface HFEC inspection for cracks 

around fasteners in the tension tie channels. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 

be emailed to: 9-ANM-Seattle-ACO-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, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(l) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(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 this AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2866, dated December 4, 2013, 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(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 July 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17312 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0055; Directorate 

Identifier 2013–NM–167–AD; Amendment 

39–17907; AD 2014–15–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A310–304, –322, –324, 

and –325 airplanes. This AD was 

prompted by reports of insufficient 

clearance between the fuel quantity 

indicator (FQI) probes and the adjacent 

structure and metallic components in 

the wing fuel tanks. This AD requires a 

one-time detailed visual inspection for 

sufficient clearance between FQI probes 

on both the left-hand side and righthand side of the trim horizontal 

stabilizer and the adjacent structure and 

metallic components in the fuel tanks, 

and modification if necessary. We are 

issuing this AD to detect and correct 

insufficient clearance, which could lead 

to electrical arcing in a fuel tank during 

a lightning strike, which could result in 

ignition and consequent fire or 

explosion in the fuel tank. 

DATES: This AD becomes effective 

September 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0055; 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 Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

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 Airbus Model A310– 

304, –322, –324, and –325 airplanes. 

The NPRM published in the Federal 

Register on February 25, 2014 (79 FR 

10431). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0188, 

dated August 19, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information to correct an 

unsafe condition on certain Airbus 


pmangrum on DSK3VPTVN1PROD with RULES