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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


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

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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• 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:



### E STIMATED 

### 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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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: