70214 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

(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 the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 12, 

2012. 

(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 FAA, Transport Airplane Directorate, 1601 

Lind Ave 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, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27843 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0461; Directorate 

Identifier 2012–NM–169–AD; Amendment 

39–17670; AD 2013–23–15] 

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) 2009–06– 

02, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747SR, 

and 747SP series airplanes. AD 2009– 

06–02 required repetitive inspections 

for skin cracks at the shear tie end 

fastener locations of the fuselage frames, 

and repair of cracks if necessary. This 

new AD also requires repetitive 

inspections for skin cracks next to the 

shear tie on airplanes with certain 

existing repair doublers, and corrective 

actions if necessary. This AD also 

revises the applicability to include 

additional airplanes. This AD was 

prompted by additional cracking found 

on an airplane not affected by AD 2009– 

06–02. We are issuing this AD to detect 

and correct fatigue cracks in the fuselage 

skin that can propagate and grow, and 

result in reduced structural integrity 

and sudden decompression of the 

airplane in flight. 

DATES: This AD is effective December 

30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 30, 2013. 

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 

Document 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–06–02, 

Amendment 39–15838 (74 FR 11013, 

March 16, 2009). AD 2009–06–02 

applied to the specified products. The 

NPRM published in the Federal 

Register on June 3, 2013 (78 FR 33012). 

The NPRM proposed to continue to 

require repetitive inspections for skin 

cracks at the shear tie end fastener 

locations of the fuselage frames, and 

repair of cracks if necessary. The NPRM 

also proposed to require repetitive 

inspections for skin cracks next to the 

shear tie on airplanes with certain 

existing repair doublers, and corrective 

actions if necessary. The NPRM also 

proposed to revise the applicability to 

include additional airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 33012, 

June 3, 2013) and the FAA’s response to 

each comment. 

Request To Revise Repetitive Inspection 

Type 

Boeing requested that we revise 

paragraph (h) of the NPRM (78 FR 

33012, June 3, 2013) to correct the 

required inspection method for the 

repetitive inspections. The NPRM 

specified repeating the ‘‘external 

detailed inspection’’ at the times 

specified in table 4 or table 5 of Boeing 

Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012. Boeing 

noted however that the compliance 

times in those tables are for internal 

high frequency eddy current (HFEC) 

inspection. 

We agree with the request. Paragraph 

(h) of this AD requires an internal HFEC 

inspection; the inspections that must be 

repeated are also internal HFEC 

inspections. We have revised paragraph 

(h) in this final rule to specify that the 

inspection to be repeated is an internal 

HFEC inspection. 

Request To Revise Description of 

Unsafe Condition 

Boeing requested that we revise the 

description of the unsafe condition to 

clarify that the subject of the unsafe 

condition is the fuselage area—not the 

frame shear ties, as stated in the NPRM 

(78 FR 33012, June 3, 2013). 

We agree with the request and 

rationale. We have revised paragraph (e) 

in this final rule to explain that the 

fuselage skin—not the ties themselves— 

is subject to widespread fatigue damage. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 


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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70215 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

33012, June 3, 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 33012, 

June 3, 2013). 

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 234 

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 ...... 30 or 49 work-hours (depending on inspection) × 

$85 per hour = $2,550 or $4,165 per inspection 

cycle.

$0 $2,550 or $4,165 per inspection cycle.Up to $974,610 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 

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) 

2009–06–02, Amendment 39–15838 (74 

FR 11013, March 16, 2009), and adding 

the following new AD: 

2013–23–15 The Boeing Company: 

Amendment 39–17670; Docket No. 

FAA–2013–0461; Directorate Identifier 

2012–NM–169–AD. 

(a) Effective Date 

This AD is effective December 30, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–06–02, 

Amendment 39–15838 (74 FR 11013, March 

16, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, as identified in 

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

certain fuselage frames are subject to 

widespread fatigue damage. The actions were 

developed to support the airplane’s limit of 

validity of the engineering data that support 

the established structural maintenance 

program. We are issuing this AD to detect 

and correct fatigue cracks in the fuselage skin 

that can propagate and grow, and result in 

reduced structural integrity and sudden 

decompression of the airplane in flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable compliance time 

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

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012, except as 

provided by paragraphs (i)(1) and (i)(2) of 

this AD, do an external detailed or high 

frequency eddy current (HFEC) inspection for 

skin cracks at specified shear tie end fastener 

locations of the fuselage frames, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the external detailed or HFEC 

inspection thereafter at the applicable time 

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

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012. 

(h) Post-Repair Inspections 

For any external repair doubler in the 

inspection area specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2682, Revision 1, 

dated May 24, 2012, that has an upper or 

lower fastener row that is common to a shear 

tie end fastener: At the applicable time 

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

AD, whichever occurs later, do an internal 

HFEC inspection for cracks in the skin next 

to the shear tie, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2682, Revision 1, 

dated May 24, 2012, except as required by 


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70216 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

paragraph (i)(3) of this AD. Do all corrective 

actions before further flight. Repeat the 

internal HFEC inspection thereafter at the 

time specified in Table 4 or Table 5 of 

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

Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012, as 

applicable. 

(1) Before further flight after an inspection 

required by paragraph (g) of this AD. 

(2) Within 2,000 flight cycles after the 

effective date of this AD. 

(i) Service Information Clarifications and 

Exceptions 

(1) Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012, specifies 

certain compliance times in terms of the 

effective date of AD 2009–06–02, 

Amendment 39–15838 (74 FR 11013, March 

16, 2009). The effective date of AD 2009–06– 

02 is April 20, 2009. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012, specifies 

counting the compliance time ‘‘after the 

revision 1 date of this service bulletin,’’ this 

AD requires compliance within the 

applicable time after the effective date of this 

AD. 

(3) Where Boeing Alert Service Bulletin 

747–53A2682, Revision 1, dated May 24, 

2012, specifies to contact Boeing for repair 

instructions, this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) 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 747–53A2682, dated May 8, 

2008. 

(k) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(l) 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 (m)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

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

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2682, Revision 1, dated May 24, 2012. 

(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 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. 

(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, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27845 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0561; Directorate 

Identifier 2013–NE–23–AD; Amendment 39– 

17680; AD 2013–24–06] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Thielert Aircraft Engines GmbH TAE 

125–01 reciprocating engines. This AD 

requires applying sealant to close the 

engine clutch housing (crankcase 

assembly) opening. This AD was 

prompted by a report of engine power 

loss due to engine coolant 

contaminating the engine clutch. The 

design of the engine allows the 

crankcase assembly opening to be 

susceptible to contamination from 

external sources. We are issuing this AD 

to prevent in-flight engine power loss, 

which could result in loss of control of, 

and damage to, the airplane. 

DATES: This AD becomes effective 

December 30, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (phone: 800– 

647–5527) is provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238 

7199; email: frederick.zink@faa.gov. 


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