Federal Register / Vol. 80, No. 123 / Friday, June 26, 2015 / Rules and Regulations 36707 

(g) A notification that the Recipient has 

passed vetting does not constitute any other 

approval under this award. 

Alternate I. When subrecipients will be 

subject to vetting, add the following 

paragraphs to the basic award term: 

(h) When the prime recipient anticipates 

that it will require prior approval for a 

subaward in accordance with 2 CFR 

200.308(c)(6) the subaward is subject to 

vetting. The prospective subrecipient must 

submit a USAID Partner Information Form, 

USAID Form 500–13, to the vetting official 

identified in paragraph (c) of this provision. 

The agreement officer must not approve a 

subaward to any organization that has not 

passed vetting when required. 

(i) The recipient agrees to incorporate the 

substance of paragraphs (a) through (i) of this 

award term in all first tier subawards under 

this award. 

Alternate II. When specific classes of 

services are subject to vetting, add the 

following paragraph: 

(j) Prospective contractors at any tier 

providing the following classes of services 

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

must pass vetting. Recipients must not 

procure these services until they receive 

confirmation from the vetting official that the 

prospective contractor has passed vetting. 

(End of award term) 

Angelique M. Crumbly, 

Assistant Administrator, Bureau for 

Management. 

[FR Doc. 2015–15017 Filed 6–25–15; 8:45 am] 

BILLING CODE 6116–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1986; Directorate 

Identifier 2012–NM–100–AD; Amendment 

39–18188; AD 2015–13–01] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

ATR–GIE Avions de Transport Re ́gional 

Model ATR42–500 and ATR72–212A 

airplanes. This AD requires inspection 

of the affected control systems rods and, 

depending on findings, a replacement of 

the affected rods. This AD was 

prompted by reports of non-conformity 

of certain control rods, which could 

result in failure of the control rods. We 

are issuing this AD to detect and correct 

failure of an affected control rod, which, 

under certain circumstances, could 

result in reduced control of the airplane. 

DATES: This AD becomes effective July 

13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 2015. 

We must receive comments on this 

AD by August 10, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre 

Nadot, 31712 Blagnac Cedex, France; 

telephone +33 (0) 5 62 21 62 21; fax +33 

(0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.com. You may 

view this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1986. 

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–2015– 

1986; 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 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2012–0064, dated April 20, 

2012 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for Model ATR42– 

500 and ATR72–212A airplanes. The 

MCAI states: 

Prompted by the findings that led to 

publication of EASA AD 2010–0063–E, 

additional quality investigation showed that 

the non-conformity of certain control rods, 

which was due to incorrect polishing during 

the rod manufacturing process, could also 

affect other flight control rods [and could 

result in failure of the control rods]. 

These other potentially non-conforming 

control rods are installed on elevator 

controls, rudder pedal assemblies and rudder 

tab controls of certain ATR aeroplanes. 

This condition, if not detected and 

corrected, could lead to failure of an affected 

control rod which, under certain 

circumstances, could result in reduced 

control of the aeroplane. 

As a result of further investigations, other 

batches have been incriminated, in addition 

to the ones identified by EASA AD 2010– 

0063–E, and new safety analyses also 

indicate the need for replacement of the rods 

(within an adapted compliance time), which 

had passed the check required by EASA AD 

2010–0063–E. Consequently, EASA AD 

2010–0063–E is superseded by this new AD. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection of 

the affected control systems rods and, 

depending on findings, replacement of the 

affected rods. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–1986. 

Related Service Information Under 1 

CFR Part 51 

ATR–GIE Avions de Transport 

Re ́gional (ATR) has issued the following 

service information. 

• ATR Service Bulletin ATR42–27– 

0104, Revision 01, dated August 30, 

2011. 

• ATR Service Bulletin ATR42–27– 

0105, Revision 01, dated August 30, 

2011. 

• ATR Service Bulletin ATR72–27– 

1065, Revision 02, dated August 30, 

2011. 


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36708 Federal Register / Vol. 80, No. 123 / Friday, June 26, 2015 / Rules and Regulations 

• ATR Service Bulletin ATR72–27– 

1066, Revision 01, dated August 30, 

2011. 

This service information describes 

procedures for the inspection of affected 

control systems rods and, depending on 

findings, a replacement of the affected 

rods. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this AD. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type designs. 

There are no products of this type 

currently registered in the United States; 

however, this rule is necessary to ensure 

that the described unsafe condition is 

addressed if any of these products are 

placed on the U.S. Register in the future. 

Differences Between This AD and the 

MCAI or Service Information 

The actions specified in paragraph (4) 

of the MCAI, for rudder pedals that have 

been inspected according to EASA AD 

2010–0063–E, dated April 1, 2010, is 

not included in this AD because the 

those actions were not required by any 

FAA AD. 

Although the MCAI requires using a 

certain repair manual to repair certain 

conditions, paragraph (i) of this AD 

requires repair using a method approved 

by the Manager, International Branch, 

ANM–116, Transport Airplane 

Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or 

ATR–GIE Avions de Transport 

Re ́gional’s EASA Design Organization 

Approval (DOA). 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–1986; 

Directorate Identifier 2012–NM–100– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

Currently, there are no affected 

airplanes on the U.S. Register. However, 

if an affected airplane is imported and 

placed on the U.S. Register in the future, 

we estimate that it will take about 1 

work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost $0 per product. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$85 per product. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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. 

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 airworthiness 

directive (AD): 

2015–13–01 ATR–GIE Avions de Transport 

Re ́gional: Amendment 39–18188. Docket 


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Federal Register / Vol. 80, No. 123 / Friday, June 26, 2015 / Rules and Regulations 36709 

No. FAA–2015–1986; Directorate 

Identifier 2012–NM–100–AD. 

(a) Effective Date 

This AD becomes effective July 13, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to airplanes specified in 

paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) ATR–GIE Avions de Transport Re ́gional 

Model ATR42–500 airplanes having 

manufacturer serial number (MSN) 671 

through 815 inclusive, except MSN 811. 

(2) ATR–GIE Avions de Transport Re ́gional 

Model ATR72–212A airplanes having MSN 

769 through 914 inclusive, except MSN 826, 

905, 908, and 911. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of nonconformity of certain control rods, which 

could result in failure of the control rods. We 

are issuing this AD to detect and correct 

failure of an affected control rod, which, 

under certain circumstances, could result in 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Elevator Control Rod Inspection 

For airplanes identified in ATR Service 

Bulletin ATR42–27–0105, Revision 01, dated 

August 30, 2011; or ATR72–27–1066, 

Revision 01, dated August 30, 2011; as 

applicable to airplane model: Within 6 

months after the effective date of this AD, 

inspect all four elevator control rods having 

part number (P/N) S27381930–004 and P/N 

S27381831–006 for batch number 

identification, in accordance with the 

Accomplishment Instructions of ATR Service 

Bulletin ATR42–27–0105, Revision 01, dated 

August 30, 2011; or ATR Service Bulletin 

ATR72–27–1066, Revision 01, dated August 

30, 2011, as applicable to airplane model. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection, if the 

batch number can be conclusively 

determined from that review. Replace any 

affected rod, including any rod with an 

unreadable batch number, at the applicable 

time specified in paragraph (g)(1) or (g)(2) of 

this AD, in accordance with ATR Service 

Bulletin ATR42–27–0105, Revision 01, dated 

August 30, 2011; or ATR72–27–1066, 

Revision 01, dated August 30, 2011; as 

applicable to airplane model. 

(1) If only one rod is affected: Replace it 

within 10 days after the inspection. 

(2) If two or more rods are affected: Replace 

all rods before further flight, except that 

replacement of one of the affected rods may 

be deferred for 10 days. 

(h) Rudder Pedal Rod Inspection 

For airplanes identified in ATR Service 

Bulletin ATR42–27–0104, Revision 01, dated 

August 30, 2011; or ATR Service Bulletin 

ATR72–27–1065, Revision 02, dated August 

30, 2011; as applicable to airplane model: 

Inspect all four rudder pedal rods having P/ 

N S2728116400000 for batch number 

identification, in accordance with the 

Accomplishment Instructions of ATR Service 

Bulletin ATR42–27–0104, Revision 01, dated 

August 30, 2011; or ATR Service Bulletin 

ATR72–27–1065, Revision 02, dated August 

30, 2011; as applicable to airplane model. For 

any affected rudder pedal rod, including any 

rod with an unreadable batch number, before 

further flight, check the rod diameter using 

a special tool, in accordance with ATR 

Service Bulletin ATR42–27–0104, Revision 

01, dated August 30, 2011; or ATR Service 

Bulletin ATR72–27–1065, Revision 02, dated 

August 30, 2011; as applicable to airplane 

model. 

(1) If, during the diameter check, the rod 

passes through the tool, replace the rod 

before further flight. 

(2) If, during the diameter check, the rod 

does not pass through the tool, replace the 

rod within 5,000 flight hours after the 

diameter check. 

(i) Rudder Tab Control Rod Inspection 

For airplanes identified in paragraph (c) of 

this AD, except for airplanes having MSNs 

671, 673, and 769 through 784 inclusive: 

Within 24 months after the effective date of 

this AD, inspect the rudder tab control rod 

P/N S27281929–002 for batch number 

identification, using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Avions de Transport Re ́gional 

(ATR)’s EASA Design Organization Approval 

(DOA). If the rudder tab control rod belongs 

to batch number 2107267 or 2120855, or if 

the batch number is unreadable: Before 

further flight, replace the rod with a 

serviceable rod using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or ATR’s EASA DOA. 

Note 1 to paragraph (i) of this AD: ATR 42/ 

72 Aircraft Maintenance Manual (AMM)/Job 

Instruction Cards (JIC) 27–20–00 DVI 1000 

and AMM/JIC 27–21–42 RAI 10000 are 

additional sources of guidance for 

accomplishment of the rudder tab control rod 

inspection. 

(j) Reporting Requirement 

Submit a report of the rod inspection and 

check required by paragraphs (g) and (h) of 

this AD at the applicable compliance time 

specified in paragraph (j)(1) of this AD, in 

accordance with the instructions specified in 

paragraph (j)(2) of this AD. 

(1) Submit the report at the applicable time 

specified in paragraph (j)(1)(i) or (j)(1)(ii) of 

this AD. 

(i) If the inspection or check was done on 

or after the effective date of this AD: Submit 

the report within 30 days after the inspection 

or check. 

(ii) If the inspection or check was done 

before the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(2) Submit the report (including no 

findings) to ATR using the Accomplishment 

Report form provided in the service 

information identified in paragraph (j)(2)(i), 

(j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) of this AD; as 

applicable to airplane model. 

(i) ATR Service Bulletin ATR42–27–0104, 

Revision 01, dated August 30, 2011. 

(ii) ATR Service Bulletin ATR42–27–0105, 

Revision 01, dated August 30, 2011. 

(iii) ATR Service Bulletin ATR72–27–1065, 

Revision 02, dated August 30, 2011. 

(iv) ATR Service Bulletin ATR72–27–1066, 

Revision 01, dated August 30, 2011. 

(3) Send the report to ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email techdesk@atr.fr. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service information specified in 

paragraphs (k)(1) through (k)(5) of this AD. 

These documents are not incorporated by 

reference in this AD. 

(1) ATR Service Bulletin ATR42–27–0104, 

dated December 17, 2010. 

(2) ATR Service Bulletin ATR42–27–0105, 

dated February 17, 2011. 

(3) ATR Service Bulletin ATR72–27–1065, 

dated April 15, 2010. 

(4) ATR Service Bulletin ATR72–27–1065, 

Revision 01, dated December 17, 2010. 

(5) ATR Service Bulletin ATR72–27–1066, 

dated February 17, 2011. 

(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, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or ATR–GIE Avions de Transport 

Re ́gional’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 


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36710 Federal Register / Vol. 80, No. 123 / Friday, June 26, 2015 / Rules and Regulations 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0064, dated 

April 20, 2012, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–1986. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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) ATR Service Bulletin ATR42–27–0104, 

Revision 01, dated August 30, 2011. 

(ii) ATR Service Bulletin ATR42–27–0105, 

Revision 01, dated August 30, 2011. 

(iii) ATR Service Bulletin ATR72–27–1065, 

Revision 02, dated August 30, 2011. 

(iv) ATR Service Bulletin ATR72–27–1066, 

Revision 01, dated August 30, 2011. 

(3) For service information identified in 

this AD, contact ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atr.fr; 

Internet http://www.aerochain.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 June 17, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–15615 Filed 6–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0524; Directorate 

Identifier 2014–NM–042–AD; Amendment 

39–18189; AD 2015–13–02] 

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–8–400 

series airplanes. This AD was prompted 

by reports of corrosion in the low-rate 

discharge tubes of the fire protection 

system leading to the forward baggage 

compartment, and perforation of one or 

more tubes. This AD requires repetitive 

checks for leakage of the discharge tubes 

of the fire protection system. This AD 

also mandates eventual replacement of 

all existing aluminum tube assemblies 

with new, improved corrosion-resistant 

stainless steel tube assemblies. We are 

issuing this AD to prevent perforation of 

the low-rate discharge tubes, which 

could result in insufficient fire 

extinguishing agent reaching the 

forward baggage compartment in the 

event of a fire, which could result in 

damage to the airplane and injury to the 

occupants. 

DATES: This AD becomes effective July 

31, 2015 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 31, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0524 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 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0524. 

FOR FURTHER INFORMATION CONTACT: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7303; 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–8–400 series airplanes. The NPRM 

published in the Federal Register on 

August 13, 2014 (79 FR 47384). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–06, 

dated January 21, 2014 (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: 

Corrosion has been reported in the fire 

protection system low rate discharge tubes 

leading to the forward baggage compartment. 

In some cases, this has led to perforation of 

one or more tubes. 

Perforation of forward baggage 

compartment fire protection system tubes 

may result in decreased effectiveness of the 

fire protection system in the event of a fire 

in the forward baggage compartment. 

This [Canadian] AD mandates a repetitive 

integrity check of the forward baggage 

compartment fire protection system tube 

assemblies, and the replacement of 

aluminum forward baggage compartment fire 

protection tube assemblies with corrosion 

resistant stainless steel (CRES) tubes. 

The unsafe condition is perforation of 

the low-rate discharge tubes, which 

could result in insufficient fire 

extinguishing agent reaching the 

forward baggage compartment and 

reduce the capability of the fire 

protection system to extinguish fires, 

possibly resulting in damage to the 


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