53630 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 

10.11 Average annual electrical standby 

mode and off mode energy consumption. 

Calculate the annual electrical standby mode 

and off mode energy consumption (ESO) in 

kilowatt-hours, defined as: 

ESO = ((PW,SB * (4160 ¥ BOH)) + (PW,OFF * 

4600)) * K 

Where: 

PW,SB = furnace or boiler standby mode 

power, in watts, as measured in section 

8.6 of this appendix 

4,160 = average heating season hours per year 

PW,OFF = furnace or boiler off mode power, 

in watts, as measured in section 8.6 of 

this appendix 

4,600 = average non-heating season hours per 

year 

K = 0.001 kWh/Wh, conversion factor for 

watt-hours to kilowatt-hours 

BOH = total burner operating hours as 

calculated in section 10.4 for gas or oilfueled furnaces or boilers. Where for gas 

or oil-fueled furnaces and boilers 

equipped with single-stage controls, 

BOH = BOHSS ; for gas or oil-fueled 

furnaces and boilers equipped with twostage controls, BOH = (BOHR + BOHH); 

and for gas or oil-fueled furnaces and 

boilers equipped with step-modulating 

controls, BOH = (BOHR + BOHM). For 

electric furnaces and boilers, BOH = 

100(2080)(0.77)DHR/(Ein 3.412)(AFUE)) 

Where: 

100 = to express a percent as a decimal 

2,080 = as specified in 10.4.1 of this 

appendix 

0.77 = as specified in 10.4.1 of this appendix 

DHR = as defined in 10.4.1 of this appendix 

3.412 = conversion to express energy in terms 

of KBtu instead of kilowatt-hours 

AFUE = as defined in 11.1 of ANSI/ASHRAE 

Standard 103–1993 (incorporated by 

reference, see § 430.3) in percent 

Ein = Steady-state electric rated power, in 

kilowatts, from section 9.3 of ANSI/ 

ASHRAE Standard 103–1993 

(incorporated by reference, see § 430.3). 

[FR Doc. 2013–21095 Filed 8–29–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0450; Directorate 

Identifier 2013–CE–010–AD; Amendment 

39–17543; AD 2013–16–05] 

RIN 2120–AA64 

Airworthiness Directives; Alexander 

Schleicher GmbH & Co. 

Segelflugzeugbau Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Alexander Schleicher GmbH & Co. 

Segelflugzeugbau Models AS –K13, 

Ka2B, Ka 6, Ka 6 B, Ka 6 BR, Ka 6 C, 

Ka 6 CR, K7, K8, and K 8 B sailplanes. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 


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Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 53631 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as misalignment of 

the automatic elevator control 

connection. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective October 4, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the 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 

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 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@alexanderschleicher.de; Internet: http://

www.alexander-schleicher.de/. You may 

review copies of the 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. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: jim.rutherford@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 23, 2013 (78 FR 30791), 

and proposed to supersede AD 64–07– 

05, Amendment 701 (29 FR 3227, March 

11, 1964) (‘‘AD 64–07–05’’). The NPRM 

proposed to correct an unsafe condition 

for the specified products. 

Since we issued AD 64–07–05, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, issued a new AD, AD No. 

2013–0091, dated April 12, 2013 

(referred to after this as ‘‘the MCAI’’), to 

add additional sailplane models to the 

applicability and to add additional 

inspections of the elevator control 

connection. Alexander Schleicher 

GmbH & Co. Segelflugzeugbau has also 

issued revised service information to 

address the unsafe condition. The MCAI 

states: 

A recent report has been received concerning 

a problem with the elevator control during 

take-off of an ASK 13 sailplane. The results 

of the technical investigation revealed a 

misalignment in the automatic elevator 

control connection, presumably caused by an 

incorrect repair or damage at the tail-planearea. In addition, similar elevator connection 

failure during early 1960’s which led to the 

issuance of LBA LTM 4/62. However, LTM, 

4/62 did not apply to ASK 13 and ASK 18 

sailplanes coming later into production. 

This condition, if not detected and 

corrected, could lead to failure of the 

automatic elevator control connection, 

possibly resulting in loss of control of the 

sailplane. 

To address this unsafe condition, 

Alexander Schleicher GmbH issued a 

Technical Note (TN) (Ka 6 TN–Nr. 26; K 7 

TN–Nr. 24; K 8 TN–Nr. 30; ASK 13 TN–Nr. 

19; ASK 18 TN–Nr. 9) providing instructions 

for elevator control inspection and 

replacement and EASA issued AD 2012–0246 

to require accomplishment of those 

instructions. 

Since that AD was issued, Alexander 

Schleicher GmbH issued a revision of TN (Ka 

6 TN–Nr. 26; K 7 TN–Nr. 24; K 8 TN–Nr. 30; 

ASK 13 TN–Nr. 19, ASK 18 TN–Nr. 9), dated 

08 January 2013 to re-introduce a pushrod 

support modification for K 7 and K 8 

sailplanes, previously required by LBA LTM 

4/62, but no longer required by EASA AD 

2012–0246, which superseded the LBA LTM. 

For the reasons described above, this AD 

retains the requirements of EASA AD 2012– 

0246, which is superseded, and additionally 

requires, for K 7 and K 8 sailplanes, 

verification of embodiment of pushrod 

support modification, and depending on 

finding, pushrod support modification. 

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 NPRM (78 

FR 30791, May 23, 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 

30791, May 23, 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 30791, 

May 23, 2013). 

Costs of Compliance 

We estimate that this AD will affect 

127 products of U.S. registry. We also 

estimate that it will take about .5 workhour per product to comply with the 

new inspection requirements of this AD. 

The average labor rate is $85 per workhour. 

Based on these figures, we estimate 

the cost of the initial inspection 

required in this AD on U.S. operators to 

be $5,397.50, or $42.50 per product. 

We have no way of determining the 

number of repetitive inspections an 

owner/operator will incur over the life 

of the sailplane. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 1 work-hour and require parts 

costing $119, for a cost of $204 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with actions retained from AD 

64–07–05 for Models Ka2B, Ka 6, Ka 6 

B, Ka 6 BR, Ka 6 C, Ka 6 CR, K7, K8, 

and K 8 B sailplanes in this AD, which 

affects 112 products of U.S. registry, and 

may require parts costing $103, for a 

cost of $273 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. 


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53632 Federal Register / Vol. 78, No. 169 / Friday, August 30, 2013 / Rules and Regulations 

For the reasons discussed above, I 

certify 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; 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 the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 

removing Amendment 701 (29 FR 3227, 

March 11, 1964) and adding the 

following new AD: 

2013–16–05 Alexander Schleicher GmbH & 

Co. Segelflugzeugbau: Amendment 39– 

17543; Docket No. FAA–2013–0450; 

Directorate Identifier 2013–CE–010–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 4, 2013. 

(b) Affected ADs 

This AD supersedes AD 64–07–05, 

Amendment 701 (29 FR 3227; March 11, 

1964). 

(c) Applicability 

This AD applies to Alexander Schleicher 

GmbH & Co. Segelflugzeugbau Models AS 

–K13, Ka2B, Ka 6, Ka 6 B, Ka 6 BR, Ka 6 C, 

Ka 6 CR, K7, K8, and K 8 B sailplanes, all 

serial numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as 

misalignment of the automatic elevator 

control connection. The European Aviation 

Safety Agency (EASA) has issued a new AD 

to add additional sailplane models to the 

applicability and to add additional 

inspections of the elevator control 

connection. Alexander Schleicher GmbH & 

Co. Segelflugzeugbau has also issued revised 

service information to address the unsafe 

condition. We are issuing this AD to prevent 

failure of the automatic elevator control 

connection, which could result in loss of 

control. 

(f) Actions and Compliance Retained From 

AD 64–07–05, Amendment 701 (29 FR 3227, 

March 1, 1964) 

Unless already done, do the following 

actions specified in paragraphs (f)(1), (f)(2), 

and (f)(3) of this AD. 

(1) For Models Ka2B, Ka 6, Ka 6 B, Ka 6 

BR, Ka 6 C, Ka 6 CR, K7, K8, and K 8 B: 

Unless already done, within the next 10 

hours time-in-service (TIS) after April 13, 

1964 (the effective date retained from AD 64– 

07–05, Amendment 701 (29 FR 3227, March 

1, 1964)), inspect the automatic elevator 

control rod for conformity following 

Alexander Schleicher Automatischer 

Ho ̈henruderanschlub (English translation: 

Automatic Elevator Connection) document, 

dated December 5, 1961, translation added 

May, 2012. 

(2) For Models Ka2B, Ka 6, Ka 6 B, Ka 6 

BR, Ka 6 C, Ka 6 CR, K7, K8, and K 8 B: If 

any discrepancy is found during the 

inspection required in paragraph (f)(1) of this 

AD, before further flight, make any necessary 

repairs or modification. 

Note to paragraph (f)(2) of this AD: For 

guidance on making the necessary repairs or 

modification required in paragraph (f)(2) of 

this AD, you may refer to 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. 

(3) For Models Ka2B, K7, K8 and K 8 B: 

Unless already done, within the next 10 

hours TIS after April 13, 1964 (the effective 

date retained from AD 64–07–05, 

Amendment 701 (29 FR 3227, March 1, 

1964)), install an additional push pull rod 

support. For Models Ka2B, follow Alexander 

Schleicher Modification No. 7, dated July 4, 

1962. For Models K7, follow Alexander 

Schleicher Modification No. 8, dated 

November 23, 1961. For Models K8, follow 

Alexander Schleicher Modification No. 7, 

dated November 24, 1961. 

(g) New Actions and Compliance 

Unless already done, do the following 

actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) For all models: Within 90 days after 

October 4, 2013 (the effective date of this AD) 

and repetitively thereafter at intervals not to 

exceed 12 months, inspect the elevator 

control rod in the tailplane following the 

Action section in 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. 

(2) For all models: During any inspection 

required in paragraph (g)(1) of this AD, if any 

bend and/or misaligned elevator control 

connection is detected, before further flight 

after the inspection, replace the elevator 

control connection with a serviceable part. 

Do the replacement following the Action 

section in 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. 

(h) Credit for Actions Done Following 

Previous Service Information 

This AD provides credit for the initial 

inspection required in paragraph (g)(1) of this 

AD and any necessary replacement required 

in paragraph (g)(2) of this AD if already done 

before the effective date of this AD following 

the Action sections in 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. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 


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(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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