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was increased. We are issuing this AD to 

prevent reduced control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Airplane Flight Manual Revision 

For airplanes identified in paragraphs 

(g)(1) and (g)(2) of this AD, except as 

provided by paragraph (j) of this AD: Within 

10 days after the effective date of this AD, 

revise the Emergency Procedures of the 

Airbus A330 and A340 Airplane Flight 

Manuals (AFMs), as applicable, by 

incorporating Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; as 

applicable; to advise the flight crew of 

emergency procedures for addressing AOA 

sensor blockage. This can be done by 

inserting the Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; 

into the applicable AFM. When the 

information in Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; and Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; is 

included in the general revisions of the 

applicable AFM, the general revisions may be 

incorporated into the AFM, and the 

temporary revisions may be removed. 

(1) Model A330–201, –202, –203, –223, 

223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

all manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A330–34–3255 has 

been embodied in service. 

(2) Model A340–211, –212, –213, –311, 

–312, –313, –541, and –642 airplanes, all 

manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A340–34–4250 or 

A340–34–5081, as applicable, has been 

embodied in service. 

(h) Replacement 

Except as provided by paragraph (j) of this 

AD: Within 5 months after the effective date 

of this AD, replace all AOA sensor conic 

plates having part number (P/N) 

F3411060200000 or P/N F3411060900000 

with an applicable AOA sensor flat plate 

identified in paragraph (h)(1) or (h)(2) of this 

AD. Performing this replacement constitutes 

terminating action for the AFM revision 

required by paragraph (g) of this AD; and 

Airbus A330 Temporary Revision TR293, 

Issue 1.0, dated December 4, 2012, and 

Airbus A340 Temporary Revision TR294, 

Issue 1.0, dated December 4, 2012, to the 

Airbus A330 and A340 AFMs, as applicable, 

must be removed from the AFMs before 

further flight after doing the replacement. 

(1) Replace with a flat plate having P/N 

F3411007920200 or P/N F3411007920300, as 

applicable, in accordance with the applicable 

service information specified in paragraph 

(h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–34–3293, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(ii) Airbus Mandatory Service Bulletin 

A340–34–4273, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(iii) Airbus Mandatory Service Bulletin 

A340–34–5093, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(2) Replace with a flat plate having P/N 

F3411007920000 or P/N F3411007920100, in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) or its delegated agent. 

(i) Modification of Installation 

For airplanes on which any AOA sensor 

conic plate has been replaced with an AOA 

sensor flat plate, in accordance with the 

applicable service information specified in 

paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of 

this AD: Within 5 months after the effective 

date of this AD, modify the installation of the 

AOA sensor flat plates so that the plates are 

flush with the fuselage in accordance with 

the applicable service information identified 

in paragraph (h)(1)(i), (h)(1)(ii),or (h)(1)(iii) of 

this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–34–3293, including Appendix 01, 

dated January 31, 2013. 

(ii) Airbus Mandatory Service Bulletin 

A340–34–4273, including Appendix 01, 

dated January 30, 2013. 

(iii) Airbus Mandatory Service Bulletin 

A340–34–5093, including Appendix 01, 

dated January 30, 2013. 

(j) Exception to Paragraphs (g) and (h) of 

This AD 

For airplanes on which Airbus 

Modification 203285 (improved AOA flat 

plate protection treatment) has been 

embodied in production: The actions 

specified in paragraphs (g) and (h) of this AD 

are not required, provided that, since first 

flight, no AOA probe conic plate having P/ 

N F3411060200000 or P/N F3411060900000 

has been installed. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, an AOA 

sensor conic plate having P/N 

F3411060200000 or P/N F3411060900000 or 

an AOA protection cover having P/N 

98D34203003000. 

(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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2013–0023, dated 

February 1, 2013, for related information, 

which can be found in the AD docket on the 

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

(2) For service information identified in 

this proposed AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http://

www.airbus.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 

September 23, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24058 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0835; Directorate 

Identifier 2013–NM–095–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc., 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 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD 

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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 60801 

results from fuel system reviews 

conducted by the manufacturer. This 

proposed AD would require 

accomplishing modifications to the fuel 

system. We are proposing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 18, 

2013. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@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. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Morton Lee, Propulsion Engineer, 

Propulsion & Services Branch, ANE– 

173; FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7355; fax 

516–794–5531. 

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–2013–0835; Directorate Identifier 

2013–NM–095–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 based on 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 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, combination of failures, 

and unacceptable (failure) experience. 

For all three failure criteria, the 

evaluations included consideration of 

previous actions taken that may mitigate 

the need for further action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–07, 

dated March 1, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Bombardier Aerospace has completed a 

system safety review of the aeroplane fuel 

system against fuel tank safety standards 

* * *. The identified non-compliances were 

then assessed * * * to determine if 

mandatory corrective action is required. 

The assessment showed that a number of 

modifications to the fuel system are required 

to mitigate unsafe conditions that could 

result in potential ignition sources within the 

fuel system. 

* * * * * 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier Inc. has issued the 

following service bulletins. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Bombardier Service Bulletin 8–28–35, 

Revision C, dated January 14, 2013. 

• Bombardier Service Bulletin 8–28–36, 

Revision C, dated October 7, 2009. 

• Bombardier Service Bulletin 8–28–39, 

Revision B, dated August 19, 2009. 

• Bombardier Service Bulletin 8–28–41, 

Revision B, dated August 8, 2012. 

• Bombardier Service Bulletin 8–28–42, 

Revision A, dated October 1, 2008. 

• Bombardier Service Bulletin 8–28–43, 

Revision A, dated June 25, 2009. 

• Bombardier Service Bulletin 8–28–44, 

Revision B, dated July 25, 2009. 

• Bombardier Service Bulletin 8–28–47, 

dated May 2, 2008. 

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60802 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 

• Bombardier Service Bulletin 8–28–48, 

Revision A, dated February 27, 2012. 

• Bombardier Service Bulletin 8–28–49, 

Revision A, dated July 23, 2012. 

• Bombardier Service Bulletin 8–28–52, 

dated November 3, 2009. 

• Bombardier Service Bulletin 8–28–53, 

dated November 3, 2008. 

• Bombardier Service Bulletin 8–28–55, 

dated July 23, 2012. 

• Bombardier Service Bulletin 8–28–56, 

dated July 23, 2012. 

• Bombardier Service Bulletin 8–28–58, 

dated July 25, 2011. 

• Bombardier Service Bulletin 8–57–44, 

Revision D, dated October 8, 2008. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 94 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 

Modifications .............................. 519 work-hours × $85 per hour = $44,115 ................................. $58,924 $103,039 $9,685,666 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2013– 

0835; Directorate Identifier 2013–NM– 

095–AD. 

(a) Comments Due Date 

We must receive comments by November 

18, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes; certificated in any 

category; serial numbers (S/Ns) 002 through 

672. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination with 

flammable fuel vapors, could result in fuel 

tank explosions and consequent loss of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Modifications—Part I 

Within 6,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD, do the modifications specified in 

paragraphs (g)(1) through (g)(14) of this AD, 

as applicable. 

(1) For airplanes having S/Ns 003 through 

624 inclusive: Accomplish Modsum 

8Q101512, ‘‘Fuel System—Fuel Tank 

Mechanical Design, SFAR 88 Compliance 

(Retrofit),’’ Revision G, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–44, 

Revision D, dated October 8, 2008. 

(2) For airplanes having S/Ns 003 through 

629 inclusive on which a long range fuel 

system has been installed as specified in 

Change Request (CR) 828CH00044, 

CR828SO08061, Special Order Option (SOO) 

8061, CR828CH00027, or CF828SO00006: 

Accomplish Bombardier Modsum 8Q902091, 

‘‘Fuel System—Fuel Tank Mech. Design, 

SFAR 88 Compl.—Extended Range Tank 

Option (Retrofit),’’ Revision C, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–28–39, 

Revision B, dated August 19, 2009. 

(3) For airplanes having S/Ns 003 through 

624 inclusive on which SOO 8155, 

849SO08155, SOO 8098, SOO 8099, or SOO 

6082; or Supplemental Type Certificate 

SA85–1; or Limited Supplemental Type 

Certificate W–LSA98–005/D has been 

incorporated: Accomplish Bombardier 

Modsum 8Q902144, ‘‘Fuel System—Fuel 

Tank Mechanical Design, SFAR 88 

Compliance—APU Option (Retrofit),’’ 

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Revision E, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–44, Revision B, dated 

July 25, 2009. 

(4) For airplanes having S/Ns 003 through 

624 inclusive: Accomplish Bombardier 

Modsum 8Q101865, ‘‘Fuel System—Fuel 

Tank Mechanical Design, SFAR 88 

Compliance (Retrofit),’’ Revision B, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–47, dated May 2, 2008. 

(5) For Models DHC–8–102, –103, and 

–106 having S/Ns 002 through 014 inclusive: 

Accomplish Bombardier Modsum 8Q101916, 

‘‘Fuel System—Fuel Tank Secondary 

Pressure Relief Valve Rework SFAR 88 

Compliance (Retrofit),’’ Revision A, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–58, dated July 25, 2011. 

(6) For airplanes having S/Ns 002 through 

629 inclusive on which a long range fuel 

system has been installed as specified in 

CR828CH00044, CR828SO08061, SOO 8061, 

CR828CH00027, or CR828SO00006, 

including airplanes on which metric refuel/ 

defuel indicators were installed as specified 

in CR828CH00029: Accomplish Bombardier 

Modsum 8Q902122, ‘‘Production/Retrofit— 

Fuel System—Long Range Wiring 

Installation—SFAR 88 Compliance,’’ 

Revision F, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–41, Revision B, dated 

August 8, 2012. 

(7) For airplanes having S/Ns 002 through 

619 inclusive with imperial refuel/defuel 

indicators, excluding airplanes on which a 

long range fuel system has been installed as 

specified in CF828CH00044, CR828SO08061, 

SOO 0861, CF828CH00027, or 

CR828SO00006: Accomplish Bombardier 

Modsum 8Q101511, ‘‘Production/Retrofit— 

Fuel System—Fuel Tank Wiring 

Installation—SFAR88 Compliance,’’ Revision 

C, in accordance with the Accomplishment 

Instruction of Bombardier Service Bulletin 8– 

28–35, Revision C, dated January 14, 2013. 

(8) For airplanes having S/Ns 002 through 

619 inclusive on which metric refuel/defuel 

indicators have been installed as specified in 

CR828CH00020, excluding airplanes on 

which a long range fuel system has been 

installed as specified in CR828CH00044, 

CF828SO08061, SOO 8061, CR828CH00027, 

or CR828SO00006: Accomplish Bombardier 

Modsum 8Q901117, ‘‘Production/Retrofit— 

Fuel System—Metric Indication—Fuel Tank 

Wiring Installation—SFAR 88,’’ Revision C, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–43, Revision A, dated June 25, 2009. 

(9) For airplanes having S/Ns 003 through 

619 inclusive, excluding airplanes that have 

incorporated Modsum 8Q101652 in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–36, Revision A, dated November 17, 

2006; or Revision B, dated February 12, 2008: 

Accomplish Bombardier Modsum 8Q101652, 

‘‘Electrical—Fuel Quantity Indication Wire 

Routing Segregation and Identification,’’ 

Revision F, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–36, Revision C, dated 

October 7, 2009. In addition, for Models 

DHC–8–102, –103, –106, –201, and –202 

airplanes on which an active noise and 

vibration suppression (ANVS) system has 

been installed, and on which Modsum 

8Q101652 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–36, Revision A, dated November 17, 

2006; or Revision B, dated February 12, 2008: 

Do the actions specified in paragraph (h)(1) 

of this AD. 

(10) For airplanes having S/Ns 003 through 

672 inclusive on which Modsum 8Q101513 

or 8Q101652 has been installed as specified 

in CR828CH00044, CR828SO08061, SOO 

8061, CR828CH00027, or CR828CO00006, 

excluding airplanes having a long range fuel 

system: Accomplish Bombardier Modsum 

8Q101907, ‘‘Fuel System—Fuel Qty Ind., 

Wire Routing Segregation, Installation of Top 

Hat Support—SFAR88 (Standard Aircraft),’’ 

Revision B, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–48, Revision A, dated 

February 27, 2012. 

(11) For airplanes having S/Ns 003 through 

619, excluding airplanes on which a long 

range fuel system has been installed as 

specified in CR828CH00044, CR828SO08061, 

SOO 8061, CR828CH00027, or 

CR828SO00006, and excluding airplanes on 

which Modsum 8Q101652 was incorporated 

in accordance with the Accomplishment 

Instructions in Bombardier Service Bulletin 

8–28–36, Revision A, dated November 17, 

2006; Revision B, dated February 12, 2008, or 

Revision C, dated October 7, 2009: 

Accomplish Modsum 8Q101908, ‘‘Fuel 

System—Fuel Qty Ind., Wire Routing 

Segregation, Installation of Dual Spacers— 

SFAR88 (Standard A/C),’’ Revision B, in 

accordance with the Accomplishment 

Instruction of Bombardier Service Bulletin 8– 

28–55, dated July 23, 2012. In addition, for 

airplanes on which Modsum 8Q101652 was 

incorporated in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–36, dated August 9, 

2006; Revision A, dated November 17, 2006; 

Revision B, dated February 12, 2008; or 

Revision C, dated October 7, 2009: Do the 

actions in paragraph (i)(1) of this AD. 

(12) For airplanes having S/Ns 002 through 

629 inclusive, on which a long range fuel 

system has been installed as specified in 

CR828CH00044, CR828SO08061, SOO 8061, 

CF828CH00027, or CR828SO00006, 

excluding airplanes on which Modsum 

8Q902064 has been incorporated in 

accordance with the Accomplishment 

Instructions contained in Bombardier Service 

Bulletin 8–28–42: Accomplish Bombardier 

Modsum 8Q902064, ‘‘Electrical—Long Range 

Fuel Quantity Indication Wire Routing 

Segregation and Identification—SFAR 88,’’ 

Revision G, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–42, Revision A, dated 

October 1, 2008. 

(13) For airplanes having S/Ns 003 through 

672 inclusive on which a long range fuel 

system has been installed as specified in 

CR828CH00044, CR828SO08061, SOO 8061, 

CR828CH00027, or CR828SO00006; and with 

Modsum 8Q902064 and either Modsum 

8Q101513 or Modsum 8Q101652: 

Accomplish Bombardier Modsum 8Q902382, 

‘‘Fuel System—Fuel Qty Ind., Wire Routing 

Segregation, Installation of Top Hat 

Support—SFAR88 (Long Range Aircraft),’’ 

Revision B, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–49, Revision A, dated 

July 23, 2012. 

(14) For airplanes having S/Ns 003 through 

629 inclusive on which a long range fuel 

system has been installed as specified in 

CR828CH00044, CR828SO08061, SOO 8061, 

CR828CH00027, or CR828SO00006, 

excluding airplanes on which Modsum 

8Q902064 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–42, dated December 21, 2008 or 

Revision A, dated October 1, 2008: 

Accomplish Bombardier Modsum 8Q902383, 

‘‘Fuel System—Fuel Qty Ind., Wire Routing 

Segregation, Installation of Dual Spacers— 

SFAR88 (Long Range A/C),’’ Revision B, 

including installing dual spacers inside the 

center fuselage at certain locations, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–56, dated July 23, 2012. 

(h) Inspections, Modifications, and 

Corrective Actions—Part II 

For the airplanes identified in paragraphs 

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

12,000 flight hours or 72 months, whichever 

occurs first, after the effective date of this 

AD, do the actions specified in paragraphs 

(h)(1), (h)(2), and (h)(3) of this AD, as 

applicable. 

(1) For Model DHC–8–102, –103, –106, 

–201, and –202 airplanes having S/Ns 003 

through 619 inclusive, on which an ANVS 

system has been installed and on which 

Modsum 8Q101652 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–36, dated August 9, 2006; or Revision 

A, dated November 17, 2006; or Revision B, 

dated February 12, 2008: Accomplish 

Bombardier Modsum 8Q101652, 

‘‘Electrical—Fuel Quantity Indication Wire 

Routing Segregation and Identification,’’ 

Revision F, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–36, Revision C, dated 

October 7, 2009. 

(2) For Model DHC–8–102, –103, –106, 

–201, and –202 airplanes having S/Ns 002 

through 629 inclusive, on which an ANVS 

system has been installed and on which 

Modsum 8Q902064 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–42, dated December 21, 2008: 

Accomplish Bombardier Modsum 8Q902064, 

‘‘Electrical—Long Range Fuel Quantity 

Indication Wire Routing Segregation and 

Identification—SFAR 88,’’ Revision G, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–42, Revision A, dated October 1, 2008. 

(3) For Model DHC–8–102, –103, –106, 

–201, and –202 airplanes having S/Ns 620 

through 666 inclusive, on which an ANVS 

system has been installed: Do a one-time 

visual inspection to determine whether the 

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60804 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 

fuel quantity indicating system (FQIS) wiring 

harness is routed correctly and relocate if 

necessary, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–52, dated November 3, 

2009. 

(i) Wire Routing Segregation and Installation 

of Dual Spacers—Part III 

Within 18,000 flight hours or 108 months, 

whichever occurs first, after the effective date 

of this AD, do the modification specified in 

paragraphs (i)(1) and (i)(2) of this AD, as 

applicable. 

(1) For airplanes having S/Ns 003 through 

672 inclusive, on which Modsum 8Q101513 

has been incorporated or on which Modsum 

8Q101652 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–36, dated August 9, 2006; Revision A, 

dated November 17, 2006; Revision B, dated 

February 12, 2008; or Revision C, dated 

October 7, 2009; excluding airplanes on 

which a long-range fuel system has been 

installed as specified in CF828CH00044, 

CR828SO08061, SOO 8061, CR828CH00027, 

or CR828SO00006: Accomplish Bombardier 

Modsum 8Q101908, ‘‘Fuel System—Fuel Qty 

Ind., Wire Routing Segregation, Installation 

of Dual Spacers—SFAR88 (Standard A/C),’’ 

Revision B, including installing dual spacers 

inside certain center fuselage locations, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–55, dated July 23, 2012. 

(2) For airplanes having S/Ns 003 through 

672 inclusive on which a long-range fuel 

system has been installed as specified in 

CF828CH00044, CR828SO08061, SOO 8061, 

CR828CH00027, or CR828SO00006, and on 

which Modsum 8Q902064 has been 

incorporated, or on which Modsum 

8Q902064 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–42, dated December 21, 2008; or 

Revision A, dated October 1, 2008: 

Accomplish Bombardier Modsum 8Q902383, 

‘‘Fuel System—Fuel Qty Ind., Wire routing 

Segregation, Installation of Dual Spacers— 

SFAR88 (Long Range A/C),’’ Revision B, 

including installing dual spacers inside 

certain center fuselage locations, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–56, dated July 23, 2012. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–39, 

Revision A, March 15, 2007. 

(2) This paragraph provides credit for 

actions required by paragraph (g)(3) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–44, dated 

August 9, 2006; or Revision A, dated 

November 15, 2006. 

(3) This paragraph provides credit for 

actions required by paragraph (g)(6) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–41, 

Revision A, dated April 11, 2007. 

(4) This paragraph provides credit for 

actions required by paragraph (g)(8) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–43, dated 

August 10, 2006. 

(5) This paragraph provides credit for 

actions required by paragraph (g)(10) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–48, dated 

October 1, 2010. 

(6) This paragraph provides credit for 

actions required by paragraph (g)(13) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–49, dated 

October 1, 2010. 

(7) This paragraph provides credit for 

actions required by paragraph (h)(3) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–53, dated 

November 3, 2008. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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 ATTN: 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 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–07, dated 

March 1, 2013, for related information, which 

can be found in the AD docket on the 

internet at http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

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

may review copies of 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 

September 19, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24077 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0836; Directorate 

Identifier 2013–NM–126–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) 2005–07– 

12 that applies to certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2005–07–12 requires detailed and 

eddy current inspections to detect 

cracking of the frame web around the 

cutout for the doorstop intercostal strap 

at the aft side of the station (STA) 291.5 

frame at stringer 16R, and corrective 

action if necessary. Since we issued AD 

2005–07–12, we received reports of new 

findings of cracking at various locations 

of the STA 277 to STA 291.5 frames and 

intercostals, including webs, chords, 

clips, and shear ties, between stringers 

7R and 17R. This proposed AD would 

add new inspections for cracking at the 

forward galley door cutout, and 

corrective actions if necessary. This 

proposed AD would also reduce a 

certain inspection threshold required by 

AD 2005–07–12. We are proposing this 

AD to detect and correct fatigue 

cracking of the aft frame and frame 

support structure of the forward galley 

door, which could result in a severed 

fuselage frame web, rapid 

decompression of the airplane, and 

possible loss of the forward galley door. 

DATES: We must receive comments on 

this proposed AD by November 18, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

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