54848 Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane a 

hydraulic system accumulator having P/N 

900095–1, on which the letter ‘‘E’’ is not part 

of the suffix of the serial number on the 

identification plate. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

(516) 228–7300; fax (516) 794–5531. 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 FAAapproved 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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–41, dated October 31, 

2011; and Bombardier Service Bulletin 100– 

29–14, dated December 16, 2010; for related 

information. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@aero.bombardier. 

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

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21946 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–2012–0863; Directorate 

Identifier 2012–NM–108–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 adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–300, 

–400, –500, –600, –700, –700C, –800, 

–900, and –900ER series airplanes. This 

proposed AD was prompted by a review 

of the tail strobe light installation, 

which revealed that the tail strobe light 

is not electrically bonded to primary 

structure of the airplane. This proposed 

AD would require installing a new tail 

strobe light housing and a new 

disconnect bracket, and changing the 

wire bundles. We are proposing 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. 

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. 

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, 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0863; Directorate Identifier 2012– 

NM–108–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 

As a result of a review of the tail 

strobe light installation, located at the 

aft end of section 48, it was determined 

that the tail strobe light is not 

electrically bonded to primary structure 

of the airplane. In case of a direct 

lightning strike to the tail strobe light, 

electromagnetic coupling and large 

transient voltages can be transmitted 

into the pressure vessel and couple to 

wires of the airplane systems that are 

routed with the tail strobe light wires. 

The large transient voltages could cause 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 173 / Thursday, September 6, 2012 / Proposed Rules 54849 

damage to the operation of the 

airplane’s electrical systems, as well as 

flight control and avionics equipment. 

In addition to electromagnetic coupling, 

since the tail strobe light is located in 

a flammable leakage zone, electrical 

current on the tail strobe light system 

wiring could create an ignition source 

and potential fire, which could cause 

damage to the control mechanisms or 

surfaces. This condition, if not 

corrected, could result in loss of control 

of the airplane. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 737–33– 

1146, dated November 2, 2011 (for 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes); and 

Boeing Special Attention Service 

Bulletin 737–33–1149, dated April 13, 

2012 (for Model (for Model 737–300, 

–400, and –500 series airplanes). The 

service information describes 

procedures for installing a new tail 

strobe light housing, installing a new 

disconnect bracket, and changing the 

wire bundles. 

Concurrent Service Information 

Boeing Special Attention Service 

Bulletin 737–33–1149, dated April 13, 

2012, also specifies the concurrent 

accomplishment of the following service 

bulletins: 

• Boeing Service Bulletin 737–33– 

1076, dated September 22, 1988. 

• Boeing Service Bulletin 737–33– 

1078, dated November 3, 1988. 

• Boeing Service Bulletin 737–33– 

1111, dated August 29, 1996. 

These service bulletins describe 

procedures for installing wingtips and 

tail strobe lights. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,512 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 Cost on U.S. operators 

Installation for Model 737–300, –400, 

and –500 series airplanes (478 U.S. 

registered airplanes).

Up to 33 work-hours × 

$85 per hour = Up to 

$2,805.

Up to $14,886 .............. Up to $17,691 .............. Up to $8,456,298. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 1 (922 U.S. registered airplanes).

Up to 18 work-hours × 

$85 per hour = Up to 

$1,530.

Up to $4,422 ................ Up to $5,952 ................ Up to $5,487,744. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 2 (85 U.S. registered airplanes).

Up to 18 work-hours × 

$85 per hour = Up to 

$1,530.

Up to $2,818 ................ Up to $4,348 ................ Up to $369,580. 

Installation for Model 737–600, –700, 

–700C, –800, –900, and –900ER series airplanes, Group 3 (27 U.S. registered airplanes).

Up to 21 work-hours × 

$85 per hour = Up to 

$1,785.

Up to $4,478 ................ Up to $6,263 ................ Up to $169,101. 

According to the manufacturer, all of 

the costs of this proposed 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 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 this 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: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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