Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 4769 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Costruzioni Aeronautiche TECNAM 

Service Bulletin No. SB 170–CS–Ed 1, Rev 1, 

dated September 25, 2014. 

(ii) Reserved. 

(3) For Costruzioni Aeronautiche TECNAM 

service information identified in this AD, 

contact Costruzioni Aeronautiche Tecnam 

Airworthiness Office, Via Maiorise–81043 

Capua (CE) Italy; telephone: +39 0823 

997538; fax: +39 0823 622899; email: 

technical.support@tecnam.com; Internet: 

http://www.tecnam.com/Customer-Care/

Service-Bulletins.aspx. 

(4) You may review this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. In addition, you can access 

this service information on the Internet at 

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

and locating Docket No. FAA–2014–0876. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Kansas City, Missouri, on January 

14, 2015. 

Kelly A. Broadway, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00992 Filed 1–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0230; Directorate 

Identifier 2013–NM–242–AD; Amendment 

39–18070; AD 2015–02–03] 

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 certain 

Airbus Model A300 B4–601, B4–603, 

B4–605R, F4–605R, and C4–605R 

Variant F airplanes. This AD was 

prompted by reports of cracking found 

in the pylon box, which was due to the 

stresses resulting from the pressure 

applied by the thrust reverser cowl 

bumpers. This AD requires repetitive 

high frequency eddy current (HFEC) 

inspections for cracking; and 

replacement of all fittings if necessary, 

which terminates the repetitive HFEC 

inspections for the modified side only. 

We are issuing this AD to detect and 

correct cracks of the pylon rib 5, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

March 5, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 5, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0230; 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, 

Washington 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 certain Airbus Model A300 B4– 

601, B4–603, B4–605R, F4–605R, and 

C4–605R Variant F airplanes. The 

NPRM published in the Federal 

Register on April 14, 2014 (79 FR 

20837). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0286R1, dated June 6, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A300 B4–601, B4–603, B4–605R, 

F4–605R, and C4–605R Variant F 

airplanes. The MCAI states: 

Cracks were found on the lower side of rib 

5 in the pylon box on A300 aeroplanes 

powered with General Electric engines. 

Investigations revealed that these cracks 

were due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

Airbus developed an inspection 

programme to detect the cracks and 

associated actions to correct them. 

For the reasons described above, EASA 

issued AD 2013–0286 [http://

ad.easa.europa.eu/blob/easa_ad_2013_0286_

R1.pdf/AD_2013-0286R1_2] to require 

repetitive [HFEC] inspections of the pylon rib 

5 on the left hand side (LH) and right hand 

(RH) side and, when cracks are detected, 

replacement of the affected structural part(s). 

[Replacement of all fittings terminates the 

repetitive HFEC inspections.] 

Since that [EASA] AD was issued, it was 

found that the [EASA] AD has inadvertently 

been made applicable to all A300–600 

Models, which is incorrect. This [EASA] AD 

has been revised to reduce the Applicability 

to only the affected Models. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0230- 

0004. 

Revision to Applicability 

Since the NPRM (79 FR 20837, April 

14, 2014), was issued, we have 

determined that paragraph (c), 

‘‘Applicability,’’ of this AD should not 

include Airbus Model A300 B4–620, 

B4–622, B4–622R, and F4–622R 

airplanes. We have removed these 

airplanes from paragraph (c) of this AD, 

and have revised the SUMMARY section 

and Costs of Compliance section of this 

final rule accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 20837, 

April 14, 2014) and the FAA’s response 

to each comment. 

Request for Credit for Modification 

FedEx requested that we revise 

paragraph (i) of the NPRM (79 FR 20837, 

April 14, 2014) to indicate that prior 

incorporation of the modification 

specified in Airbus Service Bulletin 

A300–54–6031, dated May 30, 1996, 

provides credit as a terminating action 

for the repetitive HFEC inspections 

specified in the NPRM. 

We find that clarification is necessary. 

Paragraph (h) of this AD already 

specifies that accomplishment of the 


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4770 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 

referenced modification is terminating 

action for the repetitive HFEC 

inspections required by paragraph (g)(1) 

of this AD for the modified side only. 

We have made no change to this AD in 

this regard. 

Request for Clarification 

UPS requested that we revise 

paragraphs (g)(2) and (h) of the NPRM 

(79 FR 20837, April 14, 2014) to clarify 

that replacement of fittings is to be done 

on the affected pylon or on the modified 

side only. UPS reasoned that one 

interpretation of the phrase ‘‘all the 

fittings’’ would be to replace the fittings 

in the left and right pylons, even though 

cracking was found in only one of the 

pylons. 

We agree to clarify. We have revised 

paragraphs (g)(2) and (h) of this AD to 

include the clarifications requested by 

the commenter. 

‘‘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 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. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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 

20837, April 14, 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 20837, 

April 14, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information 

We reviewed Airbus Service Bulletin 

A300–54–6031, dated May 30, 1996; 

and Airbus Service Bulletin A300–54– 

6034, Revision 02, dated August 26, 

2013. The service information describes 

procedures for repetitive HFEC 

inspections for cracking of the lower 

side of rib 5 in the LH and RH pylon box 

and replacing certain fittings. You can 

find this information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0230. 

Costs of Compliance 

We estimate that this AD affects 54 

airplanes of U.S. registry. 

We also estimate that it will take 

about 9 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

$0 per product. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $41,310, or $765 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 32 work-hours and require parts 

costing $2,450, for a cost of $5,170 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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; 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 4771 

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-2014-0230; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2015–02–03 Airbus: Amendment 39–18070. 

Docket No. FAA–2014–0230; Directorate 

Identifier 2013–NM–242–AD. 

(a) Effective Date 

This AD becomes effective March 5, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–605R, F4–605R, and C4– 

605R Variant F airplanes, certificated in any 

category, all manufacturer serial numbers, 

except those on which Airbus Modification 

11110 has been embodied in production, or 

that have been modified in service as 

specified in Airbus Service Bulletin A300– 

54–6031, dated May 30, 1996. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Reason 

This AD was prompted by reports of 

cracking found in the pylon box, which was 

due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. We are issuing this AD to detect 

and correct cracks of the pylon rib 5, which 

could result in reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Replacement 

(1) Before the accumulation of 15,000 total 

flight hours since the airplane’s first flight, or 

within 6,000 flight hours after the effective 

date of this AD, whichever occurs later: Do 

a high frequency eddy current (HFEC) 

inspection for cracking on the lower area of 

rib 5 on the left-hand and right-hand side 

pylons, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–54–6034, Revision 02, 

dated August 26, 2013. Repeat the inspection 

thereafter at intervals not to exceed 15,000 

flight hours. 

(2) If any crack is found during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace all the 

fittings—on the affected pylon only—with 

new standard fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–54–6031, dated May 

30, 1996. 

(h) Terminating Action 

Replacement of all fittings as required by 

paragraph (g)(2) of this AD; or modification 

of pylons in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–54–6031, dated May 

30, 1996; terminates the repetitive HFEC 

inspections required by paragraph (g)(1) of 

this AD for the modified side only. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

inspections required by paragraph (g)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A300–54–6034, 

Revision 01, dated September 14, 1999, 

which is not incorporated by reference in this 

AD. 

(j) 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, Washington 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0286R1, dated 

June 6, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0230-0004. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available 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) Airbus Service Bulletin A300–54–6031, 

dated May 30, 1996. 

(ii) Airbus Service Bulletin A300–54–6034, 

Revision 02, dated August 26, 2013. 

(3) 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. 

(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. 


tkelley on DSK3SPTVN1PROD with RULES
4772 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 

Issued in Renton, Washington, on January 

12, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00997 Filed 1–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0096; Directorate 

Identifier 2014–CE–040–AD; Amendment 

39–18077; AD 2015–02–10] 

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 Models DHC–2 Mk. I, DHC– 

2 Mk. II, and DHC–2 Mk. III 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 failed locknuts 

on the horizontal stabilizer attach 

bracket. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective February 18, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 18, 2015. 

We must receive comments on this 

AD by March 16, 2015. 

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/support/servicebulletins. 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–2015– 

0096; 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: Aziz 

Ahmed, Aerospace Safety Engineer, 

FAA, New York Aircraft Certification 

Office (ACO), 1600 Steward Avenue, 

Suite 410, Westbury, New York 11590; 

telephone: (516) 228–7329; fax: (516) 

794–5531; email: aziz.ahmed@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada, which is the 

aviation authority for Canada, has 

issued AD No. CF–2014–38, dated 

October 20, 2014 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for Viking Air Limited Models 

DHC–2 Mk. I, DHC–2 Mk. II, and DHC– 

2 Mk. III airplanes. The MCAI states: 

There has been an in-service report of 

failed MS21042 locknuts on the horizontal 

stabilizer attach bracket of a DHC–2 Mk. I 

aeroplane. Laboratory examinations of these 

nuts found intergranular fractures typical of 

hydrogen embrittlement possibly due to the 

introduction of hydrogen during the 

manufacturing process. 

Failure of these nuts could result in 

detachment of the horizontal stabilizer and 

loss of control of the aeroplane. 

This AD mandates the inspection and 

replacement, of the horizontal stabilizer 

attach bracket MS21042 locknuts. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0096. 

Relevant Service Information 

Viking Air Limited has issued Viking 

Alert Service Bulletin No. V2/0007, 

Revision ‘NC’, dated April 29, 2013. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. The service bulletin describes 

procedures to inspect and replace the 

horizontal stabilizer attach bracket 

locknuts. You can find this service 

information on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0096. 

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. 

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 any locknut on 

the horizontal stabilizer attach bracket 

could result in detachment of the 

horizontal stabilizer and consequent 

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–2015–0096; 

Directorate Identifier 2014–CE–040– 

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 


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