Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 51083 

(3) Task 55–21–27–960–802 of the 

Canadair Regional Jet Model CL–600–2B19 

Aircraft Maintenance Manual, CSP A–001, 

Revision 49, dated May 10, 2014. 

(j) 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) 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–04, dated 

January 13, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2014-0175- 

0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(l) 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 601R–55– 

008, Revision B, dated March 12, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

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/ibr-locations.html. 

Issued in Renton, Washington, on August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19976 Filed 8–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0236; Directorate 

Identifier 2013–NM–184–AD; Amendment 

39–17937; AD 2014–16–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 series airplanes. 

This AD was prompted by our 

determination of the need to incorporate 

new life limits for the main landing gear 

(MLG) barrel assembly, retraction 

actuator assembly linkage, and flange 

duct. This AD requires revising the 

maintenance or inspection program, as 

applicable, to include the new life 

limits. We are issuing this AD to prevent 

reduced structural integrity of the 

airplane and possible loss of 

controllability of the airplane. 

DATES: This AD becomes effective 

October 1, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0236 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 Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM 116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

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 all Airbus Model A300 series 

airplanes. The NPRM published in the 

Federal Register on April 17, 2014 (79 

FR 21651). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0210, 

dated September 11, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

all Airbus Model A300 series airplanes. 

The MCAI states: 

Some life limits previously defined in 

Revision 00 of A300 ALS [airworthiness 

limitations section] Part 1 have been removed 

[from] that document at Revision 01 and 

should normally be included in an ALS Part 

4. 

At this time, there are no plans to issue an 

ALS Part 4 for A300 aeroplanes. 

Nevertheless, failure to comply with these 

life limits could result in an unsafe 

condition. 

For the reasons described above, it has 

been decided to require the application of 

these life limits through a separate [EASA] 

AD. Consequently, this [EASA] AD requires 

application of life limits applicable to Main 

Landing Gear (MLG) barrel assembly, 

retraction actuator assembly linkage 

assembly and flanged duct which were 

previously contained in Airbus ALS Part 1 

Revision 00. 

EASA AD 2007–0293 [which corresponds 

with FAA AD 2009–18–15, Amendment 39– 

16011 (74 FR 48143, September 22, 2009)], 

which required compliance with the actions 

specified in ALS Part 1, will be superseded 

by a new [EASA] AD, requiring compliance 

with ALS Part 1 at Revision 1. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2014-0236-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

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51084 Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 

received no comments on the NPRM (79 

FR 21651, April 17, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

21651, April 17, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 21651, 

April 17, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 7 

airplanes of U.S. registry. 

We also estimate that it takes about 1 

work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work hour. 

Based on these figures, we estimate the 

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

$595, or $85 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-2014-0236; 

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. 

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Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 51085 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–16–13 Airbus: Amendment 39–17937. 

Docket No. FAA–2014–0236; Directorate 

Identifier 2013–NM–184–AD. 

(a) Effective Date 

This AD becomes effective October 1, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A300 

B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 

103, and B4–203 airplanes, certificated in 

any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear; and 36, 

Pneumatic. 

(e) Reason 

This AD was prompted by our 

determination of the need to incorporate new 

life limits for the main landing gear (MLG) 

barrel assembly, retraction actuator assembly 

linkage, and flange duct. We are issuing this 

AD to prevent reduced structural integrity of 

the airplane and possible loss of 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revise the Maintenance or Inspection 

Program 

Within 90 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the life 

limits specified in Appendix 1 of this AD 

into the Airbus A300 Airworthiness 

Limitations Section (ALS) Part 1. The initial 

compliance time for the replacement is 

identified in Appendix 1 of this AD and is 

prior to the applicable life limits specified in 

Appendix 1 of this AD, or within 90 days 

after the effective date of this AD, whichever 

occurs later. 

(h) No Alternative Actions and Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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 Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0210, dated September 11, 

2013, for related information. This MCAI 

may be found in the AD docket on the 

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

!documentDetailD=FAA-2014-0236-0002. 

(k) Material Incorporated by Reference 

None. 

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Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction A

Linkage, and Flange Duct 

(*) Whichever occurs first. LIFE LIMITS (*) LIFE LIMITS APPLICABILIT

Notes are located under the assy title. 

Part Number FH LOG Cal. B2-1A B2K-3C 82-320 B4-2C 

B2-1C B2-20x B4-1xx 

ATA32-10-00 MAIN LANDING GEAR 

BARREL ASSEMBLY 

Stirrup C66277-10 N/A 66600 N/A X X 

C66277-12 N/A 76600 N/A X X C66277-14 N/A 76600 N/A X X 

058303-1 N/A 76600 N/A X X 

Stirrup pin C66457 N/A 76600 N/A X X 

048939 N/A 76600 N/A X X 

048939-1 N/A 76600 N/A X X 058314-1 N/A 76600 N/A X X 

Universal joint C66279 N/A 76600 N/A X X 

C66279-2 N/A 76600 N/A X X C66279-6 N/A 76600 N/A X X 

058313-1 N/A 76600 N/A X X 

Plate (Upper end) C61637-10 N/A 76600 N/A X X 

C61637-11 N/A 76600 N/A X X C61637-12 N/A 76600 N/A X X 

Plate (Rear head end) C61638-10 N/A 53300 N/A X X 

C61638-11 N/A 53300 N/A X X C61638-20 N/A 76600 N/A X X 

Tie rod C68523-3 N/A 76600 N/A X X 

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Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction Ac

Linkage, and Flange Duct (continued) 

(*) Whichever occurs first. LIFE LIMITS (*) LIFE LIMITS APPLICABILIT

Notes are located under the assy title. 

Part Number FH LDG Cal. B2-1A B2K-3C 82-320 B4-2C 

B2-1C B2-20x B4-1xx 

RETRACTION ACTUATOR ASSEMBLY 

(1) When SB A300-32-0123 embodied before SB A300-32-0113. 

(2) When SB A300-32-0123 embodied after SB A300-32-0113. 

Sliding rod C69028-1 N/A 34 000 N/A X X 

C69028-4 N/A 34 000 N/A X X 

C69029-1 (1) N/A 32 000 N/A X X 

C69029-2 N/A 32 000 N/A X X C69029-3 N/A 32 000 N/A X X 

C69029-4 (2) N/A 22 000 N/A X X 

Piston C67078 N/A 33 000 N/A X X 

C67078-1 N/A 33 000 N/A X X 

End fitting C61342-4 N/A 36 700 N/A X X 

C66510-4 N/A 32 000 N/A X X 

LINKAGE ASSEMBLY 

Upper multiple link pin C61505 N/A 76 600 N/A X X 

(Multiple link/Upper C61505-1 N/A 76 600 N/A X X 

link) C61505-20 N/A 76 600 N/A X X 

ATA36-11-05 PNEUMATIC 

(1) "xx" at the end of the P/N stands for any number between 00 and 99. 

Duct flanged ( 1 ) A2127 4063000xx N/A 24 000 N/A X X X 
51088 Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 

Issued in Renton, Washington, on August 

4, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19708 Filed 8–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0616; Directorate 

Identifier 2014–CE–018–AD; Amendment 

39–17954; AD 2014–17–01] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Viking 

Air Limited Model DHC–3 airplanes. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by the aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as looseness of the 

horizontal stabilizer actuator mounting 

block in the forward-aft and side-to-side 

directions. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective September 

16, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 16, 2014. 

We must receive comments on this 

AD by October 14, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Viking Air Limited 

Technical Support, 1959 De Havilland 

Way, Sidney, British Columbia, Canada, 

V8L 5V5; Fax: 250–656–0673; 

telephone: (North America) 1–800–663– 

8444; email: technical.support@

vikingair.com; Internet: http://www.

vikingair.com/content.aspx?id=358. You 

may view 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. 

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–2014– 

0616; 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 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: 

Cesar Gomez, Aerospace Safety Enginer, 

FAA, New York Aircraft Certification 

Office, 1600 Steward Avenue, Suite 410, 

Westbury, New York 11590; telephone: 

(516) 228–7318; fax: (516) 794–5531; 

email: cesar.gomez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada, which is the 

aviation authority for Canada, has 

issued AD No. CF–2014–14, dated June 

5, 2014 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for Viking Air Limited Model DHC–3 

airplanes. The MCAI states: 

A horizontal stabilizer actuator (trim jack) 

mounting block, part number C3FS79–5, was 

found loose in the forward-aft and side-toside directions. The trim jack mounting block 

fastens the stabilizer actuator (trim jack) 

which allows the angle of incidence of the 

stabilizer to be varied. The stabilizer actuator 

(trim jack) also functions as the rear 

mounting point for the stabilizer. 

Failure of the mounting block through 

breakage or detachment may cause loss of 

control of the horizontal stabilizer and 

subsequent loss of control of the aeroplane. 

Therefore, this AD mandates a one-time 

inspection of the stabilizer actuator (trim 

jack) mounting block. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0616. 

Relevant Service Information 

Viking Air Limited has issued Viking 

Service Bulletin No. V3/0005, Revision 

‘A’, dated May 27, 2014. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Interim Action 

We consider this AD interim action. 

After the State of Design reviews and 

evaluates the reporting data, we may 

take further rulemaking action in the 

future. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because failure of the mounting 

block through breakage or detachment 

may cause loss of control of horizontal 

stabilizer and subsequent loss of 

control. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

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–2014–0616; 

Directorate Identifier 2014–CE–018– 

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 

mstockstill on DSK4VPTVN1PROD with RULES