Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 76047 

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 to the extent that it justifies 

making a regulatory distinction, 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): 

2013–24–17 General Electric Company: 

Amendment 39–17694; Docket No. 

FAA–2013–0879; Directorate Identifier 

2013–NE–30–AD. 

(a) Effective Date 

This AD is effective December 31, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–110B1 and GE90–115B 

turbofan engines with high pressure 

compressor (HPC) rotor stage 2–5 spools, part 

numbers (P/Ns) 351–103–106–0, 351–103– 

107–0, 351–103–141–0, 351–103–142–0, 

351–103–144–0, 351–103–145–0, 351–103– 

148–0, 351–103–149–0, and 351–103–151–0, 

with spool serial numbers listed in paragraph 

4, Appendix A of GE Service Bulletin (SB) 

No. GE90–100 S/B 72–0499, dated August 14, 

2013. 

(d) Unsafe Condition 

This AD was prompted by reports of cracks 

in HPC rotor stage 2–5 spool aft spacer arms. 

We are issuing this AD to prevent failure of 

a critical life-limited rotating engine part, 

which could result in an uncontained engine 

failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Parts Removal 

Remove from service HPC rotor stage 2–5 

spools with serial numbers listed in 

paragraph 4, Appendix A of GE SB No. 

GE90–100 S/B 72–0499, dated August 14, 

2013, as follows: 

(1) For spools with fewer than 4,500 cycles 

since new (CSN) on the effective date of this 

AD, before exceeding 5,000 CSN. 

(2) For spools with 4,500 CSN or more but 

fewer than 5,200 CSN on the effective date 

of this AD, within an additional 500 cycles 

in service (CIS) after the effective date of this 

AD but not to exceed 5,500 CSN. 

(3) For spools with 5,200 CSN or more but 

fewer than 5,600 CSN on the effective date 

of this AD, within an additional 300 CIS after 

the effective date of this AD but not to exceed 

5,800 CSN. 

(4) For spools with 5,600 CSN or more but 

fewer than 5,800 CSN on the effective date 

of this AD, within an additional 200 CIS after 

the effective date of this AD but not to exceed 

5,850 CSN. 

(5) For spools with 5,800 CSN or more but 

fewer than 6,000 CSN on the effective date 

of this AD, within an additional 50 CIS after 

the effective date of this AD but not to exceed 

6,000 CSN. 

(6) For spools with 6,000 CSN or more on 

the effective date of this AD, before the next 

flight. 

(7) For spools that are not installed on the 

effective date of this AD and are 

subsequently installed onto any engine after 

the effective date of this AD, before 

exceeding 5,000 CSN. 

(g) Prohibition Statement 

After the effective date of this AD, do not 

install or re-install onto any engine any HPC 

rotor stage 2–5 spool with a serial number 

listed in paragraph 4, Appendix A of GE SB 

No. GE90–100 S/B 72–0499, dated August 14, 

2013, that exceeds 5,000 CSN. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve alternative methods of 

compliance for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7735; fax: (781) 

238–7199; email: tomasz.rakowski@faa.gov. 

(j) 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) General Electric Company (GE) Service 

Bulletin No. GE90–100 S/B 72–0499, dated 

August 14, 2013. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, phone: (513) 552– 

3272; email: geae.aoc@ge.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call (781) 238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

November 27, 2013. 

Carlos A. Pestana, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–29055 Filed 12–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0704; Directorate 

Identifier 2013–NM–074–AD; Amendment 

39–17695; AD 2013–24–18] 

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 747–200B, 

–200C, –200F, –300, and 747SR series 

airplanes. This AD was prompted by 

reports of cracks of both lower chords 

and web on certain outboard struts. This 

AD requires repetitive inspections for 

cracking of the lower spar chords and 

web, web lower spar chord 

modification, which includes 

inspections for cracking of the lower 

spar chords, and repetitive post 

modification inspections for cracking of 

the lower spar web and chord; and 

applicable corrective actions. We are 

issuing this AD to prevent cracked 

chords and web on certain outboard 

struts, which, if the chord severs, could 

result in reduced structural integrity of 

the diagonal brace load path and of the 

strut-to-wing attachment, and 


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76048 Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 

consequent separation of a strut and 

engine from the airplane during flight. 

DATES: This AD is effective January 21, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 21, 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, Washington. 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; 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 the specified products. The 

NPRM published in the Federal 

Register on August 28, 2013 (78 FR 

53078). The NPRM proposed to require 

repetitive inspections for cracking of the 

lower spar chords and web, web lower 

spar chord modification, which 

includes inspections for cracking of the 

lower spar chords, and repetitive post 

modification inspections for cracking of 

the lower spar web and chord; and 

applicable corrective actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing stated that it supports the NPRM 

(78 FR 53078, August 28, 2013). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the 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 (78 FR 

53078, August 28, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 53078, 

August 28, 2013). 

Costs of Compliance 

We estimate that this AD affects 25 

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 .................... 27 work-hours × $85 per hour = $2,295 per inspection cycle.$0 $2,295 per inspection 

cycle.

$57,375 per inspection 

cycle. 

Modification ................... 11 work-hours × $85 per hour = $935 ............... 95 $1,030 .......................... $25,750. 

Post Modification Inspection.27 work-hours × $85 per hour = $2,295 per inspection cycle.0 $2,295 per inspection 

cycle.

$57,375 per inspection 

cycle. 

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. 


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Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 76049 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–24–18 The Boeing Company: 

Amendment 39–17695; Docket No. 

FAA–2013–0704; Directorate Identifier 

2013–NM–074–AD. 

(a) Effective Date 

This AD is effective January 21, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–200B, 747–200C, 747–200F, 747– 

300, and 747SR series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

of both lower chords and web on certain 

outboard struts. We are issuing this AD to 

prevent cracked chords and web on certain 

outboard struts, which, if the chord severs, 

could result in reduced structural integrity of 

the diagonal brace load path and of the strutto-wing attachment, and consequent 

separation of a strut and engine from the 

airplane during flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial and Repetitive Inspections 

Except as required by paragraph (j)(1) of 

this AD, at the compliance time specified in 

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

Boeing Alert Service Bulletin 747–54A2237, 

dated March 14, 2013: Do a detailed 

inspection for cracking of the lower spar 

chords and web, a high frequency eddy 

current (HFEC) inspection for cracking of the 

lower spar chords, and all applicable repairs 

and modifications, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013, except as required by paragraph 

(j)(2) of this AD. If no cracking is found, 

repeat the inspections thereafter at intervals 

not to exceed 600 flight cycles, until the 

actions specified in paragraph (h) of this AD 

have been accomplished. Do all applicable 

corrective actions before further flight. 

Accomplishing a repair and modification, 

including open-hole HFEC inspections for 

cracking and applicable corrective actions 

required by this paragraph terminates the 

actions required by paragraphs (g) and (h) of 

this AD for the repaired and modified strut 

only. The open-hole HFEC inspection for 

cracking must be done before the 

modification. 

(h) Inspection and Modification 

Except as required by paragraph (j)(1) of 

this AD, at the compliance time specified in 

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

Alert Service Bulletin 747–54A2237, dated 

March 14, 2013: Do a detailed inspection for 

cracking of the lower spar chords and web, 

an HFEC inspection for cracking of the lower 

spar chords, a lower spar chord modification, 

including open-hole HFEC inspections for 

cracking in the chord and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013, except as required by paragraph 

(j)(2) of this AD. Do all applicable corrective 

actions before further flight. Doing the 

actions specified in this paragraph terminates 

the requirements of paragraph (g) of this AD 

for the modified strut only. The open-hole 

HFEC inspection for cracking must be done 

before the modification. 

(i) Post Modification Repetitive Inspections 

For airplanes on which a modification 

required by paragraph (g) or (h) of this AD 

has been done: At the compliance time 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2237, dated March 14, 

2013, do a detailed inspection for any 

cracking of the lower spar web and chord, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, except 

as required by paragraph (j)(2) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed 18 months. Do all applicable 

corrective actions before further flight. 

(j) Exceptions 

(1) Where Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, 

specifies a compliance time after the original 

issue date on the service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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) 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. 

(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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

54A2237, dated March 14, 2013. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at FAA, 1601 Lind Avenue SW., Renton, 

Washington. 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 26, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–29051 Filed 12–13–13; 8:45 am] 

BILLING CODE 4910–13–P 


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