Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 64053 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, all manufacturer serial numbers 

except those on which Airbus Modification 

22626 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power; and Code 

92. 

(e) Reason 

This AD was prompted by reports of wire 

chafing in the left-hand wing trailing edge. 

We are issuing this AD to prevent wire 

chafing in the trailing edge of the wings, 

which could result in a short circuit in the 

vicinity of the fuel tanks, consequently 

resulting in a potential source of ignition in 

a fuel tank vapor space and consequent fuel 

tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification, With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2005–15–07, with revised 

service information. Within 60 months after 

August 30, 2005 (the effective date of AD 

2005–15–07), install insulator and cable ties 

to the electrical cables of the S routes at the 

gaps in the raceway in the wing trailing edge 

and the wing tip and wing root areas, in 

accordance with Airbus Service Bulletin 

A320–24–1062, Revision 05, dated June 27, 

2002; or the Accomplishment Instructions of 

Airbus Service Bulletin A320–24–1062, 

Revision 07, dated November 28, 2011. As of 

the effective date of this AD, only Airbus 

Service Bulletin A320–24–1062, Revision 07, 

dated November 28, 2011, may be used. 

(h) New Requirement of This AD: 

Modification of Trailing Edges 

Within 60 months after the effective date 

of this AD, modify the trailing edges of both 

wings by accomplishing the actions specified 

in paragraphs (h)(1) and (h)(2) of this AD. 

(1) Install the additional anti-chafing 

protection in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–92–1049, Revision 01, 

dated November 28, 2011. 

(2) Replace the current electrical cable with 

the new standard one in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–92–1052, dated 

December 5, 2007. During the replacement, 

ensure that the anti-chafing protection 

specified in Airbus Service Bulletin A320– 

92–1049, Revision 01, dated November 28, 

2011, as required by paragraph (h)(1) of this 

AD, remains in place. 

(i) New Additional Modification 

For airplanes on which the installation 

specified in Airbus Service Bulletin A320– 

24–1062, Revision 05, dated June 27, 2002, 

has been done: Within 60 months after the 

effective date of this AD, install insulators 

and cable ties, in accordance with 

‘‘Modification—Additional Work (Introduced 

at Revision No. 06)’’ of the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

24–1062, Revision 07, dated November 28, 

2011. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

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

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–24–1062, 

Revision 06, dated June 26, 2007, which is 

not incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–92–1049, dated July 23, 2007, 

which is not incorporated by reference in this 

AD. 

(k) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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: As of the 

effective date of this AD, 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0198, dated 

September 5, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2016–5591. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(4) and (m)(5) of this AD. 

(m) 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. 

(3) The following service information was 

approved for IBR on October 24, 2016. 

(i) Airbus Service Bulletin A320–24–1062, 

Revision 07, dated November 28, 2011. 

(ii) Airbus Service Bulletin A320–92–1049, 

Revision 01, dated November 28, 2011. 

(iii) Airbus Service Bulletin A320–92– 

1052, dated December 5, 2007. (4) For service 

information identified in this AD, contact 

Airbus, Airworthiness Office—EIAS, 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. 

(5) 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. 

(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 Renton, Washington, on 

September 6, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–22191 Filed 9–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4229; Directorate 

Identifier 2015–CE–038–AD; Amendment 

39–18657; AD 2016–19–08] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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 an aviation authority 

of another country to identify and 


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64054 Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as corrosion of the 

elevator control rod and of the elevator 

actuating lever on the control column. 

We are issuing this AD to detect and 

correct corrosion and/or cracking of the 

elevator control rod assemblies and the 

elevator actuating lever, which if not 

detected and corrected, could cause 

these components to fail. This failure 

could result in loss of control. 

DATES: This AD is effective October 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 24, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4229; or in person at Document 

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 Viking Air Limited 

Technical Support, 1959 De Havilland 

Way, Sidney, British Columbia, Canada, 

V8L 5V5; Fax: 250–656–0673; 

telephone: (North America) (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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for Docket No. FAA–2016– 

4229. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, FAA, New 

York Aircraft Certification Office (ACO), 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone: 

(516) 228–7329; fax: (516) 794–5531; 

email: aziz.ahmed@faa.gov. 

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 Viking Air Limited Models 

DHC–2 Mk. I, DHC–2 Mk. II, and DHC– 

2 Mk. III airplanes. The NPRM was 

published in the Federal Register on 

March 3, 2016 (81 FR 11132). The 

NPRM proposed to correct an unsafe 

condition for the specified products and 

was based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. The MCAI states: 

There have been a number of reports of 

corrosion and/or cracking at the elevator 

actuating lever on the control column, in the 

elevator control rod assemblies, and at the 

rod end plug. 

Undetected corrosion and/or cracking of 

the elevator control rod assemblies or 

elevator actuating lever may lead to the 

failure of the components with consequent 

loss of aeroplane control. 

The MCAI requires visually inspecting 

the elevator control rod assemblies, the 

elevator actuating lever on the control 

column, and the control column torque 

tube for corrosion, cracking, and/or 

other damages, and repairing or 

replacing damaged parts. The MCAI also 

requires incorporating revisions into the 

maintenance program and adds a life 

limit to certain elevator control rod 

assemblies. The MCAI can be found in 

the AD docket on the Internet at https:// 

www.regulations.gov/ 

document?D=FAA-2016-4229-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (81 FR 11132, 

March 3, 2016) and the FAA’s response 

to each comment. 

Request To Change Inspection 

Procedure for the Elevator Control Rod 

Roger Braun requested allowance for 

inspecting the elevator control rod 

without removing it from the airplane. 

The commenter stated that even 

though the inspection procedure in 

Viking Air Limited DHC–2 Beaver 

Service Bulletin Number: V2/0005, 

Revision ‘C’, dated July 17, 2015 (SB No. 

V2/0005, Rev. C), requires removing the 

elevator control rod, that doing so is 

excessively invasive and adds an 

increased risk of maintenance errors 

and/or damage to the part over simply 

inspecting it in place. 

We do not agree with the commenter. 

The elevator control rod ends are not 

required to be removed from its 

assembly. Removal of the elevator 

control rod assembly is necessary to do 

the required inspections. Viking Air 

Limited and Transport Canada 

determined that removing the elevator 

control rod assembly is necessary to 

adequately do the inspection, and the 

process of removing the elevator control 

rod assembly does not pose additional 

risk to safety. 

We have not changed the AD based on 

this comment. 

Request To Rename/Revise the 

Airworthiness Limitations Section 

Roger Braun requested to omit the 

requirement to revise the Airworthiness 

Limitation section and instead include 

the repetitive inspection in the final rule 

AD action. The commenter stated that it 

is very hard to find the compliance 

times for the repetitive inspections, 

which are embedded in the temporary 

revisions to be inserted into the 

Airworthiness Limitation section of the 

FAA-approved maintenance program. 

The commenter asked that instead of 

inserting continued airworthiness 

instructions into the manual, why not 

include the language ‘‘repeat inspection 

every 400 flight hours’’ in the AD 

actions? 

We partially agree. We agree that the 

repetitive inspection requirements that 

are embedded in the temporary 

revisions are not clear or easy to 

understand. However, we disagree with 

writing the repetitive inspections into 

the AD because Viking Air Limited 

plans to have all the required 

inspections in their maintenance 

manual rather than dispersed over 

numerous other documents. We have 

determined that revising the 

Airworthiness Limitations section of the 

FAA-approved maintenance program to 

mandate the repetitive inspections is 

acceptable. To clarify the intent of the 

of the Airworthiness Limitations 

section, we have changed the heading of 

that section to Repetitive Inspection in 

order to make the repetitive inspections 

clear. 

We have changed the AD based on 

this comment. 

Request To Allow Minor Surface 

Corrosion 

Roger Braun requested that the final 

rule AD action be changed to include an 

allowance for minor surface corrosion. 

The commenter stated that the 

proposed AD and the related service 

information are vague in delineating 

what corrosion is considered 

unacceptable by stating if ‘‘any 

corrosion’’ is found, which would be an 

unrealistic standard. The commenter 

requested relief for minor surface 

corrosion. 

We do not agree. Viking Air Limited 

and Transport Canada determined that 

all corrosion is unacceptable. Small 

surface corrosion must also be repaired 

following the SB No. V2/0005, Rev. C, 

dated July 17, 2015. 

We have not changed the AD based on 

this comment. 


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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 64055 

Request for Clarification of Life Limit 

for Part Number (P/N) C2FC619A–11 

Roger Braun requested clarification in 

the final rule AD action to clearly state 

that P/N C2FC619A–11 elevator control 

rod is not a life-limited part. 

The commenter stated that it is not 

entirely clear in the proposed AD that 

elevator control rod, P/N C2FC619A–11, 

is not a life-limited part. The commenter 

requested further clarification in the 

final rule AD action specifying that 

there is no life limit on P/N C2FC619A– 

11. 

We agree with the commenter and 

have added a statement in the AD to 

further clarify that the P/N C2CF619A– 

11 elevator control rod has no life limit. 

We have changed the AD based on 

this comment. 

Request To Extend Repetitive 

Inspection Compliance Times 

Roger Braun requested relief for the 

repetitive inspection of the elevator 

control rods with a known date of 

manufacture, for example, 5 or 10 years. 

We infer that the commenter wants 

the repetitive inspections changed from 

every 400 hours time-in-service (which 

is what is specified in the Temporary 

Revisions to the Airworthiness 

Limitations section) to a repetitive 5- 

year inspection. 

We do not agree. Viking Air Limited 

and Transport Canada determined that 

damage can occur at any time. 

Therefore, no threshold is provided that 

will allow a certain period of time 

before the start of the repetitive 

inspection requirement. 

We have not changed the AD based on 

this comment. 

Request To Change Repetitive 

Inspection Compliance Time 

Mark Henshaw requested the 

repetitive inspections be yearly/12- 

month inspections. The commenter 

stated that he operated his airplane 400– 

500 hours per summer season, as most 

operators do. The commenter stated that 

the 400-hour recurring inspection will 

require the operators to remove the 

airplane from service, remove the pilot 

floor panel, pilot side panels, oil cooler 

cowl, side after cowl, unbolt the control 

column bearings and the inboard 

control column mount then remove it, 

pull the elevator control rod out of the 

airplane, and then do the elevator 

control rod inspection. We infer that the 

commenter is making the point that the 

inspection is very labor intensive. The 

commenter stated that this inspection 

would fit nicely into a yearly/12-month 

inspection criteria instead of what 

probably will fall right in the middle of 

their busy season when a 100-hour 

inspection may or may not have been 

scheduled. This inspection will add at 

least 4–6 hours (on a good night) to a 

routine 100-hour inspection. 

The commenter requested an 

alternative of yearly/every 12 months, 

that way all the elevator control rods get 

looked at every year and nobody has to 

stop their airplane right in the middle 

of their busy season for this inspection. 

The commenter stated that there has 

never been a requirement to remove the 

elevator control rod, and does agree that 

doing the inspection is great idea, but 

not every 400 hours. 

We do not agree that yearly/12 month 

inspections are an acceptable level of 

safety to address the unsafe condition. 

The 400-hour inspection should assure 

that any damage will be detected before 

it rises to an unsafe level. Additionally, 

Viking Air Limited informed us that 

there are existing inspections specified 

in the applicable maintenance manuals 

around the same affected area as this AD 

that requires lifting of floor boards. 

We have not changed the AD based on 

this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the 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 (81 FR 

11132, March 3, 2016) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (81 FR 11132, 

March 3, 2016). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Viking Air Limited 

DHC–2 Beaver Service Bulletin Number: 

V2/0005, Revision ‘C’, dated July 17, 

2015; Temporary Revision No.: 2–38, 

dated March 4, 2015, of VIKING PSM 

NO.: 1–2–2, AIRCRAFT: DHC–2 

BEAVER, SERIES: ALL, PUBLICATION: 

MAINTENANCE MANUAL; and 

Temporary Revision No.: 2T–14, dated 

March 4, 2015, of VIKING PSM NO.: 1– 

2T–2, AIRCRAFT: DHC–2 TURBO 

BEAVER, SERIES: ALL, PUBLICATION: 

MAINTENANCE MANUAL. The service 

information describes procedures for 

doing detailed visual inspections of the 

elevator control rod assemblies, the 

elevator actuating lever on the control 

column, and the control column torque 

tube for corrosion, cracking, and/or 

other damages. The service bulletin also 

describes procedures for repairing or 

replacing damaged parts. 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 the AD. 

Costs of Compliance 

We estimate that this AD will affect 

135 products of U.S. registry. We also 

estimate that it will take about 11.5 

work-hours per product to comply with 

the basic inspection requirements of this 

AD. The average labor rate is $85 per 

work-hour. 

Based on these figures, we estimate 

the cost of the basic inspection 

requirements of this AD on U.S. 

operators to be $131,962.50, or $977.50 

per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 8 work-hours and require parts 

costing $1,859, for a cost of $2,539 per 

product. Contact Viking Air Limited at 

the address identified in the ADDRESSES

section of this AD for current pricing 

and lead time. We have no way of 

determining the number of products 

that may need these actions. 

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 


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64056 Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 

responsibilities among the various 

levels of government. 

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 by searching for 

and locating Docket No. FAA–2016– 

4229; 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 adding 

the following new AD: 

2016–19–08 Viking Air Limited: 

Amendment 39–18657; Docket No. 

FAA–2016–4229; Directorate Identifier 

2015–CE–038–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 24, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Viking Air Limited 

Models DHC–2 Mk. I, DHC–2 Mk. II, and 

DHC–2 Mk. III airplanes, 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 corrosion of 

the elevator control rod and of the elevator 

actuating lever on the control column. We are 

issuing this AD to detect and correct 

corrosion and/or cracking of the elevator 

control rod assemblies and the elevator 

actuating lever, which if not detected and 

corrected, could cause these components to 

fail. This failure could result in loss of 

control. 

(f) Actions and Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (l) of this AD, including all 

subparagraphs, unless already done. 

(g) Initial Inspections 

Within the next 120 days after October 24, 

2016 (the effective date of this AD) or within 

the next 100 hours time-in-service (TIS) after 

October 24, 2016 (the effective date of this 

AD), whichever occurs first, do the following 

inspections in accordance with section I. 

PLANNING INFORMATION, paragraph D. of 

Viking DHC–2 Beaver Service Bulletin 

Number: V2/0005, Revision ‘‘C’’, dated July 

17, 2015: 

(1) For airplanes with an installed elevator 

control rod assembly, part number (P/N) 

C2CF619A, do a detailed visual inspection of 

P/N C2CF619A for corrosion, cracking, and/ 

or other damages. 

(2) For airplanes with an installed elevator 

control rod assembly, P/N CT2CF1021–1, do 

a detailed visual inspection of P/N 

CT2CF1021–1 for corrosion, cracking, and/or 

other damages. 

(3) For all airplanes, do a detailed visual 

inspection of the elevator actuating lever on 

the control column and the control column 

torque tube for corrosion, cracking and/or 

other damages. 

(h) Repetitive Inspections (Airworthiness 

Limitations) 

Within the next 30 days after October 24, 

2016 (the effective date of this AD), insert the 

following into the Airworthiness Limitations 

section of the FAA-approved maintenance 

program (e.g., maintenance manual). This 

revision to the Limitations section 

incorporates repetitive inspections of the 

elevator control rod assemblies, the elevator 

actuating lever, and the control column 

torque tube for corrosion, cracks, and/or 

other damage. Insert item 20A., of Part 3, in 

Appendix 2 of Temporary Revision No.: 2– 

38, dated March 4, 2015, into the VIKING 

PSM NO.: 1–2–2, AIRCRAFT: DHC–2 

BEAVER, SERIES: ALL, PUBLICATION: 

MAINTENANCE MANUAL; and Insert item 

20A., in Part 4, of Temporary Revision No.: 

2T–14, dated March 4, 2015, into VIKING 

PSM NO.: 1–2T–2, AIRCRAFT: DHC–2 

TURBO BEAVER, SERIES: ALL, 

PUBLICATION: MAINTENANCE MANUAL. 

(i) Replacement/Repair for P/N C2CF619A 

(1) Before further flight after the inspection 

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

corrosion, cracking, or other damages are 

found, replace P/N C2CF619A with P/N 

C2CF619A–11 following section I. 

PLANNING INFORMATION, paragraph D. of 

Viking DHC–2 Beaver Service Bulletin 

Number: V2/0005, Revision ‘‘C’’, dated July 

17, 2015, or contact Viking Air Limited at the 

address specified in paragraph (o) of this AD 

for an FAA-approved repair and incorporate 

the repair. 

(2) Within the next 120 days after October 

24, 2016 (the effective date of this AD) or 

within the next 100 hours TIS after October 

24, 2016 (the effective date of this AD), 

whichever occurs first, you may replace P/N 

C2CF619A with P/N C2CF619A–11 instead 

of doing the inspection required in paragraph 

(g)(1) of this AD. Do the replacement 

following section I. PLANNING 

INFORMATION, paragraph D. of Viking 

DHC–2 Beaver Service Bulletin Number: V2/ 

0005, Revision ‘‘C’’, dated July 17, 2015. 

(3) After replacing P/N C2CF619A with P/ 

N C2CF619A–11, you must still do the 

repetitive inspections of the elevator control 

rod assemblies following the Airworthiness 

Limitations section of the FAA-approved 

maintenance program (e.g., maintenance 

manual) specified in paragraph (k)(1) of this 

AD. 

(j) Replacement/Repair for P/N CT2CF1021– 

1 

(1) Before further flight after the inspection 

required in paragraph (g)(2) of this AD, if 

corrosion, cracking, or other damages are 

found, replace the elevator control rod 

assembly with P/N CT2CF1021–1 that has 

been inspected and is free of corrosion, 

cracking, or other damages following section 

I. PLANNING INFORMATION, paragraph D. 

of Viking DHC–2 Beaver Service Bulletin 

Number: V2/0005, Revision ‘‘C’’, dated July 

17, 2015, or contact Viking Air Limited at the 

address specified in paragraph (o) of this AD 

for an FAA-approved repair and incorporate 

the repair. 

(2) After replacing or repairing P/N 

CT2CF1021–1, you must still do the 

repetitive inspections of the elevator control 

rod assemblies following the Airworthiness 

Limitations section of the FAA-approved 

maintenance program (e.g., maintenance 

manual) specified in paragraph (k)(1) of this 

AD. 

(k) Repair of the Elevator Actuating Lever 

Before further flight after the inspection 

required in paragraph (g)(3) of this AD, if 

corrosion, cracking, or other damages are 

found, contact Viking Air Limited at the 

address specified in paragraph (o) of this AD 

for an FAA-approved repair and incorporate 

the repair. 

(l) Restrictions 

As of October 24, 2016 (the effective date 

of this AD), do not install P/N C2CF619A or 

C2CF619A–9 as a replacement part. 


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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations 64057 

(m) Life Limit for P/N C2CF619A 

As of October 24, 2016 (the effective date 

of this AD), elevator control rod assemblies, 

P/N C2CF619A, are life-limited to 15 years 

and must be replaced with P/N C2CF619A– 

11, which is not a life-limited part, at the 

following compliance time: 

(1) If, as of October 24, 2016 (the effective 

date of this AD), the age of the installed P/ 

N C2CF619A is known, it must be replaced 

before exceeding the life limit or within the 

next 12 months after October 24, 2016 (the 

effective date of this AD), whichever occurs 

later. 

(2) If, as of October 24, 2016 (the effective 

date of this AD), the age of the installed P/ 

N C2CF619A is not known, it must be 

replaced within the next 12 months after 

October 24, 2016 (the effective date of this 

AD). 

(n) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Credit will be given for the inspections 

required in paragraphs (g)(1) through (3) of 

this AD if they were done before October 24, 

2016 (the effective date of this AD) following 

Viking Air Limited DHC–2 Beaver Service 

Bulletin Number: V2/0005, Revision ‘NC’, 

dated March 26, 2012; Viking Air Limited 

DHC–2 Beaver Service Bulletin Number: V2/ 

0005, Revision ‘A’, dated November 7, 2014; 

or Viking Air Limited DHC–2 Beaver Service 

Bulletin Number: V2/0005, Revision ‘B’, 

dated March 4, 2015. 

(o) 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), 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: Aziz 

Ahmed, Aerospace Engineer, FAA, New York 

ACO, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone: (516) 

228–7329; fax: (516) 794–5531; email: 

aziz.ahmed@faa.gov. Before using any 

approved AMOC on any airplane 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. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, 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. 

(p) Related Information 

Refer to MCAI Transport Canada AD No. 

CF–2015–21, dated July 30, 2015; and Viking 

Air Limited DHC–2 Beaver Service Bulletin 

Number: V2/0005, Revision ‘NC’, dated 

March 26, 2012; Viking Air Limited DHC–2 

Beaver Service Bulletin Number: V2/0005, 

Revision ‘A’, dated November 7, 2014; or 

Viking Air Limited DHC–2 Beaver Service 

Bulletin Number: V2/0005, Revision ‘B’, 

dated March 4, 2015, for related information. 

You may examine the MCAI on the Internet 

at https://www.regulations.gov/ 

document?D=FAA-2016-4229-0002. 

(q) 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. 

(i) Viking DHC–2 Beaver Service Bulletin 

Number: V2/0005, Revision ‘‘C’’, dated July 

17, 2015. 

(ii) Item 20A., of Part 3, in Appendix 2 of 

Temporary Revision No.: 2–38, dated March 

4, 2015, into the VIKING PSM NO.: 1–2–2, 

AIRCRAFT: DHC–2 BEAVER, SERIES: ALL, 

PUBLICATION: MAINTENANCE MANUAL. 

(iii) Item 20A., in Part 4, of Temporary 

Revision No.: 2T–14, dated March 4, 2015, 

into VIKING PSM NO.: 1–2T–2, AIRCRAFT: 

DHC–2 TURBO BEAVER, SERIES: ALL, 

PUBLICATION: MAINTENANCE MANUAL. 

(3) For Viking Air Limited 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) (800) 663–8444; 

email: technical.support@vikingair.com; 

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

service-bulletins. 

(4) You may view this 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–2016–4229. 

(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 

September 8, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–22183 Filed 9–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5035; Directorate 

Identifier 2015–NM–042–AD; Amendment 

39–18650; AD 2016–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F28 Mark 

0070 and Mark 0100 airplanes. This AD 

was prompted by reports of cracking in 

a certain area of the pressure bulkhead 

webplate and skin connection angle. 

This AD requires a one-time inspection 

of the affected pressure bulkhead 

webplate and skin connection angle, 

and corrective actions if necessary. We 

are issuing this AD to detect and correct 

cracking of the pressure bulkhead 

webplate and skin connection angle that 

could lead to sudden inflight 

decompression of the airplane, resulting 

in injury to occupants. 

DATES: This AD is effective October 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone 

+31 (0)88–6280–350; fax +31 (0)88– 

6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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–2016– 

5035. 


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