Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17399 

FAA–2013–0966; Directorate Identifier 

2013–CE–040–AD. 

(a) Effective Date 

This AD is effective May 2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to the following 

Rockwell Collins, Inc. Mode S transponders 

that are installed on but not limited to the 

airplanes listed in paragraphs (c)(2)(i) and 

(c)(2)(ii) of this AD: 

(i) TPR–720: CPN 622–7878–001, 622– 

7878–020, 622–7878–120, 622–7878–200, 

622–7878–201, 622–7878–301, 622–7878– 

440, 622–7878–460, 622–7878–480, 622– 

7878–901; and 

(ii) TPR–900: CPN 822–0336–001, 822– 

0336–020, 822–0336–220, 822–0336–440, 

822–0336–460, 822–0336–480, 822–0336– 

902. 

(2) The products listed in paragraphs 

(c)(1)(i) and (c)(1)(ii) of this AD may be 

installed on but not limited to the following 

airplanes, certificated in any category: 

(i) Airbus Models A319, A320, A330, 

A340; and 

(ii) The Boeing Company Models B737, 

B747, B757, B767, B777, MD–80, and DC–9. 

(3) The listing of airplanes in paragraphs 

(c)(2)(i) and (c)(2)(ii) of this AD is not 

intended as all-inclusive. The affected 

transponders may be installed using a 

supplemental type certificate or other means 

on other airplanes not listed in those 

paragraphs. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 34, Navigation. 

(e) Unsafe Condition 

This AD was prompted by the 

identification that the TPR–720 and TPR–900 

Mode S transponders respond intermittently 

to Mode S interrogations from both groundbased and traffic collision avoidance system 

equipped airplanes. We are issuing this AD 

to correct possible misalignment issues with 

the transponders that could result in 

increased pilot and air traffic controller 

workload as well as reduced separation of 

airplanes. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraph (g) 

of this AD, unless already done. 

(g) Test and Calibration 

(1) Within the next 2 years after the 

effective date of this AD and repetitively 

thereafter at intervals not to exceed every 4 

years, send the TPR–720 and TPR–900 Mode 

S transponders to a properly certified repair 

facility for test and calibration to assure 

proper alignment following Rockwell Collins 

Service Information Letter 13–1, Revision No. 

1, 523–0821603–101000, dated October 24, 

2013. 

(2) Rockwell Collins Service Information 

Letter 13–1, Revision No. 1, 523–0821603– 

101000, dated October 24, 2013, recommends 

the affected transponders be sent to a 

Rockwell Collins authorized repair facility 

for the alignment and return to service 

testing; however, any properly certified 

repair facility may do this alignment and 

return to service testing. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i) of this AD. 

(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. 

(i) Related Information 

For more information about this AD, 

contact Roger A. Souter, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: 316–946–4134; 

facsimile: 316–946–4107; email address: 

roger.souter@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Rockwell Collins Service Information 

Letter 13–1, Revision No. 1, 523–0821603– 

101000, dated October 24, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Rockwell Collins, Inc., 

Collins Aviation Services, 350 Collins Road 

NE., M/S 153–250, Cedar Rapids, IA 52498– 

0001; telephone: 888–265–5467 (U.S.) or 

319–265–5467; fax: 319–295–4941 (outside 

U.S.); email: techmanuals@

rockwellcollins.com; Internet: http://

www.rockwellcollins.com/Services_and_

Support/Publications.aspx. 

(4) You may review this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on March 

4, 2014. 

Steven W. Thompson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–05202 Filed 3–27–14; 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; Amendment 

39–17790; AD 2014–05–17] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

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

–315 airplanes. This AD was prompted 

by results from fuel system reviews 

conducted by the manufacturer. This 

AD requires accomplishing 

modifications to the fuel system. 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. 

DATES: This AD becomes effective May 

2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0835; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., QSeries 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 view 

this referenced service information at 

the FAA, Transport Airplane 


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Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

NPRM published in the Federal 

Register on October 2, 2013 (78 FR 

60800). The NPRM was prompted by 

results from fuel system reviews 

conducted by the manufacturer. The 

NPRM proposed to require 

accomplishing modifications to the fuel 

system. 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. 

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 examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0835- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 60800, October 2, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

60800, October 2, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 60800, 

October 2, 2013). 

Costs of Compliance 

We estimate that this AD affects 94 

airplanes of U.S. registry. 

We also estimate that it will take 

about 519 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $58,924 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$9,685,666, or $103,039 per product. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0835; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2014–05–17 Bombardier, Inc.: Amendment 

39–17790. Docket No. FAA–2013–0835; 

Directorate Identifier 2013–NM–095–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 2, 2014. 

(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 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 


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(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 

Comply with this AD within the 

compliance times specified, unless already 

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 Bombardier 

ModSum 8Q101512, ‘‘Fuel System—Fuel 

Tank Mechanical Design, SFAR 88 

Compliance (Retrofit),’’ Revision G, dated 

June 10, 2009, 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 specified in de Havilland Change 

Request (CR) CR828CH00044, 

CR828SO08061, CR828CH00027, 

CR828SO00006, or Special Order Option 

(SOO) 8061 has been installed: Accomplish 

Bombardier ModSum 8Q902091, ‘‘Fuel 

System—Fuel Tank Mech. Design, SFAR 88 

Compl.—Extended Range Tank Option 

(Retrofit),’’ Revision C, dated December 22, 

2006, 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 de Havilland SOO 

8155, SOO 8098, SOO 8099, SOO 6082, or 

CR849SO08155; 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),’’ 

Revision E, dated June 17, 2009, 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, dated 

May 26, 2008, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–47, dated May 2, 2008. 

(5) For Model DHC–8–102, –103, and –106 

airplanes 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, 

dated October 19, 2010, 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 specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, or CR828SO00006, or SOO 

8061 has been installed, including airplanes 

on which metric refuel/defuel indicators 

specified in de Havilland CR828CH00029 

have been installed: Accomplish Bombardier 

ModSum 8Q902122, ‘‘Production/Retrofit— 

Fuel System—Long Range Wiring 

Installation—SFAR 88 Compliance,’’ 

Revision F, dated December 8, 2011, 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 specified in de 

Havilland CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

0861, has been installed: Accomplish 

Bombardier ModSum 8Q101511, 

‘‘Production/Retrofit—Fuel System—Fuel 

Tank Wiring Installation—SFAR88 

Compliance,’’ Revision C, dated January 30, 

2009, 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 specified in de Havilland 

CR828CH00020 have been installed, 

excluding airplanes on which a long range 

fuel system specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed: Accomplish 

Bombardier ModSum 8Q901117, 

‘‘Production/Retrofit—Fuel System—Metric 

Indication—Fuel Tank Wiring Installation— 

SFAR 88,’’ Revision C, dated March 23, 2009, 

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 on which 

Bombardier ModSum 8Q101652 specified in 

Bombardier Service Bulletin 8–28–36, 

Revision A, dated November 17, 2006; or 

Revision B, dated February 12, 2008; has 

been installed: Accomplish Bombardier 

ModSum 8Q101652, ‘‘Electrical—Fuel 

Quantity Indication Wire Routing 

Segregation and Identification,’’ Revision F, 

dated March 10, 2011, in accordance with the 

Accomplishment Instructions of Bombardier 

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

October 7, 2009. In addition, for Model 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 Bombardier 

ModSum 8Q101652 specified in Bombardier 

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

November 17, 2006; or Revision B, dated 

February 12, 2008; has been incorporated: Do 

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

this AD. 

(10) For airplanes having S/Ns 003 through 

672 inclusive on which Bombardier ModSum 

8Q101513 or 8Q101652 specified in de 

Havilland CR828CH00044, CR828SO08061, 

CR828CH00027, CR828CO00006, or SOO 

8061 has been installed, excluding airplanes 

having a long range fuel system installed: 

Accomplish Bombardier ModSum 8Q101907, 

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

Segregation, Installation of Top Hat 

Support—SFAR88 (Standard Aircraft),’’ 

Revision B, dated September 10, 2010, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–48, Revision A, dated July 23, 2012. 

(11) For airplanes having S/Ns 003 through 

619 inclusive, excluding airplanes on which 

a long range fuel system specified in de 

Havilland CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed; and excluding 

airplanes on which Bombardier ModSum 

8Q101652 specified 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, has been installed: 

Accomplish Bombardier ModSum 8Q101908, 

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

Segregation, Installation of Dual Spacers— 

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

September 10, 2010, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–55, dated July 23, 

2012. In addition, for airplanes on which 

Bombardier ModSum 8Q101652 specified in 

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; 

has been installed: 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 specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed; excluding airplanes 

on which Bombardier ModSum 8Q902064 

specified in Bombardier Service Bulletin 8– 

28–42 has been incorporated: Accomplish 

Bombardier ModSum 8Q902064, 

‘‘Electrical—Long Range Fuel Quantity 

Indication Wire Routing Segregation and 

Identification—SFAR 88,’’ Revision G, dated 

March 10, 2011, 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 specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed; and on which 

Bombardier ModSum 8Q902064, and either 

Bombardier ModSum 8Q101513 or ModSum 

8Q101652, has been installed: Accomplish 

Bombardier ModSum 8Q902382, ‘‘Fuel 

System—Fuel Qty Ind., Wire Routing 

Segregation, Installation of Top Hat 

Support—SFAR88 (Long Range Aircraft),’’ 

Revision B, dated September 10, 2010, 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 specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 


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8061, has been installed; excluding airplanes 

on which Bombardier ModSum 8Q902064 

specified in Bombardier Service Bulletin 8– 

28–42, dated December 21, 2006, or Revision 

A, dated October 1, 2008, has been installed: 

Accomplish Bombardier ModSum 8Q902383, 

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

Segregation, Installation of Dual Spacers— 

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

dated September 10, 2010, 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 airplanes identified in paragraphs 

(h)(1), (h)(2), and (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 

Bombardier ModSum 8Q101652 specified in 

Bombardier Service Bulletin 8–28–36, dated 

August 9, 2006, Revision A, dated November 

17, 2006, or Revision B, dated February 12, 

2008, has been installed: Accomplish 

Bombardier ModSum 8Q101652, 

‘‘Electrical—Fuel Quantity Indication Wire 

Routing Segregation and Identification,’’ 

Revision F, dated March 10, 2011, 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 

Bombardier ModSum 8Q902064 specified in 

Bombardier Service Bulletin 8–28–42, 

Revision A, dated October 1, 2008, has been 

installed: Accomplish Bombardier ModSum 

8Q902064, ‘‘Electrical—Long Range Fuel 

Quantity Indication Wire Routing 

Segregation and Identification—SFAR 88,’’ 

Revision G, dated March 10, 2011, 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 

fuel quantity indicating system (FQIS) wiring 

harness is routed correctly and relocate the 

wiring harness 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 

paragraph (i)(1) or (i)(2) of this AD, as 

applicable. 

(1) For airplanes having S/Ns 003 through 

672 inclusive on which Bombardier ModSum 

8Q101513 has been incorporated; or on 

which Bombardier ModSum 8Q101652 

specified in 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, has been incorporated; 

excluding airplanes on which a long-range 

fuel system specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed: Accomplish 

Bombardier ModSum 8Q101908, ‘‘Fuel 

System—Fuel Qty Ind., Wire Routing 

Segregation, Installation of Dual Spacers— 

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

September 10, 2010, 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 specified in de Havilland 

CR828CH00044, CR828SO08061, 

CR828CH00027, CR828SO00006, or SOO 

8061, has been installed; and on which 

Bombardier ModSum 8Q902064 has been 

incorporated, or on which ModSum 

8Q902064 as specified in Bombardier Service 

Bulletin 8–28–42, dated December 21, 2006, 

or Revision A, dated October 1, 2008, has 

been incorporated: Accomplish Bombardier 

ModSum 8Q902383, ‘‘Fuel System—Fuel Qty 

Ind., Wire routing Segregation, Installation of 

Dual Spacers—SFAR88 (Long Range A/C),’’ 

Revision B, dated September 10, 2010, 

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. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2013-0835-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 8–28–35, 

Revision C, dated January 14, 2013. 

(ii) Bombardier Service Bulletin 8–28–36, 

Revision C, dated October 7, 2009. 

(iii) Bombardier Service Bulletin 8–28–39, 

Revision B, dated August 19, 2009. 

(iv) Bombardier Service Bulletin 8–28–41, 

Revision B, dated August 8, 2012. 

(v) Bombardier Service Bulletin 8–28–42, 

Revision A, dated October 1, 2008. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17403 

(vi) Bombardier Service Bulletin 8–28–43, 

Revision A, dated June 25, 2009. 

(vii) Bombardier Service Bulletin 8–28–44, 

Revision B, dated July 25, 2009. 

(viii) Bombardier Service Bulletin 8–28–47, 

dated May 2, 2008. 

(ix) Bombardier Service Bulletin 8–28–48, 

Revision A, dated July 23, 2012. 

(x) Bombardier Service Bulletin 8–28–49, 

Revision A, dated July 23, 2012. 

(xi) Bombardier Service Bulletin 8–28–52, 

dated November 3, 2009. 

(xii) Bombardier Service Bulletin 8–28–55, 

dated July 23, 2012. 

(xiii) Bombardier Service Bulletin 8–28–56, 

dated July 23, 2012. 

(xiv) Bombardier Service Bulletin 8–28–58, 

dated July 25, 2011. 

(xv) Bombardier Service Bulletin 8–57–44, 

Revision D, dated October 8, 2008. 

(3) 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. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

19, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–05939 Filed 3–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0862; Directorate 

Identifier 2011–NM–198–AD; Amendment 

39–17803; AD 2014–05–31] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–08– 

25 that applied to certain The Boeing 

Company Model 747–400 and 747–400F 

series airplanes. AD 2008–08–25 

required installing drains and drain 

tubes to eliminate water accumulation 

in the drip shield above the M826 

cardfile in the main equipment center. 

This new AD requires installing 

modified drain tubes, relocating wire 

bundle routing, installing a new drip 

shield and drip shield deflectors, and 

replacing insulation blankets. For 

certain airplanes, this new AD also 

concurrently requires sealing the drain 

slot, installing spuds, and installing 

drain tubes. This AD was prompted by 

reports of continued water damage to 

diode fire card 285U0072–1 in the M826 

automatic fire overheat logic test system 

cardfile following a false FWD CARGO 

FIRE message, with no change in 

frequency, which resulted in an air turn 

back. We are issuing this AD to prevent 

water from exiting over the edge of the 

existing drip shield and contaminating 

electrical components in the M826 

cardfile, which could result in an 

electrical short and potential loss of 

several functions essential for safe 

flight. 

DATES: This AD is effective May 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA 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 by searching for 

and locating Docket No. FAA–2012– 

0862; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Control 

Systems, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6596; fax: 425–917– 

6590; email: francis.smith@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–08–25, 

Amendment 39–15479 (73 FR 21240, 

April 21, 2008). AD 2008–08–25 applied 

to certain The Boeing Company Model 

747–400 and 747–400F series airplanes. 

The NPRM published in the Federal 

Register on September 6, 2012 (77 FR 

54854). The NPRM was prompted by 

reports of continued water damage to 

diode fire card 285U0072–1 in the M826 

automatic fire overheat logic test system 

cardfile following a false FWD CARGO 

FIRE message, with no change in 

frequency, which resulted in an air turn 

back. The NPRM proposed to require 

installing drain tubes, relocating wire 

bundle routing, installing a new drip 

shield and drip shield deflectors, and 

replacing insulation blankets. For 

certain airplanes, the NPRM also 

proposed to concurrently require sealing 

the drain slot, installing spuds, and 

installing drain tubes. We are issuing 

this AD to prevent water from exiting 

over the edge of the existing drip shield 

and contaminating electrical 

components in the M826 cardfile, which 

could result in an electrical short and 

potential loss of several functions 

essential for safe flight. 

Relevant Service Information 

Since we issued the NPRM (77 FR 

54854, September 6, 2012), we have 

reviewed Boeing Alert Service Bulletin 

747–25A3580, Revision 2, dated May 

13, 2013. We referred to Boeing Alert 

Service Bulletin 747–25A3580, Revision 

1, dated July 14, 2011, as an appropriate 

source of service information for 

accomplishing certain actions specified 

in the NPRM. 

Boeing Alert Service Bulletin 747– 

25A3580, Revision 2, dated May 13, 

2013, among other changes, revises line 

number 1087 to 1332 for group 1 

airplanes to account for airplanes that 

had the drain tubes installed in 

production, adds figures to account for 

actions required by certain groups, adds 

brackets and rivets, and changes certain 

part numbers of certain brackets. 

Boeing Alert Service Bulletin 747– 

25A3581, Revision 2, dated September 

11, 2012, among other things, clarifies 

wire routing, allows for trimming of 

parts, and adds parts to the top kit. 

We have added a new paragraph (i) to 

this final rule to allow for credit for 


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