Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 545 

window with P/N NP165312–13 and P/N 

NP165312–14 with improved seal) or 

Modification 153534 (installation of sliding 

window with P/N NP165312–11 and P/N 

NP165312–12 with amendment M) has been 

embodied in production are not affected by 

the requirements of paragraphs (g) and (h) of 

this AD, provided that no sliding window or 

sliding window seal has been replaced since 

first flight. 

(2) Airplanes on which Airbus 

Modification 39587 (installation of affected 

seal on PPG Aerospace sliding windows) has 

not been embodied in production are not 

affected by the requirements of paragraphs (g) 

and (h) of this AD, provided that no sliding 

window or sliding window seal has been 

replaced since first flight. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install on any airplane any PPG 

Aerospace sliding window with a part 

number listed in table 1 to paragraph (h) of 

this AD with a seal having P/N 22–17–7640– 

1 or P/N 22–17–7640–2, unless the seal has 

been modified in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–56–1015, dated 

September 14, 2012; or PPG Aerospace 

Service Bulletin 165312–56–001, dated 

February 29, 2012. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0011, dated 

January 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-2013-0467-0002. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–56–1015, 

dated September 14, 2012. 

(ii) Airbus Service Bulletin A320–56–1016, 

including Appendices 01 and 02, dated 

September 14, 2012. 

(iii) PPG Aerospace Service Bulletin 

165312–56–001, dated February 29, 2012. 

(3) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) For PPG Aerospace service information 

identified in this AD, contact PPG Aerospace, 

12780 San Fernando Road, Sylmar, CA 

91342; telephone 818–362–6711; fax 818– 

362–0603; Internet http://

corporateportal.ppg.com/na/aerospace. 

(5) 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. 

(6) 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 

December 20, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31313 Filed 1–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0032; Directorate 

Identifier 2010–NM–236–AD; Amendment 

39–17717; AD 2013–26–08] 

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 737–600, 

–700, –700C, –800, and –900 series 

airplanes. This AD was prompted by 

reports of arcing and smoke at the left 

number 2 window in the flight deck. 

This AD requires inspecting the 

orientation of both sides of the coil cord 

connector keyways of the number 2 

windows on the flight deck; re-clocking 

the connector keyways, if necessary; 

and replacing the coil cord assemblies 

on both number 2 windows on the flight 

deck. We are issuing this AD to prevent 

arcing, smoke, and fire in the flight 

deck, which could lead to injuries to or 

incapacitation of the flightcrew. 

DATES: This AD is effective February 10, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 10, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. 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. 

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–2011– 

0032; 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: 

Louis Natsiopoulos, Aerospace 

Engineer, Systems and Equipment 

Branch, ANM–130S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6478; fax: 425– 

917–6590; email: Elias.Natsiopoulos@

faa.gov. 

SUPPLEMENTARY INFORMATION: 


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Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to the specified 

products. The SNPRM published in the 

Federal Register on July 17, 2012 (77 FR 

41931). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM), which published in the 

Federal Register January 26, 2011 (76 

FR 4567). The NPRM (76 FR 4567, 

January 26, 2011) proposed to require 

inspecting the orientation of both sides 

of the coil cord connector keyways of 

the number 2 windows on the flight 

deck; re-clocking the connector keyways 

to 12 o’clock, if necessary; and replacing 

the coil cord assemblies on both number 

2 windows on the flight deck. The 

SNPRM proposed to require changing 

the keyway position of certain 

receptacle connectors and adding 

airplanes to the applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 41931, 

July 17, 2012) and the FAA’s response 

to each comment. 

Request To Expand Applicability 

Boeing requested that we revise the 

applicability of the SNPRM (77 FR 

41931, July 17, 2012) to include the 

airplanes specified in Boeing Special 

Attention Service Bulletin 737–30– 

1058, Revision 5, dated April 24, 2013. 

Boeing stated that the effectivity of this 

service bulletin includes 75 airplanes 

that were delivered with the identified 

unsafe condition. 

We agree that the 75 airplanes were 

delivered with the identified unsafe 

condition. However, we disagree with 

expanding the applicability of this final 

rule, because that would necessitate 

(under the provisions of the 

Administrative Procedure Act) reissuing 

the notice, reopening the period for 

public comment, considering additional 

comments subsequently received, and 

eventually issuing a final rule. We have 

determined that further delay of this 

final rule is not appropriate in light of 

the identified unsafe condition that 

exists in the airplanes specified in the 

applicability of the SNPRM (77 FR 

41931, July 17, 2012). However, we 

might consider additional rulemaking in 

the future. We have not changed this 

final rule in this regard. 

Request To Allow a Power Removal 

Procedure 

American Airlines (AAL) stated that it 

has no objections to the SNPRM (77 FR 

41931, July 17, 2012), but requested that 

we allow the removal of power by 

opening circuit breakers in Step B.1., of 

Part 1, of the Work Instructions in 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 4, dated 

November 3, 2011. AAL stated that 

removal of power by opening circuit 

breakers is allowed in Step B.1.(b)., of 

Part 2, of the Work Instructions in 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 4, dated 

November 3, 2011. AAL explained that 

removal of power by opening circuit 

breakers would greatly reduce the 

disruption to airplane maintenance 

being accomplished concurrently. 

We agree with AAL’s request. The 

requested procedure is included in 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013. We have changed 

paragraphs (g), (h), and (k) of this final 

rule (paragraph (k) in this final rule was 

identified as paragraph (i) in the 

SNPRM (77 FR 41931, July 17, 2012)) to 

refer to Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 

5, dated April 24, 2013, as the 

appropriate source of service 

information. 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013, specifies an additional 

inspection that is not included in 

Revision 4 of Boeing Special Attention 

Service Bulletin, dated November 3, 

2011. For Group 1, Configuration 3, and 

Group 2, Configuration 2, airplanes, 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013, specifies a general visual 

inspection for rubbing damage on the 

coil cords, and replacement of the coil 

cord with a new coil cord if rubbing 

damage is found. Boeing Special 

Attention Service Bulletin 737–30– 

1058, Revision 5, dated April 24, 2013, 

describes the labor hours required for 

the inspection as less than one hour for 

each coil cord. We have determined that 

this minor change in inspection 

procedures will not impose an 

additional burden on any operator; 

further, because it is a logical outgrowth 

of the notice, an additional opportunity 

for public comment will not be 

necessary. We have added the costs for 

this inspection to the Costs of 

Compliance section of this final rule, 

added new paragraph (i) to this final 

rule to require the coil cord inspection, 

and re-designated subsequent 

paragraphs accordingly. 

Revision 5 of Boeing Special 

Attention Service Bulletin 737–30– 

1058, dated April 24, 2013, also 

describes changes to a wire diagram 

reference and adds improved figure 

work instructions. 

Request To Allow Re-installation of 

Coil Cords 

AAL requested that we allow 

retention and re-installation of coil 

cords if they are the new part number 

and no damage is found on them during 

the inspections proposed in the SNPRM 

(77 FR 41931, July 17, 2012). AAL stated 

that since the new coil cord has been 

available for several years, it is possible 

that some airplanes may already have 

the new coil cord installed. 

We disagree with revising this final 

rule because this final rule and the 

referenced service information, Boeing 

Special Attention Service Bulletin 737– 

30–1058, Revision 5, dated April 24, 

2013, specify further actions beyond 

simply installing a new coil cord. 

Figures 12 and 14 in Boeing Special 

Attention Service Bulletin 737–30– 

1058, Revision 5, dated April 24, 2013, 

provide procedures for installation of 

receptacle connectors on the cover as 

part of the coil cord replacement for 

certain airplanes. Operators must ensure 

that all applicable actions specified in 

the service information have been done 

in addition to the installation of the new 

coil cord. However, under the 

provisions of paragraph (l) of this final 

rule, we will consider requests for 

approval of an alternative method of 

compliance (AMOC) to allow retaining 

and reinstalling the coil cord on 

airplanes after the effective date of this 

final rule, providing sufficient data is 

submitted to address the identified 

unsafe condition. We have not changed 

this final rule in this regard. 

Request To Clarify Certain Work 

Instructions 

AAL requested that we clarify the 

work instructions for reinstallation of 

connector receptacle D10572 for Group 

1, Configuration 1, airplanes as 

identified in Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 

4, dated November 3, 2011. AAL stated 

that Figures 12 and 14 of this service 

bulletin have steps to reinstall the 

connector receptacle, but the work 

instructions and figures for Group 1, 

Configuration 1 airplanes do not include 

steps that remove the connector 

receptacle. 

We agree to clarify. The removal of 

the receptacle connector D10572 was 

addressed in Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 

3, dated July 7, 2010. The instructions 

were inadvertently omitted in Boeing 

Special Attention Service Bulletin 737– 

30–1058, Revision 4, dated November 3, 

2011. Boeing has added the requested 


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Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 547 

clarification to Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 

5, dated April 24, 2013. As referenced 

previously, we have specified Boeing 

Special Attention Service Bulletin 737– 

30–1058, Revision 5, dated April 24, 

2013, as the appropriate source of 

service information in this final rule. 

Additional Change to This Final Rule 

We have added new paragraph (j) to 

this final rule to specify exceptions to 

Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013, and redesignated the 

subsequent paragraphs accordingly. 

Conclusion 

We reviewed the available data, 

including the comments 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 changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

41931, July 17, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 41931, 

July 17, 2012). 

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 712 

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 Number of 

airplanes Cost on U.S. operators 

Keyway inspection and installation of new cord 

assemblies on both 

sides of the flight deck 

(Group 1, Configuration 

1 airplanes).

6 work-hours × $85 per 

hour = $510.

$1,608 $2,118 ............................. 712 $1,508,016. 

Adjustment of receptacles 

on both sides of the 

flight deck (Group 1, 

Configuration 2, and 

Group 2 airplanes).

4 work-hours × $85 per 

hour = $340.

0 340 .................................. 404 137,360. 

Coil cord inspection 

(Group 1, Configuration 

3, and Group 2 airplanes).

1 work-hour × $85 per 

hour = $85 per coil 

cord.

0 85 per coil cord ............... 404 34,240 per coil cord. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement .. 3 work-hours × $85 per hour = $255 per coil cord assembly $1,735 per coil cord assembly $1,990 per coil cord assembly. 

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 

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: 


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548 Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 

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): 

2013–26–08 The Boeing Company: 

Amendment 39–17717 ; Docket No. 

FAA–2011–0032; Directorate Identifier 

2010–NM–236–AD. 

(a) Effective Date 

This AD is effective February 10, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800, –900, 

and –900ER series airplanes, certificated in 

any category, as identified in Boeing Special 

Attention Service Bulletin 737–30–1058, 

Revision 4, dated November 3, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 30, Ice and Rain Protection. 

(e) Unsafe Condition 

This AD was prompted by reports of arcing 

and smoke at the left number 2 window in 

the flight deck. We are issuing this AD to 

prevent arcing, smoke, and fire in the flight 

deck, which could lead to injuries to or 

incapacitation of the flightcrew. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Replacement for Group 1, 

Configuration 1, Airplanes 

For airplanes identified as Group 1, 

Configuration 1, in Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

dated April 24, 2013: Within 48 months after 

the effective date of this AD, do the actions 

in paragraphs (g)(1) and (g)(2) of this AD. 

(1) Do a general visual inspection of the 

orientation of the coil cord connector 

keyways on the captain’s and first officer’s 

sides of the flight compartment, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

dated April 24, 2013, except as specified in 

paragraph (j) of this AD. If the orientation is 

not at the specified position, before further 

flight, turn the receptacle connector to the 

correct position, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–30– 

1058, Revision 5, dated April 24, 2013, 

except as specified in paragraph (j) of this 

AD. 

(2) Replace the coil cords with new coil 

cords on both sides of the flight deck, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

dated April 24, 2013, except as specified in 

paragraph (j) of this AD. 

(h) Receptacle Replacement for Group 1, 

Configuration 2, and Group 2, Configuration 

1 Airplanes 

For airplanes identified as Group 1, 

Configuration 2, and Group 2, Configuration 

1, in Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013: Within 48 months after the 

effective date of this AD, install the 

receptacle connector with changed keyway 

position on both sides of the flight deck, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

dated April 24, 2013, except as specified in 

paragraph (j) of this AD. 

(i) Coil Cord Inspection and Corrective 

Action 

For airplanes identified as Group 1, 

Configuration 3, and Group 2, Configuration 

2, in Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013: Within 48 months after the 

effective date of this AD, do a general visual 

inspection for rubbing damage of the coil 

cord on the captain’s and first officer’s sides 

of the flight compartment, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–30–1058, Revision 5, dated April 24, 

2013, except as specified in paragraph (j) of 

this AD. If any rubbing damage is found: 

Before further flight, replace the coil cord 

with a new coil cord, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–30– 

1058, Revision 5, dated April 24, 2013, 

except as specified in paragraph (j) of this 

AD. 

(j) Exceptions to Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

Dated April 24, 2013 

(1) In the circuit breaker tables of the Work 

Instructions of Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

dated April 24, 2013, the panel number for 

circuit breaker C00393 is incorrectly 

identified as ‘‘P6–12.’’ The correct panel 

number reference for circuit breaker C00393, 

‘‘WINDOW HEAT POWER RIGHT SIDE,’’ is 

P6–11. 

(2) In paragraph 3.B Work Instructions, of 

Boeing Special Attention Service Bulletin 

737–30–1058, Revision 5, dated April 24, 

2013, the description for Part 3 work 

instructions as PART 3: RECEPTACLE 

CONNECTOR POSITION CHANGE is 

incorrect. The correct description for Part 3 

work instructions is PART 3: COIL CORD 

INSPECTION AND REPLACEMENT IF 

DAMAGE IS FOUND. 

(3) In Figures 13 and 14, in paragraph 3.B 

Work Instructions, of Boeing Special 

Attention Service Bulletin 737–30–1058, 

Revision 5, dated April 24, 2013, before the 

step tables, the note misidentified certain 

parts and airplane groups. The note should 

read: 

NOTE: Group 1 and Group 2 airplanes 

have the connector receptacle identified as 

D10572. Group 3 airplanes have the 

connector receptacle identified as D10560. 

Except for Group 1 airplanes, a wire diagram 

change is not necessary and not shown in 

this service bulletin. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

replacement required by paragraph (g)(2) of 

this AD, if the replacement was performed 

before the effective date of this AD using the 

service information specified in paragraph 

(k)(1), (k)(2), (k)(3), (k)(4), or (k)(5) of this AD, 

provided that the actions required by 

paragraph (h) of this AD are done in 

accordance with Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 4, 

dated November 3, 2011; or Boeing Special 

Attention Service Bulletin 737–30–1058, 

Revision 5, dated April 24, 2013; for Group 

1, Configuration 2, and Group 2 airplanes. 

(1) Boeing Service Bulletin 737–30–1058, 

dated July 27, 2006, which is not 

incorporated by reference in this AD. 

(2) Boeing Service Bulletin 737–30–1058, 

Revision 1, dated June 18, 2007, which is not 

incorporated by reference in this AD. 

(3) Boeing Service Bulletin 737–30–1058, 

Revision 2, dated February 13, 2009, which 

is not incorporated by reference in this AD. 

(4) Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 3, dated July 

7, 2010, which is not incorporated by 

reference in this AD. 

(5) Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 4, dated 

November 3, 2011. 

(l) 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 (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. 

(m) Related Information 

(1) For more information about this AD, 

contact Louis Natsiopoulos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 425– 

917–6478; fax: 425–917–6590; email: 

Elias.Natsiopoulos@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. 


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Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 549 

(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 Special Attention Service 

Bulletin 737–30–1058, Revision 4, dated 

November 3, 2011. 

(ii) Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013. 

(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, 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 

December 20, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31307 Filed 1–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0945; Directorate 

Identifier 2010–SW–110–AD; Amendment 

39–17722; AD 2013–26–13] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Model S–70, S–70A, S–70C, S– 

70C (M), and S–70C (M1) helicopters 

with General Electric (GE) T700–GE– 

401C or T700–GE–701C engines 

installed. This AD requires establishing 

new fatigue life limits for certain GE 

engine gas generator turbine (GGT) rotor 

parts. This AD was prompted by a 

reevaluation of the method for 

determining the life limit for certain GE 

engine GGT rotor parts and the 

determination that these life limits 

should be based on low cycle fatigue 

(LCF) events instead of hours time-inservice (TIS). The actions are intended 

to prevent fatigue failure of a GGT rotor 

part, engine failure, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective February 10, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 10, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (800) 562–4409, 

email address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137. 

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, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Davison, Flight Test Engineer, 

New England Regional Office, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7156; fax: (781) 238–7170; email: 

michael.davison@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

On September 7, 2012, at 77 FR 

55166, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 by adding an AD that 

would apply to Sikorsky Model S–70, 

S–70A, S–70C, S–70C (M), and S–70C 

(M1) helicopters with GE T700–GE– 

401C or T700–GE–701C engines 

installed. The NPRM proposed 

establishing new fatigue life limits for 

certain GE engine GGT rotor parts, 

based upon a formula in GE’s service 

information. The NPRM was prompted 

by the determination that the affected 

engines could fail due to fatigue unless 

the life limits of certain GE engine rotor 

parts are changed from hours TIS to LCF 

events. 

On July 23, 2013, at 78 FR 44052, the 

Federal Register published our 

supplemental notice of proposed 

rulemaking (SNPRM), which proposed 

to revise the formula in the NPRM for 

establishing the new fatigue life limits 

by using the correct formula in a newer 

revision of GE’s service information. 

Also, the SNPRM corrected a 

typographical error made in the 

preamble of the previous NPRM in the 

‘‘Related Service Information,’’ which 

referenced the service bulletin number 

as 72–041 rather than the correct service 

bulletin number 72–0041. 

The proposed actions in the SNPRM 

were intended to prevent failure of a 

GGT rotor part, engine failure, and 

subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (77 FR 55166, 

September 7, 2012), and the SNPRM (78 

FR 44052, July 23, 2013), but we did not 

receive any comments. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed in the SNPRM (78 FR 44052, 

July 23, 2013). 

Costs of Compliance 

We estimate that this AD will affect 9 

helicopters of U.S. registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD: 

A minimal amount for work hours and 

labor costs because these parts are 

replaced as part of the periodic 

maintenance on the helicopter; a 

minimal amount of time to calculate the 

new retirement life; $360,000 to replace 

the GGT rotor parts per helicopter; and 

$3,240,000 to replace the GGT rotor 

parts for the entire U.S. operator fleet. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


sroberts on DSK5SPTVN1PROD with RULES