Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3527 

thermography inspection of the complete 

side shell panels to identify and mark the 

repair locations for disbonding or damage, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

55–6050; or A310–55–2051; both Revision 

01, dated August 20, 2014; as applicable. 

(h) Related Investigative Actions/Repair or 

Replace 

If any disbonding or damage is found 

during any inspection required by paragraph 

(g)(1) or (g)(2) of this AD: Do the actions 

required by paragraphs (h)(1) and (h)(2) of 

this AD, as applicable. 

(1) At the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service Bulletin 

A300–55–6050; or A310–55–2051; both 

Revision 01, dated August 20, 2014; as 

applicable, except as required by paragraph 

(j)(2) of this AD; do the applicable related 

investigative actions identified in Tables 3, 

4A, 4B, 4C, 4D, and 5 of paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service Bulletin 

A300–55–6050; or A310–55–2051; both 

Revision 01, dated August 20, 2014; as 

applicable, to determine the type and extent 

of the disbonding or damage, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–55–6050; or 

A310–55–2051; both Revision 01, dated 

August 20, 2014; as applicable. Repeat the 

applicable inspection at the time specified in 

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

Service Bulletin A300–55–6050; or A310–55– 

2051; both Revision 01, dated August 20, 

2014; as applicable. 

(2) Before further flight: Repair any 

disbonding or damage found during any 

inspection required by paragraph (h)(1) of 

this AD, or replace any affected rudder, as 

applicable, in accordance with the 

Accomplishment Instructions Airbus Service 

Bulletin A300–55–6050; or A310–55–2051; 

both Revision 01, dated August 20, 2014; as 

applicable, except as required by paragraph 

(j)(4) of this AD. 

(i) Repair Using SRM Procedure Not 

Allowed 

As of the effective date of this AD, do not 

accomplish a composite side shell panel 

repair on any rudder using an SRM 

procedure identified in Figure A–GBBAA 

(Sheet 01 and 02) or Figure A–GBCAA (Sheet 

02) of Airbus Service Bulletin A310–55– 

2051; or Figure A–GBBAA (Sheet 01, 02, or 

03) or Figure A–GBCAA (Sheet 02 or 04) of 

Airbus Service Bulletin A300–55–6050; as 

applicable. 

(j) Exceptions to Service Information 

(1) Where Airbus Service Bulletins A300– 

55–6050; and A310–55–2051; both dated 

September 11, 2012; specify a compliance 

time ‘‘from original service bulletin issue 

date,’’ this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(2) Where Airbus Service Bulletins A300– 

55–6050; and A310–55–2051 both dated 

September 11, 2012; specify to contact 

Airbus for appropriate action: Before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). 

(3) Airplanes on which a rudder is 

installed having a serial number that is not 

in the range HF–1005 through HF–1323, 

inclusive; HF–1325, HF–1327, HF–1329, HF– 

1331, HF–1332, HF–1340, TS–1324, TS– 

1326, TS–1328, TS–1330, TS–1333 through 

TS–1339, inclusive; TS–1341 through TS– 

1420, inclusive; or TS–2001 through TS– 

2197, inclusive; are not affected by the 

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

AD, provided that no repairs have been done 

on the composite side shell panel of that 

rudder since installation in accordance with 

the applicable structural repair manual 

(SRM). 

(4) The compliance time for the initial 

detailed inspection of the restored area for 

loose or lost tape identified in Tables 3 and 

4 of paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Service Bulletins A300–55–6050 and A310– 

55–2051, both Revision 01, dated August 20, 

2014; specifies ‘‘within 500 FH or 4 months 

after closing holes.’’ This AD requires this 

action within 500 flight hours or 4 months, 

whichever occurs later after the holes are 

closed. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A300–55–6050; or A310–55–2051; 

both dated September 11, 2012; as 

applicable; which are not incorporated by 

reference in this AD. 

(l) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install any affected rudder on 

any airplane, unless the actions required by 

paragraphs (g) and (h) of this AD have been 

accomplished. 

(m) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–2125; 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2014–0026, dated 

January 28, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–1045. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

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. 

Issued in Renton, Washington, on January 

13, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00946 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0075; Directorate 

Identifier 2014–NM–202–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–26– 

08, which applies to certain The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. AD 2013–26–08 currently 

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. Since we issued AD 2013–26–08, 

we have determined that additional 

airplanes are subject to the identified 

unsafe condition. This proposed AD 

would add airplanes to the 

applicability. We are proposing this AD 


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to prevent arcing, smoke, and fire in the 

flight deck, which could lead to injuries 

to or incapacitation of the flightcrew. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 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–2015– 

0075; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Frank Carreras, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6442; fax: 425–917–6590; email: 

frank.carreras@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0075; Directorate Identifier 

2014–NM–202–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 20, 2013, we issued AD 

2013–26–08, Amendment 39–17717 (79 

FR 545, January 6, 2014), for certain The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. AD 2013–26–08 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. AD 2013– 

26–08 resulted from reports of arcing 

and smoke at the left number 2 window 

in the flight deck. We issued AD 2013– 

26–08 to prevent arcing, smoke, and fire 

in the flight deck, which could lead to 

injuries to or incapacitation of the 

flightcrew. 

Actions Since AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, 

January 6, 2014) Was Issued 

In AD 2013–26–08, Amendment 39– 

17717 (79 FR 545, January 6, 2014), a 

commenter to the SNPRM (77 FR 41931, 

July 17, 2012) requested that we add 

additional airplanes to the applicability. 

We determined that further delay of AD 

2013–26–08 was not appropriate in light 

of the identified unsafe condition that 

existed on the airplanes specified in the 

applicability of AD 2013–26–08. We 

stated that we might consider additional 

rulemaking in the future. We now have 

determined that further rulemaking is 

indeed necessary, and this proposed AD 

follows from that determination. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, 

January 6, 2014). This proposed AD 

would add Group 3 airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 

5, dated April 24, 2013, to the 

applicability. 

Costs of Compliance 

We estimate that this proposed AD 

affects 718 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Number of 

airplanes 

Cost on U.S. 

operators 

Keyway inspection and installation 

(Group1, Configuration 1 airplanes) [actions retained from 

AD 2013-26-08, Amendment 

39-17717 (79 FR 545, January 

6, 2014)].

6 work-hours × $85 per hour = 

$510.

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

Adjustment of receptacles (Group 

1, Configuration 2, Group 2, and 

Group 3 airplanes) [actions retained from AD 2013-26-08, 

Amendment 39-17717 (79 FR 

545, January 6, 2014)].

4 work-hours × $85 per hour = 

$340.

$0 $340 .................. 410 $139,400. 


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ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per product Number of 

airplanes 

Cost on U.S. 

operators 

Coil cord inspection (Group 1, 

Configuration 3, and Group 2 

airplanes) [actions retained from 

AD 2013-26-08, Amendment 

39-17717 (79 FR 545, January 

6, 2014)].

1 work-hour × $85 per hour = $85 

per coil cord.

$0 $85 per coil cord 404 $34,340 per coil 

cord. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed 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 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2013–26–08, Amendment 39–17717 (79 

FR 545, January 6, 2014), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2015–0075; Directorate Identifier 2014– 

NM–202–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by March 9, 2015. 

(b) Affected ADs 

This AD replaces AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014). 

(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 5, dated April 24, 2013. 

(d) Subject 

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) Retained Inspection and Replacement for 

Group 1, Configuration 1, Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. 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 February 10, 

2014 (the effective date of AD 2013–26–08), 

do the actions specified 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 


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paragraph (k) 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 (k) 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 (k) of this AD. 

(h) Retained Receptacle Replacement for 

Group 1, Configuration 2, and Group 2, 

Configuration 1 Airplanes 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. 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 February 10, 2014 (the effective 

date of AD 2013–26–08), 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 (k) of this AD. 

(i) Retained Coil Cord Inspection and 

Corrective Action 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–26–08, Amendment 

39–17717 (79 FR 545, January 6, 2014), with 

no changes. 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 

February 10, 2014 (the effective date of AD 

2013–26–08), 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 (k) 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 (k) of this 

AD. 

(j) New Requirements of This AD: Receptacle 

Replacement for Group 3 Airplanes 

For airplanes identified as Group 3 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 (k) of 

this AD. 

(k) Exceptions to Boeing Special Attention 

Service Bulletin 737–30–1058, Revision 5, 

Dated April 24, 2013 

(1) This paragraph restates the provisions 

of paragraph (j)(1) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. 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) This paragraph restates the provisions 

of paragraph (j)(2) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. In paragraph 3.B. of 

the Work Instructions of Boeing Special 

Attention Service Bulletin 737–30–1058, 

Revision 5, dated April 24, 2013, the 

description for Part 3 of the Work 

Instructions is identified as ‘‘PART 3: 

RECEPTACLE CONNECTOR POSITION 

CHANGE,’’ which is incorrect. The correct 

description for Part 3 of the Work 

Instructions is ‘‘PART 3: COIL CORD 

INSPECTION AND REPLACEMENT IF 

DAMAGE IS FOUND.’’ 

(3) This paragraph restates the provisions 

of paragraph (j)(3) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. In Figures 13 and 14, 

in paragraph 3.B. of the Work Instructions of 

Boeing Special Attention Service Bulletin 

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

2013, the note before the step tables 

misidentifies 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. 

(l) Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (k) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), with no changes. This paragraph 

provides credit for the replacement required 

by paragraph (g)(2) of this AD, if the 

replacement was performed before February 

10, 2014 (the effective date of AD 2013–26– 

08), using the service information specified 

in paragraph (l)(1), (l)(2), (l)(3), (l)(4), or (l)(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 

airplanes in Group 1, Configuration 2, and 

Group 2. 

(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. 

(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) AMOCs approved for AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), are approved as AMOCs for the 

corresponding provisions of this AD. 

(4) For airplanes identified as Group 3 in 

Boeing Special Attention Service Bulletin 

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

2013, AMOCs approved for the actions 

required by paragraph (h) of AD 2013–26–08, 

Amendment 39–17717 (79 FR 545, January 6, 

2014), are approved as AMOCs for the 

corresponding provisions of paragraph (j) of 

this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Frank Carreras, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office 

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

98057–3356; phone: 425–917–6442; fax: 425– 

917–6590; email: frank.carreras@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on January 

14, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00962 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 


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