Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70441 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2014-0191; 

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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2014–23–14 Bombardier, Inc.: Amendment 

39–18030. Docket No. FAA–2014–0191; 

Directorate Identifier 2013–NM–256–AD. 

(a) Effective Date 

This AD becomes effective December 31, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes; 

certificated in any category; serial numbers 

4001, and 4003 through 4417 inclusive, with 

installed engine fuel feed ejector pump 

having part number (P/N) 2960008–102. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of swing 

arm assemblies of engine fuel feed ejector 

pumps detaching from the outlet port of the 

engine fuel feed ejector pump and partially 

blocking the engine fuel feed line. We are 

issuing this AD to prevent blocked engine 

fuel flow and possible engine flameout. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation 

Within 6,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD, install a restrictor into the engine 

fuel feed line, in accordance with paragraph 

3.B., ‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–28–16, Revision B, dated June 17, 2013. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 84–28–16, dated July 16, 2012; or 

Bombardier Service Bulletin 84–28–16, 

Revision A, dated May 23, 2013; which are 

not incorporated by reference in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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: 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–35, dated 

November 15, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2014-0191- 

0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) 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) Bombardier Service Bulletin 84–28–16, 

Revision B, dated June 17, 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 

November 6, 2014. 

Jeffrey E. Duven 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27357 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0170; Directorate 

Identifier 2013–NM–169–AD; Amendment 

39–18027; AD 2014–23–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2005–13– 

05, which applied to certain Boeing 

Model 747–400F series airplanes. AD 

2005–13–05 required inspections for 

cracking of the web, upper chord, and 

upper chord strap of the upper deck 

floor beams, and repair of any cracking. 

AD 2005–13–05 also required a 

preventive modification of the upper 

deck floor beams, and repetitive 

inspections for cracking after 

accomplishing the modification. This 

new AD retains these actions and 

requires a second modification, 

repetitive inspections for cracking, and 

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70442 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

repair if necessary. This AD was 

prompted by a determination that the 

upper chords of the upper deck floor 

beams at certain stations are structures 

that are susceptible to widespread 

fatigue damage, and that certain 

airplanes with an initial modification 

require a second modification for the 

airplane to meet its limit of validity 

(LOV). We are issuing this AD to detect 

and correct fatigue cracking in certain 

upper chords of the upper deck floor 

beam, which could result in reduced 

structural integrity of the airplane and 

rapid decompression or reduced 

controllability of the airplane. 

DATES: This AD is effective December 

31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of July 27, 2005 (70 FR 

35989, June 22, 2005). 

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– 

0170; 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 

(ACO), 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 to supersede AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, 

June 22, 2005). AD 2005–13–05 applied 

to certain Boeing Model 747–400F series 

airplanes. The NPRM published in the 

Federal Register on March 25, 2014 (79 

FR 16241). The NPRM was prompted by 

a determination that the upper chords of 

the upper deck floor beams at certain 

stations are structures that are 

susceptible to widespread fatigue 

damage, and that certain airplanes with 

an initial modification require a second 

modification for the airplane to meet its 

LOV. The NPRM proposed to continue 

to require inspections for cracking of the 

web, upper chord, and upper chord 

strap of the upper deck floor beams, and 

repair of any cracking; a preventive 

modification of the upper deck floor 

beams; and repetitive inspections for 

cracking after accomplishing the 

modification. The NPRM proposed to 

also require a second modification, 

repetitive inspections for cracking, and 

repair if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking in certain upper chords of the 

upper deck floor beam, which could 

result in reduced structural integrity of 

the airplane and rapid decompression or 

reduced controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 16241, 

March 25, 2014) and the FAA’s response 

to each comment. 

Request To Clarify Post-Modification 

Inspection Options 

Boeing requested that we revise 

paragraphs (j) and (l) of the NPRM (79 

FR 16241, March 25, 2014) to clarify 

that the inspection options of 

paragraphs (j)(2) and (l)(2) are 

applicable only when the primary 

preventative modification option has 

been accomplished. Boeing stated that 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, added 

an alternative preventative modification 

option for which the inspection options 

of paragraphs (j)(2) and (l)(2) of this AD 

are not viable. 

We agree with the commenter’s 

request because these words add clarity 

as to which inspection option should be 

used. We have revised paragraphs (j) 

and (l) of this AD by stating that, as of 

the effective date of this AD, for 

airplanes on which the alternative 

preventive modification has been 

accomplished, only the inspection 

methods specified by paragraphs (j)(1) 

and (l)(1), respectively, of this AD may 

be used. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

16241, March 25, 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 16241, 

March 25, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 13 

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 

Pre-modification inspections (retained actions from 

AD 2005–13–05, Amendment 39–14141 (70 FR 

35989, June 22, 2005)).

11 work-hours × $85 per hour = 

$935.

$0 ..................... $935 $12,155. 

Modification/inspections done during modification 

(retained actions from AD 2005–13–05, Amendment 39–14141 (70 FR 35989, June 22, 2005)).

Up to 524 work-hours × $85 per 

hour = $44,540.

Up to $14,874 .. 59,414 $772,382. 

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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70443 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Post-modification inspections (retained actions from 

AD 2005–13–05, Amendment 39–14141 (70 FR 

35989, June 22, 2005)).

66 work-hours × $85 per hour = 

$5,610.

$0 ..................... 5,610 $72,930. 

Zero-Timing Procedure Option 1 (including inspections) (new action).71 work-hours × $85 per hour = 

$6,035.

$0 ..................... 6,035 Up to $78,455. 

Zero-Timing Procedure Option 2 (including inspections) (new action).103 work-hours × $85 per hour = 

$8,755.

$0 ..................... 8,755 Up to $113,815. 

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 

We have determined that 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 

removing Airworthiness Directive (AD) 

2005–13–05, Amendment 39–14141 (70 

FR 35989, June 22, 2005), and adding 

the following new AD: 

2014–23–11 The Boeing Company: 

Amendment 39–18027 ; Docket No. 

FAA–2014–0170; Directorate Identifier 

2013–NM–169–AD. 

(a) Effective Date 

This AD is effective December 31, 2014. 

(b) Affected ADs 

This AD replaces AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400F series airplanes, certificated 

in any category, as identified in Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that the upper chords of the upper 

deck floor beams at stations (STA) 340 

through 520 have been determined to be 

structures that are susceptible to widespread 

fatigue damage, and airplanes that had an 

initial modification done before 15,000 total 

flight cycles require a second fastener hole 

zero-timing modification for the airplane to 

meet its limit of validity (LOV). We are 

issuing this AD to detect and correct fatigue 

cracking in certain upper chords of the upper 

deck floor beam, which could result in 

reduced structural integrity of the airplane 

and rapid decompression or reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), with revised service information. 

Before the accumulation of 15,000 total flight 

cycles, or within 1,000 flight cycles after July 

27, 2005 (the effective date of AD 2005–13– 

05), whichever is later: Accomplish detailed 

and open-hole high frequency eddy current 

(HFEC) inspections for cracking of the web, 

upper chord, and upper chord strap of the 

upper deck floor beams, by doing all the 

applicable actions in accordance with Part 

3.B.1. of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, dated 

May 9, 2002; or Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. As of the effective date 

of this AD, only Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

may be used. 

(h) Retained Repair With Revised Service 

Information and Revised Repair Approval 

Language 

This paragraph restates the requirements of 

paragraph (h) of AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), with revised service information 

and revised repair approval language. If any 

crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, accomplish the actions 

required by paragraph (h)(1) and (h)(2) of this 

AD. 

(1) Repair in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013; except 

where these service bulletins specify to 

contact Boeing for appropriate action, before 

further flight, repair the cracking using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. As of the effective date of this AD, only 

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70444 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Accomplish the inspections and 

preventive modification of the floor beams by 

doing all the actions in accordance with Part 

3.B.2. or Part 3.B.3., as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 2 or Part 3, as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. If any crack is found 

during any inspection, before further flight, 

repair as required by paragraph (h)(1) of this 

AD. As of the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(i) Retained Modification With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2005–13–05, Amendment 

39–14141 (70 FR 35989, June 22, 2005), with 

revised service information. If no crack is 

found during any inspection required by 

paragraph (g) of this AD: Accomplish the 

actions required by either paragraph (i)(1) or 

(i)(2) of this AD, at the time specified. 

(1) Before further flight: Accomplish the 

inspections and preventive modification of 

the floor beam by doing all the actions in 

accordance with Part 3.B.2 or Part 3.B.3., as 

applicable, of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, dated May 9, 2002; or Part 2 or Part 

3, as applicable, of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

If the preventive modification is performed 

concurrently with the inspections required 

by paragraph (g) of this AD, the upper chord 

straps must be removed when performing the 

open-hole HFEC inspection. If any crack is 

found during any inspection, before further 

flight, repair as required by paragraph (h)(1) 

of this AD. As of the effective date of this AD, 

only Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Before the accumulation of 20,000 total 

flight cycles, or within 1,000 flight cycles 

after July 27, 2005 (the effective date of AD 

2005–13–05, Amendment 39–14141 (70 FR 

35989, June 22, 2005), whichever is later: 

Accomplish the inspections and preventive 

modification of the upper deck floor beams, 

by doing all the actions in accordance with 

Part 3.B.2. or 3.B.3. as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 2 or Part 3, as applicable, of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, Revision 2, 

dated August 2, 2013. If any crack is found 

during any inspection, before further flight, 

repair as required by paragraph (h)(1) of this 

AD. As of the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(j) Retained Post-Modification Inspections 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (j) of AD 2005–13–05, Amendment 

39–14141 (70 FR 35989, June 22, 2005), with 

revised service information. Within 15,000 

flight cycles after accomplishing the 

applicable preventive modification required 

by paragraph (h)(2), (i)(1), or (i)(2) of this AD: 

Accomplish the applicable inspections 

required by either paragraph (j)(1) or (j)(2) of 

this AD; if any crack is found during any 

inspection, before further flight, repair as 

required by paragraph (h)(1) of this AD. As 

of the effective date of this AD, for airplanes 

on which the alternative preventive 

modification, as identified in the NOTE after 

step 3. of ‘‘PART 2—INSPECTION AND 

PREVENTIVE MODIFICATION,’’ or as 

identified in the NOTE after step 4. of ‘‘PART 

3—INSPECTION AND PREVENTIVE 

MODIFICATION,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

has been done, only the inspection specified 

by paragraph (j)(1) of this AD may be used. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and upper chord strap of the upper 

deck floor beams, by doing all the applicable 

actions in accordance with Part 3.B.4. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 4 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

If no crack is found, repeat the inspections 

at intervals not to exceed 1,000 flight cycles. 

As of the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and strap of the upper deck 

floor beams, by doing all the applicable 

actions in accordance with Part 3.B.5. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2443, dated May 9, 

2002; or Part 5 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

If no crack is found, repeat the inspections 

at intervals not to exceed 5,000 flight cycles. 

As of the effective date of this AD, only 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013, may be 

used. 

(k) New Floor Beam Hole Zero-Timing 

Within 20,000 flight cycles after 

accomplishing the preventive modification of 

the Station 340 to Station 520 upper deck 

floor beams specified in paragraph (h)(2), 

(i)(1), or (i)(2) of this AD, or within 1,000 

flight cycles after the effective date of this 

AD, whichever occurs later: Accomplish the 

floor beam hole zero-timing, in accordance 

with Part 6 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013. 

(l) New Post-Modification Floor Beam Hole 

Zero-Timing Inspections 

Within 15,000 flight cycles after 

accomplishing the floor beam hole zerotiming required by paragraph (k) of this AD: 

Accomplish the applicable inspections 

required by paragraph (l)(1) or (l)(2) of this 

AD; if any cracking is found during any 

inspection, before further flight, repair as 

required by paragraph (h)(1) of this AD. As 

of the effective date of this AD, for airplanes 

on which the alternative preventive 

modification, as identified in the NOTE after 

step 3. of ‘‘PART 2—INSPECTION AND 

PREVENTIVE MODIFICATION,’’ or as 

identified in the NOTE after step 4. of ‘‘PART 

3—INSPECTION AND PREVENTIVE 

MODIFICATION,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

has been done, only the inspection method 

specified by paragraph (l)(1) of this AD may 

be used. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 4 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 1,000 flight cycles. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 5 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 5,000 flight cycles. 

(m) Exception to Service Information 

Where Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

specifies a compliance time ‘‘after the 

revision date on this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

inspections, repairs, and modification 

required by paragraphs (g) through (j) of this 

AD, if the corresponding actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 747–53A2443, 

Revision 1, dated June 25, 2009. 

(o) 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 (p)(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 

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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70445 

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) AMOCs approved for AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), are approved as AMOCs for the 

corresponding requirements of paragraphs (g) 

through (j) (the retained actions) of this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

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

917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) 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 December 31, 2014. 

(i) Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on July 27, 2005 (70 FR 

35989, June 22, 2005). 

(i) Boeing Service Bulletin 747–53A2443, 

dated May 9, 2002. 

(ii) Reserved. 

(5) 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. 

(6) 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. 

(7) 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 

November 6, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27358 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0174; Directorate 

Identifier 2013–NM–212–AD; Amendment 

39–18028; AD 2014–23–12] 

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 787–8 

airplanes. This AD was prompted by a 

report indicating that, on a different 

Boeing airplane model, there was an 

oxygen-fed fire, which caused extensive 

damage to the flight deck. This AD 

requires replacing the low-pressure 

oxygen hoses with non-conductive 

hoses in the crew oxygen system. We 

are issuing this AD to prevent 

inadvertent electrical current from 

passing through an internal, anticollapse spring of the low pressure 

oxygen hose, which can cause the lowpressure oxygen hose to melt or burn, 

leading to an oxygen-fed fire and/or 

smoke beneath the flight deck in the 

forward electronics equipment bay. 

DATES: This AD is effective December 

31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 31, 2014. 

ADDRESSES: For Boeing 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. For B/E 

Aerospace service information 

identified in this AD, contact B/E 

Aerospace, Inc., Commercial Aircraft 

Products Group, 10800 Pfluum Road, 

Lenexa, KS 66215; phone: 913–338– 

9800; fax: 913–469–8419. 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– 

0174; 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: 

Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6457; fax: 425– 

917–6590; email: susan.l.monroe@

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 787–8 airplanes. The NPRM 

published in the Federal Register on 

March 28, 2014 (79 FR 17457). The 

NPRM was prompted by a report 

indicating that, on a different Boeing 

airplane model, there was an oxygen-fed 

fire, which caused extensive damage to 

the flight deck. The NPRM proposed to 

require replacing the low-pressure 

oxygen hoses with non-conductive 

hoses in the crew oxygen system. We 

are issuing this AD to prevent 

inadvertent electrical current from 

passing through an internal, anticollapse spring of the low pressure 

oxygen hose, which can cause the lowpressure oxygen hose to melt or burn, 

leading to an oxygen-fed fire and/or 

smoke beneath the flight deck in the 

forward electronics equipment bay. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 17457, 

March 28, 2014) and the FAA’s response 

to each comment. 

Boeing, United Airlines, and John 

Johnson stated that they support the 

NPRM (79 FR 17457, March 28, 2014). 

Request To Shorten Compliance Time 

The Air Line Pilots Association 

(ALPA) stated that it supports the intent 

of the NPRM (79 FR 17457, March 28, 

2014) but that the 60-month compliance 

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