54850 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2012–0863; Directorate Identifier 2012– 

NM–108–AD. 

(a) Comments Due Date 

We must receive comments by October 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 737–300, –400, and –500 series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 737–33–1149, 

dated April 13, 2012. 

(2) Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 737–33–1146, dated 

November 2, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 33, Lights. 

(e) Unsafe Condition 

This AD was prompted by a review of the 

tail strobe light installation, which revealed 

the tail strobe light is not electrically bonded 

to primary structure of the airplane. We are 

issuing this AD, in case of a direct lightning 

strike to the tail strobe light, to prevent 

damage to the operation of other critical 

airplane systems due to electromagnetic 

coupling and large transient voltages, and 

damage to the control mechanisms or 

surfaces due to a fire, which could result in 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation 

Within 72 months after the effective date 

of this AD, install a new tail strobe light 

housing, install a new disconnect bracket, 

and change the wire bundles, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–33–1146, dated November 2, 2011 (for 

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

and –900ER series airplanes), except as 

provided by paragraph (i) of this AD; or 

Boeing Special Attention Service Bulletin 

737–33–1149, dated April 13, 2012 (for 

Model 737–300, –400, and –500 series 

airplanes). 

(h) Concurrent Installation 

For airplanes identified in Boeing Special 

Attention Service Bulletin 737–33–1149, 

dated April 13, 2012: Prior to or concurrently 

with the actions required by paragraph (g) of 

this AD, install wingtips and tail strobe 

lights, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraph (h)(1), (h)(2), or (h)(3) of this AD: 

(1) For Group 6 airplanes identified in 

Boeing Special Attention Service Bulletin 

737–33–1149, dated April 13, 2012: Use 

Boeing Service Bulletin 737–33–1076, dated 

September 22, 1988. 

(2) For Group 7 airplanes identified in 

Boeing Special Attention Service Bulletin 

737–33–1149, dated April 13, 2012: Use 

Boeing Service Bulletin 737–33–1078, dated 

November 3, 1988. 

(3) For Group 5 airplanes identified in 

Boeing Special Attention Service Bulletin 

737–33–1149, dated April 13, 2012: Use 

Boeing Service Bulletin 737–33–1111, dated 

August 29, 1996. 

(i) Exception to Service Bulletin 

Specifications 

This paragraph clarifies the airplane 

groups and configurations identified in 

Boeing Special Attention Service Bulletin 

737–33–1146, dated November 2, 2011. 

Group 1, Config 1, comprises line number (L/ 

N) 1–1198 inclusive. Group 1, Config 2, 

comprises L/N 1199–3060 inclusive. 

(j) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(k) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, FAA, ANM– 

130S, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6418; fax: 

(425) 917–6590; email: 

marie.hogestad@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 review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356. For information on 

the availability of this material at the FAA, 

call 425–227–1221. 

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21928 Filed 9–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0864; Directorate 

Identifier 2011–NM–023–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 an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 767 airplanes. The 

existing AD currently requires sealing 

certain fasteners and stiffeners in the 

fuel tank, changing certain wire bundle 

clamp configurations on the fuel tank 

walls, inspecting certain fasteners in the 

fuel tanks and determining the method 

of attachment of the vortex generators, 

and performing corrective action if 

necessary. We issued that AD to prevent 

possible ignition sources in the 

auxiliary (center) fuel tank, main fuel 

tanks, and surge tanks caused by a 

wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss of the airplane. Since 

we issued that AD, another possible 

ignition source location was identified. 

This proposed AD would add a general 

visual inspection for the presence of a 

polytetrafluoroethylene (TFE) sleeve at 

the clamp location on the rear spar, and 

installation of a TFE sleeve if necessary. 

This proposed AD would also add 

airplanes to the applicability. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 22, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54851 

• 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 

review copies of the 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; 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 

425–917–6590; email: 

rebel.nichols@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–2012–0864; Directorate Identifier 

2011–NM–023–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 August 7, 2009, we issued AD 

2009–18–02, Amendment 39–15998 (74 

FR 43621, August 27, 2009), for certain 

Model 767–200, –300, –300F, and 

–400ER series airplanes. That AD 

requires sealing certain fasteners and 

stiffeners in the fuel tank, changing 

certain wire bundle clamp 

configurations on the fuel tank walls, 

inspecting certain fasteners in the fuel 

tanks and determining the method of 

attachment of the vortex generators, and 

corrective action if necessary. That AD 

resulted from fuel system reviews 

conducted by the manufacturer. We 

issued that AD to prevent possible 

ignition sources in the auxiliary (center) 

fuel tank, main fuel tanks, and surge 

tanks caused by a wiring short or 

lightning strike, which could result in 

fuel tank explosions and consequent 

loss of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, 

August 27, 2009), another possible 

ignition source location was identified 

that could also result in fuel tank 

explosions and consequent loss of the 

airplane. 

Relevant Service Information 

AD 2009–18–02, Amendment 39– 

15998 (74 FR 43621, August 27, 2009), 

refers to Boeing Service Bulletin 767– 

57A0102, Revision 01, dated November 

27, 2007, as the appropriate source of 

service information for installing the 

wire bundle sleeve and clamp and 

applying fastener sealant. Boeing has 

since revised this service bulletin. We 

have reviewed Boeing Service Bulletin 

767–57A0102, Revision 4, dated 

September 20, 2011, which includes the 

following changes (introduced in Boeing 

Service Bulletin 767–57A0102, Revision 

3, dated December 2, 2010): the addition 

of work package 13, which includes a 

general visual inspection of the clamp 

location on the rear spar to determine 

whether a polytetrafluoroethylene (TFE) 

sleeve is installed between the clamp 

and the plastic convoluted tubing, and 

the installation of a TFE sleeve between 

the clamp and the plastic convoluted 

tubing, if necessary. Boeing Service 

Bulletin 767–57A0102, Revision 4, 

dated September 20, 2011, also adds 

airplanes to the effectivity. 

AD 2009–18–02, Amendment 39– 

15998 (74 FR 43621, August 27, 2009), 

refers to Boeing Service Bulletin 767– 

57A0100, Revision 01, dated June 19, 

2008, as the appropriate source of 

service information for sealing certain 

bracket fasteners and rear spar 

stiffeners, and inspecting the vortex 

generator attachment. Boeing has since 

revised this service bulletin. We have 

reviewed Boeing Service Bulletin 767– 

57A0100, Revision 3, dated July 28, 

2011, which adds clarifications, but no 

new actions. 

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 2009–18–02, 

Amendment 39–15998 (74 FR 43621, 

August 27, 2009). This proposed AD 

would revise the applicability to 

include additional airplanes. This 

proposed AD would also add a general 

visual inspection for the presence of a 

TFE sleeve at the clamp location on the 

rear spar, and installation of a TFE 

sleeve if necessary. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, 

August 27, 2009). Since AD 2009–18–02 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement/information in AD 2009–18– 

02, Amendment 39– 

15998 (74 FR 43621, 

August 27, 2009) 

Corresponding 

requirement in this 

proposed AD 

paragraph (f) ............. paragraph (g). 

paragraph (g) ............ paragraph (h). 

Note 1 ....................... paragraph (i). 

Other Changes 

We have revised certain headings 

throughout this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 414 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
54852 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Number of 

U.S.-registered 

airplanes 

Cost on U.S. 

operators 

Group 1—Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions 

from AD 2009–18–02, Amendment 39–15998 

(74 FR 43621, August 27, 2009)).

6 work-hours × $85 per 

hour = $510.

$0 $510 367 $187,170 

Group 2—Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained actions 

from AD 2009–18–02, Amendment 39–15998 

(74 FR 43621, August 27, 2009)).

114 work-hours × $85 

per hour = $9,690.

0 9,690 37 358,530 

Group 3—Inspection—Boeing Service Bulletin 

767–57A0100 (retained actions from AD 

2009–18–02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

1 work-hour × $85 per 

hour = $85.

0 85 9 765 

Group 1—Change wire bundle clamp configurations, Boeing Service Bulletin 767–57A0102 

(retained actions from AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009)).

250 work-hours × $85 

per hour = $21,250.

1,632 22,882 376 8,603,632 

Group 2—Change wire bundle clamp configurations, Boeing Service Bulletin 767–57A0102 

(retained actions from AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009)).

874 work-hours × $85 

per hour = $74,290.

1,304 75,594 37 2,796,978 

Group 3—Change wire bundle clamp configuration and seal fasteners, Boeing Service Bulletin 767–57A0102 (retained actions from AD 

2009–18–02, Amendment 39–15998 (74 FR 

43621, August 27, 2009)).

26 work-hours × $85 

per hour = $2,210.

338 2,548 1 2,548 

All airplanes—Inspection (new proposed action) 1 work-hour × $85 per 

hour = $85.

0 85 414 35,190 

We estimate the following costs to do 

any necessary repair 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 this repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Seal ends of fasteners—Boeing Service Bulletin 767–57A0100 (retained 

actions from AD 2009-18–02, Amendment 39–15998 (74 FR 43621, 

August 27, 2009)).

6 work-hours × $85 per hour = $510 $0 Up to $510. 

Installation of TFE sleeve—Boeing Service Bulletin 767–57A0102 ........... 1 work-hour × $85 per hour = $85 ... 0 $85. 

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: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54853 

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) 

2009–18–02, Amendment 39–15998 (74 

FR 43621, August 27, 2009), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–0864; Directorate Identifier 2011– 

NM–023–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by October 22, 2012. 

(b) Affected ADs 

This AD supersedes AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes; certificated in any category; 

as identified in Boeing Service Bulletin 767– 

57A0100, Revision 3, dated July 28, 2011; 

and Boeing Service Bulletin 767–57A0102, 

Revision 4, dated September 20, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57: Wings. 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent possible 

ignition sources in the auxiliary (center) fuel 

tank, main fuel tanks, and surge tanks caused 

by a wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Fastener Sealant Application 

This paragraph restates the requirements of 

paragraph (f) of AD 2009–18–02, Amendment 

39–15998 (74 FR 43621, August 27, 2009), 

with revised service information. For 

airplanes identified in Boeing Service 

Bulletin 767–57A0100, Revision 1, dated 

June 19, 2008: Within 60 months after 

October 1, 2009 (the effective date of AD 

2009–18–02), do the actions in paragraphs 

(g)(1) and (g)(2) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0100, Revision 01, dated June 19, 2008; 

or Boeing Service Bulletin 767–57A0100, 

Revision 3, dated July 28, 2011. As of the 

effective date of this AD, only Boeing Service 

Bulletin 767–57A0100, Revision 3, dated July 

28, 2011, may be used to accomplish the 

requirements of this paragraph. 

(1) For Groups 1 and 2 airplanes: Seal the 

ends of the fasteners on the brackets that 

hold the vortex generators, and seal the ends 

of the fasteners on certain stiffeners on the 

rear spar, as applicable. 

(2) For Group 3 airplanes: Do a detailed 

inspection to determine the method of 

attachment of the vortex generators and, 

before further flight, do all applicable 

specified corrective actions. 

(h) Retained Wire Bundle Sleeve and Clamp 

Installation and Fastener Sealant 

Application for Currently Affected Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009), with revised service information. 

For airplanes identified in Boeing Service 

Bulletin 767–57A0102, Revision 01, dated 

November 27, 2007: Within 60 months after 

October 1, 2009 (the effective date of AD 

2009–18–02), do the actions specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–57A0102, Revision 01, 

dated November 27, 2007; or Boeing Service 

Bulletin 767–57A0102, Revision 4, dated 

September 20, 2011. As of the effective date 

of this AD, only Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011, may be used to accomplish the actions 

required by this paragraph. 

(1) Change the wire bundle clamp 

configurations at specified locations on the 

fuel tank walls. 

(2) Seal the fasteners and certain stiffeners 

at specified locations in the fuel tank. 

(3) Do a detailed inspection of the sealant 

of the fasteners in the auxiliary tank center 

bay and rib 28 of the left and right main fuel 

tanks. Seal any unsealed fasteners before 

further flight. 

(i) Definition 

This paragraph restates the information 

specified in Note 1 of AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009). For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

(j) New Wire Bundle Sleeve and Clamp 

Installation and Fastener Sealant 

Application for Newly Added Airplanes 

For airplanes identified in Boeing Service 

Bulletin 767–57A0102, Revision 4, dated 

September 20, 2011, but not identified in 

paragraph (h) of this AD: Do the actions 

required by paragraph (h) of this AD within 

60 months after the effective date of this AD. 

(k) New Inspection and Sleeve Installation 

For airplanes identified as Groups 1 and 2 

in Boeing Service Bulletin 767–57A0102, 

Revision 4, dated September 20, 2011: 

Within 60 months after the effective date of 

this AD, do a general visual inspection of the 

clamp location on the rear spar to determine 

whether a polytetrafluoroethylene (TFE) 

sleeve is installed between the clamp and the 

plastic convoluted tube, in accordance with 

Work Package 13 of the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011. 

(1) If a TFE sleeve is not installed between 

the clamp and the plastic convoluted tubing, 

before further flight, install a TFE sleeve, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0102, Revision 4, dated September 20, 

2011. 

(2) If a TFE sleeve is installed between the 

clamp and the plastic convoluted tubing, no 

more work is required by this paragraph. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 767–57A0100, dated August 21, 

2006; Revision 1, dated June 19, 2008; or 

Revision 2, dated May 20, 2010. 

(2) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 767–57A0102, Revision 01, dated 

November 27, 2007; Revision 2, dated 

January 7, 2010; or Revision 3, dated 

December 2, 2010. 

(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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 previously in 

accordance with AD 2009–18–02, 

Amendment 39–15998 (74 FR 43621, August 

27, 2009), are approved as AMOCs for the 

corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6509; fax: 425–917–6590; 

email: rebel.nichols@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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
54854 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

may review copies of the 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 August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21931 Filed 9–5–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0862; Directorate 

Identifier 2011–NM–198–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 an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 747–400 and 747–400F 

series airplanes. The existing AD 

currently requires installing drains and 

drain tubes to eliminate water 

accumulation in the dripshield above 

the M826 cardfile in the main 

equipment center. Since we issued that 

AD, we received reports of continued 

water damage to diode fire card 

285U0072–1 in the M826 automatic fire 

overheat logic test system cardfile 

following a false FWD CARGO FIRE 

message, with no change in frequency, 

which resulted in an air turn back. This 

proposed AD would instead require 

installing drain tubes, relocating wire 

bundle routing, installing a new drip 

shield and drip shield deflectors, and 

replacing insulation blankets. For 

certain airplanes, this proposed AD 

would also concurrently require sealing 

the drain slot, installing spuds, and 

installing drain tubes. We are proposing 

this AD to prevent water from exiting 

over the edge of the existing drip shield 

and contaminating electrical 

components in the M826 cardfile, which 

could result in an electrical short and 

potential loss of several functions 

essential for safe flight. 

DATES: We must receive comments on 

this proposed AD by October 22, 2012. 

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. 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P. O. Box 3707, MC 2H–65, Seattle, 

Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://www.

myboeingfleet.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356. 

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 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: 

Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Control 

Systems, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6457; fax: 

425–917–6590; email: francis.smith@

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–2012–0862; Directorate Identifier 

2011–NM–198–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 April 7, 2008, we issued AD 2008– 

08–25, Amendment 39–15479 (73 FR 

21240, April 21, 2008), for certain 

Boeing Model 747–400F and –400 series 

airplanes. That AD requires installing 

drains and drain tubes to eliminate 

water accumulation in the dripshield 

above the M826 cardfile in the main 

equipment center. That AD resulted 

from a report that water from the 

dripshield entered the card file and 

damaged a circuit card, causing the AFT 

CARGO FIRE MSG message to be 

illuminated, and resulting in an air turn 

back. We issued that AD to prevent 

water from entering the card file and 

damaging a circuit card. Failure of one 

or more of the 15 fuel system circuit 

cards in the card file could cause loss 

of fuel management, which could cause 

unavailability of fuel. Failure of one or 

more of the 35 fire detection circuit 

cards could cause a false message of a 

fire, or no message of a fire when there 

is a fire. 

Actions Since Existing AD Was Issued 

Since we issued AD 2008–08–25, 

Amendment 39–15479 (73 FR 21240, 

April 21, 2008), we received reports of 

continued water damage to diode fire 

card 285U0072–1 in the M826 

automatic fire overheat logic test system 

cardfile following a false FWD CARGO 

FIRE message, with no change in 

frequency, which resulted in an air turn 

back. These events occurred on 

airplanes on which the actions required 

by AD 2008–08–25 had already been 

accomplished. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–25A3580, Revision 1, 

dated July 14, 2011 (for Model 747– 

400F series airplanes); and Boeing Alert 

Service Bulletin 747–25A3581, Revision 

1, dated June 30, 2011 (for Model 747– 

400 series airplanes). The service 

information describes procedures for 

installing drain tubes, relocating wire 

bundle routing, installing a new drip 

shield and drip shield deflectors, and 

replacing insulation blankets. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS