Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15671 

(ii) Boeing Service Bulletin 747–78–2178, 

Revision 1, dated August 4, 2011. 

(iii) Boeing Service Bulletin 747–78–2180, 

Revision 2, dated November 11, 2011. 

(iv) Boeing Service Bulletin 767–78–0096, 

Revision 1, dated December 10, 2009. 

(4) The following service information was 

approved for IBR on February 18, 2000 (65 

FR 5222, February 3, 2000). 

(i) Boeing Service Bulletin 747–78–2158, 

Revision 2, dated July 29, 1999. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on September 14, 1994 (59 

FR 41647, August 15, 1994). 

(i) Boeing Service Bulletin 767–78–0059, 

Revision 3, dated January 20, 1994. 

(ii) Reserved. 

(6) 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. 

(7) You may view this service information 

at FAA, Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(8) 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 February 

19, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06155 Filed 3–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1023; Directorate 

Identifier 2013–NM–042–AD; Amendment 

39–17797; AD 2014–05–24] 

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) 84–19–01 

for certain The Boeing Company Model 

747–100, 747–200B, and 747–200F 

series airplanes. AD 84–19–01 required 

repetitive inspections for cracking of 

certain tension ties, and repair and 

certain modifications if necessary. This 

new AD requires, for certain airplanes, 

additional inspections for cracking of 

the tension tie at body station (BS) 760 

or 780, corrective action if necessary, 

and eventual modification of the tension 

ties. For all airplanes, this new AD 

requires repetitive post-modification 

inspections for cracking of the tension 

tie at BS 760 or 780, and corrective 

action if necessary. This AD was 

prompted by reports of cracking in the 

BS 760 tension tie as a result of bending 

due to cabin pressurization. We are 

issuing this AD to detect and correct 

tension tie cracking, which could 

eventually result in in-flight 

depressurization of the airplane and the 

inability to withstand current regulatory 

failsafe loads. 

DATES: This AD is effective April 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 25, 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–2013– 

1023; 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 84–19–01, 

Amendment 39–4913 (Docket No. 84– 

NM–10–AD; 49 FR 36365, September 

17, 1984). AD 84–19–01 applied to 

certain Boeing Model 747–100, 747– 

200B, and 747–200F series airplanes. 

The NPRM published in the Federal 

Register on December 6, 2013 (78 FR 

73457). The NPRM was prompted by 

reports of cracking in the BS 760 tension 

tie as a result of bending due to cabin 

pressurization. The NPRM proposed to 

continue to require repetitive 

inspections for cracking of certain 

tension ties, and repair and certain 

modifications if necessary. The NPRM 

also proposed to require, for certain 

airplanes, additional inspections for 

cracking of the tension tie at BS 760 or 

780, corrective action if necessary, and 

eventual modification of the tension 

ties. For all airplanes, the NPRM also 

proposed to require repetitive postmodification inspections for cracking of 

the tension tie at BS 760 or 780, and 

corrective action if necessary. We are 

issuing this AD to detect and correct 

tension tie cracking, which could 

eventually result in in-flight 

depressurization of the airplane and the 

inability to withstand current regulatory 

failsafe loads. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supported the NPRM (78 FR 

73457, December 6, 2013). 

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 (78 FR 

73457, December 6, 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 73457, 

December 6, 2013). 

Costs of Compliance 

We estimate that this AD affects 24 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

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15672 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Number of U.S. 

airplanes 

Cost on U.S. 

operators 

Inspection .................... 3 work-hours × $85 per 

hour = $255 per inspection cycle.

$0 $255 per inspection 

cycle.

Up to 24 ..................... $6,120 per inspection 

cycle. 

Modification ................. 32 work-hours × $85 per 

hour = $2,720.

672 $3,392 ........................ Up to 24 ..................... $81,408. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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) 

84–19–01, Amendment 39–4913 (Docket 

No. 84–NM–10–AD; 49 FR 36365, 

September 17, 1984), and adding the 

following new AD: 

2014–05–24 The Boeing Company: 

Amendment 39–17797; Docket No. 

FAA–2013–1023; Directorate Identifier 

2013–NM–042–AD. 

(a) Effective Date 

This AD is effective April 25, 2014. 

(b) Affected ADs 

This AD supersedes AD 84–19–01, 

Amendment 39–4913 (Docket No. 84–NM– 

10–AD; 49 FR 36365, September 17, 1984). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–200B, and 747–200F 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the body station (BS) 760 tension 

tie as a result of bending due to cabin 

pressurization. We are issuing this AD to 

detect and correct tension tie cracking, which 

could eventually result in in-flight 

depressurization of the airplane and the 

inability to withstand current regulatory 

failsafe loads. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections: Unmodified 

Airplanes 

For airplanes that have not been modified 

as specified in Boeing Service Bulletin 747– 

53–2088: At the applicable time specified in 

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

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, except as 

required by paragraph (j)(1) of this AD, do 

detailed (close visual) and surface high 

frequency eddy current inspections for 

cracking of the tension tie at BS 760 or 780, 

as applicable, and do all applicable 

corrective actions, in accordance with Part I 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, except as 

required by paragraph (j)(2) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the inspections thereafter at the 

applicable time specified in Table 1 or Table 

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

Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, until 

accomplishment of the requirements of 

paragraph (h) of this AD. 

(h) Modification 

For airplanes that have not been modified 

as specified in Boeing Service Bulletin 747– 

53–2088: At the applicable time specified in 

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

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, except as 

required by paragraph (j)(1) of this AD, 

modify the tension ties, including doing an 

open-hole high frequency eddy current 

inspection for cracks, as applicable, and all 

applicable corrective actions, in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, except as required by paragraph (j)(2) 

of this AD. All applicable corrective actions 

must be done before further flight. This 

modification terminates the repetitive 

inspection requirements of paragraph (g) of 

this AD. 

(i) Post-modification Repetitive Inspections 

For airplanes that have been modified as 

specified in Boeing Service Bulletin 747–53– 

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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15673 

2088: At the applicable time specified in 

Table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, do a 

detailed inspection for cracking of the 

tension tie at BS 760 or 780, and do all 

applicable corrective actions, in accordance 

with Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, except as required by paragraph (j)(2) 

of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection thereafter at the applicable time 

specified in Table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013. Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013, notes that additional postmodification inspections are specified in 

Boeing Service Bulletin 747–53A2502; those 

post-modification inspections are required by 

AD 2006–01–07, Amendment 39–14446 (71 

FR 1947, January 12, 2006). 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies a compliance time ‘‘after the 

Revision 4 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Alert Service Bulletin 

747–53A2088, Revision 3, dated September 

8, 1994, which is not incorporated by 

reference in this AD. 

(l) 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. 

(m) 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 (n)(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) AMOCs approved for AD 84–19–01, 

Amendment 39–4913 (Docket No. 84–NM– 

10–AD; 49 FR 36365, September 17, 1984), 

are approved as AMOCs for the 

corresponding requirements of paragraph (g) 

(the retained detailed inspections) and 

paragraph (i) of this AD, but not as AMOCs 

for the high frequency eddy current 

inspections required by paragraph (g) of this 

AD. 

(n) 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 in 

this AD may be obtained at the addresses 

specified in paragraphs (o)(3) and (o)(4) of 

this AD. 

(o) 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– 

53A2088, Revision 4, dated January 11, 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 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 February 

26, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06153 Filed 3–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0051; Directorate 

Identifier 2007–NE–37–AD; Amendment 39– 

17801; AD 2014–05–29] 

RIN 2120–AA64 

Airworthiness Directives; Continental 

Motors, Inc. Reciprocating Engines 

With Superior Air Parts, Inc. (SAP) 

Cylinder Assemblies Installed 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2009–16– 

03 for certain Continental Motors, Inc. 

(CMI) IO–520, TSIO–520, and IO–550 

series reciprocating engines, with 

certain SAP replacement parts 

manufacturer approval (PMA) 

investment cast cylinder assemblies 

installed. AD 2009–16–03 required 

initial and repetitive inspections and 

compression tests to detect cracks in 

those cylinders. This new AD requires 

that additional engines be added to the 

applicability. This AD was prompted by 

the need to add to the applicability all 

other engine models approved for the 

use of CMI 520 and 550 cylinder 

assemblies, such as the CMI 470 series 

engines when modified by 

supplemental type certificate (STC), 

with affected SAP investment cast 

cylinder assemblies installed. We are 

issuing this AD to prevent the 

separation of the cylinder head, damage 

to the engine, and damage to the 

airplane. 

DATES: This AD is effective April 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 25, 2014. 

ADDRESSES: For service information 

identified in this AD, contact 

Continental Motors, Inc., 2039 Broad 

St., Mobile, AL 36615; phone: 251–438– 

3411; Web site: http://

www.continentalmotors.aero/Support_

Materials/Publications/Service_

Bulletins/. You may view this service 

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