Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 53633 

(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. 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2013–0091, dated 

April 12, 2013, which can be found in the AD 

docket on the Internet at http://

www.regulations.gov; FAA Civil Aeronautics 

Manual (CAM) 18, Maintenance, Repair, And 

Alteration, Of Airframes, Powerplants, 

Propellers, And Appliances, dated December 

15, 1959, which can be found on the Internet 

at: http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgccab.nsf/0/

41df1277f2dc7e0e86257bcf005112bf/$FILE/

CAM_18_1959.pdf, without handwritten 

annotations, as revised through November 

15, 1962; and Alexander Schleicher 

Technische Mitteilung (English translation: 

Technical Note) TM–Nr. 13 for Ka 2 and Ka 

2b, TM–Nr. 26 for Ka 6, TM–Nr. 24 for K 7, 

TM–Nr. 30 for K 8, TM–Nr. 19 for ASK 13, 

and TM–Nr. 9 for ASK 18, dated August 30, 

2012, which can be obtained from the 

manufacturer at the address specified in 

paragraph (k)(4) of this AD, for related 

information. 

(k) 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. 

(3) The following service information was 

approved for IBR on October 4, 2013. 

(i) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 13, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

(ii) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 26, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

(iii) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 24, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

(iv) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 30, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

(v) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 19, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

(vi) Alexander Schleicher Technische 

Mitteilung (English translation: Technical 

Note) TM–Nr. 9, Berichtigung 1 (English 

translation: Revision 1), dated January 8, 

2013. 

Note 1 to paragraphs (k)(3)(i) through 

(k)(3)(vi) of this AD: Alexander Schleicher 

Technische Mitteilung (English translation: 

Technical Note) TM–Nr. 13 for Ka 2 and Ka 

2b, TM–Nr. 26 for Ka 6, TM–Nr. 24 for K 7, 

TM–Nr. 30 for K 8, TM–Nr. 19 for ASK 13, 

and TM–Nr. 9 for ASK 18, all Berichtigung 

1 (English translation: Revision 1), all dated 

January 8, 2013, are co-published as one 

document. This service information contains 

German to English translation. EASA used 

the English translation in referencing the 

document from Alexander Schleicher GmbH 

& Co. Segelflugzeugbau. For enforceability 

purposes, we will cite references to the 

Alexander Schleicher GmbH & Co. 

Segelflugzeugbau service information as it 

appears on the document. 

(vii) Alexander Schleicher Automatischer 

Ho ̈henruderanschlub (English translation: 

Automatic Elevator Connection) document, 

dated December 5, 1961, translation added 

May, 2012. 

Note 2 to paragraph (k)(3)(vii) of this AD: 

This service information contains German to 

English translation. EASA used the English 

translation in referencing the document from 

Alexander Schleicher GmbH & Co. 

Segelflugzeugbau. For enforceability 

purposes, we will cite references to the 

Alexander Schleicher GmbH & Co. 

Segelflugzeugbau service information as it 

appears on the document. 

(viii) Alexander Schleicher Modification 

No. 7 Glider Ka 2 and Ka 2B, L–140 and L– 

203, dated July 4, 1962. 

(ix) Alexander Schleicher Modification No. 

7 Glider K 8 L–216, dated November 24, 

1961. 

(x) Alexander Schleicher Modification No. 

8 Glider K 7 L–211, dated November 23, 

1961. 

(4) For Alexander Schleicher GmbH & Co 

Segelflugzeugbau service information 

identified in this AD, contact Alexander 

Schleicher GmbH & Co Segelflugzeugbau, 

Stra+e 1 D—36163 Poppenhausen, Germany; 

phone: ++49 (0) 6658/89–0, fax: +49 (0) 6658/ 

89–40, email: info@alexander-schleicher.de; 

Internet: http://www.alexander-schleicher.de. 

(5) You may view this service information 

at 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. 

(6) 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 July 31, 

2013. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–21075 Filed 8–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1003; Directorate 

Identifier 2012–NM–064–AD; Amendment 

39–17563; AD 2013–16–25] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This AD was prompted 

by reports of advance pneumatic 

detectors (APDs) for engine fire/

overheat detector assemblies failing to 

reset after activation due to permanent 

deformation of the detector switch 

diaphragm after being exposed to high 

temperatures. This AD requires 

replacing all three APDs with new 

detector assemblies. We are issuing this 

AD to prevent a continued engine fire 

indication in the cockpit after the actual 

fire has been extinguished, which is 

misleading and might influence the 

pilot to conduct a potentially hazardous 

‘‘off-airport’’ landing. 

DATES: This AD becomes effective 

October 4, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 4, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

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. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7330; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 


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53634 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the specified 

products. The SNPRM published in the 

Federal Register on April 9, 2013 (78 FR 

21077). The notice of proposed 

rulemaking NPRM (77 FR 60060, 

October 2, 2012), which preceded the 

SNPRM, proposed to require replacing 

all three APDs with new detector 

assemblies. The SNPRM proposed to 

add airplanes to the applicability. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–07R1, 

effective December 21, 2012 (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: 

There have been engine fires on DHC–8 

Series 400 aeroplanes, where the ‘‘ENGINE 

FIRE, CHECK FIRE DETECT’’ warning and 

‘‘FUEL OFF’’ handle lights failed to reset and 

remained illuminated after the fire was 

extinguished. An investigation has revealed 

that the existing engine fire/overheat detector 

assemblies ‘‘Advance Pneumatic Detectors 

(APD)’’ may fail to reset after activation due 

to permanent deformation of the detector 

switch diaphragm after being exposed to high 

temperatures. 

This abnormal condition of a continued 

engine fire indication in the cockpit, after the 

actual fire has been extinguished, is 

misleading and may influence the pilot’s 

decision to conduct a potentially hazardous 

‘‘off-airport’’ landing, which is considered an 

unsafe condition that warrants mitigating 

action. 

To mitigate this potentially hazardous 

condition, Bombardier has issued multiple 

service bulletins (SBs) [Bombardier Service 

Bulletins 84–26–08, Revision A, dated May 

12, 2011; 84–26–09, Revision A, dated May 

12, 2011; and 84–26–12, Revision B, dated 

October 12, 2012] to replace all three affected 

APDs with new detector assemblies that are 

not susceptible to the subject diaphragm 

deformation when exposed to excessive heat. 

* * * 

This revised [Canadian] AD is issued to 

include the additional 26 aeroplane S/Ns in 

the applicability section of the AD. The 

additional S/Ns, 4374 through 4399, only 

affect the compliance with Part III of this 

[Canadian] AD. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(78 FR 21077, April 9, 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 SNPRM (78 FR 

21077, April 9, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 21077, 

April 9, 2013). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects 399 

products of U.S. registry. We also 

estimate that it will take about 63 workhours 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 $5,700 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$4,410,945, or $11,055 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 

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 AD and placed it in the AD docket. 

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 AD, the MCAI, 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: 

2013–16–25 Bombardier, Inc.: Amendment 

39–17563; Docket No. FAA–2012–1003; 

Directorate Identifier 2012–NM–064–AD. 

(a) Effective Date 

This AD becomes effective October 4, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

(S/Ns) 4001 through 4399 inclusive. 


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Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 53635 

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire protection. 

(e) Reason 

This AD was prompted by reports of 

advance pneumatic detectors (APDs) for 

engine fire/overheat detector assemblies 

failing to reset after activation due to 

permanent deformation of the detector 

switch diaphragm after being exposed to high 

temperatures. We are issuing this AD to 

prevent a continued engine fire indication in 

the cockpit after the actual fire has been 

extinguished, which is misleading and might 

influence the pilot to conduct a potentially 

hazardous ‘‘off-airport’’ landing. 

(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) Installation 

Within 6,000 flight hours or 30 months 

after the effective date of this AD, whichever 

occurs first, replace the APDs as specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

as applicable. 

(1) For airplanes having S/Ns 4001 through 

4373 inclusive: For the nacelle of the engine 

primary zone, remove any APD having part 

number (P/N) 10–1098 and install a new APD 

having P/N 10–1098–01, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–26–08, 

Revision B, dated September 24, 2012. 

(2) For airplanes having S/Ns 4001 through 

4373 inclusive: For the nacelle of the landing 

gear primary zone, remove any APD having 

P/N 10–1097 or 10–1097–01 and install a 

new APD having P/N 10–1097–02, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–26–09, Revision A, dated May 12, 2011. 

(3) For all airplanes: For the propeller 

engine controller, remove any APD having 

P/N 10–1096, 10–1096–01, or 10–1096–02 

(serial number is all numeric characters), and 

install a new APD having P/N 10–1096–02 

(serial number is three alpha and four 

numeric characters), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–26–12, Revision B, dated 

October 12, 2012. 

(h) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information specified in paragraph (h)(1)(i) or 

(h)(1)(ii) of this AD, which are not 

incorporated by reference in this AD. 

(i) Bombardier Service Bulletin 84–26–08, 

dated March 11, 2011. 

(ii) Bombardier Service Bulletin 84–26–08, 

Revision A, dated May 12, 2011. 

(2) 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 84–26–09, dated 

March 11, 2011, which is not incorporated by 

reference in this AD. 

(3) 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 the service 

information specified in paragraph (h)(3)(i) or 

(h)(3)(ii) of this AD, which are not 

incorporated by reference in this AD. 

(i) Bombardier Service Bulletin 84–26–12, 

dated October 12, 2011. 

(ii) Bombardier Service Bulletin 84–26–12, 

Revision A, dated December 13, 2011. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to 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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Airworthiness Directive CF–2012–07R1, 

effective December 21, 2012, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the address specified in 

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

(k) 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 84–26–08, 

Revision B, dated September 24, 2012. 

(ii) Bombardier Service Bulletin 84–26–09, 

Revision A, dated May 12, 2011. 

(iii) Bombardier Service Bulletin 84–26–12, 

Revision B, dated October 12, 2012. 

(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 review copies of the 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 August 

1, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19830 Filed 8–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0422; Directorate 

Identifier 2012–NM–097–AD; Amendment 

39–17567; AD 2013–17–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes; Model A340–200 and –300 

series airplanes; and Model A340–541 

and –642 airplanes. This final rule was 

prompted by reports of wing tip brakes 

(WTBs) losing their braking function in 

service due to heavy wear on the brake 

discs. WTBs are designed to stop and 

hold the mechanical transmission of 

slats and flaps in certain failure cases. 

This final rule requires repetitive 

operational tests of certain WTB 

pressure-off-brakes (POBs) for 

performance on the flap and slat 

systems, and replacement of any 

affected WTB with a new or serviceable 

part if the test fails. This final rule also 

requires eventual replacement of all 

affected WTBs with a new part, which 

terminates the repetitive tests. We are 

issuing this final rule to prevent loss of 

the WTB braking function, and 

consequent inability of the flap or slat 

system to be stopped and held in 


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