Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 54891 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0298; Directorate 

Identifier 2012–NM–175–AD; Amendment 

39–17522; AD 2013–15–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–-315 airplanes. This AD was prompted 

by reports of dual alternating current 

(AC) generator failure during flight. The 

failure was attributed to wire chafing 

along the wing lower flap shroud. This 

AD requires revising the maintenance 

program to incorporate certain tasks for 

the electrical wiring interconnection 

system inspection program. We are 

issuing this AD to prevent failure of 

both AC generators due to wire chafing, 

which could result in loss of power to 

the anti-icing heaters for the elevator 

horn, engine inlet, and propeller, and 

consequent ice accumulation in these 

areas, which could adversely affect the 

controllability of the airplane. 

DATES: This AD becomes effective 

October 20, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0298; 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 referenced in 

this AD, contact Bombardier, Inc., Q 

Series Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7301; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

NPRM published in the Federal 

Register on April 11, 2013 (78 FR 

21573). The NPRM was prompted by 

reports of dual alternating current (AC) 

generator failure during flight. The 

NPRM proposed to require revising the 

maintenance program to incorporate 

certain tasks for the electrical wiring 

interconnection system inspection 

program. We are issuing this AD to 

prevent failure of both AC generators 

due to wire chafing, which could result 

in loss of power to the anti-icing heaters 

for the elevator horn, engine inlet, and 

propeller, and consequent ice 

accumulation in these areas, which 

could adversely affect the controllability 

of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–25, 

dated August 28, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

MCAI states: 

There have been several reported 

occurrences of dual [alternating current] AC 

Generator failure during flight, resulting in 

the loss of the variable frequency AC System. 

Investigations revealed wire chafing along 

the wing lower flap shroud due to sagging 

wiring harnesses resting on the support 

structure, missing teflon tape at the fairlead 

locations, and missing grommets. Chafed 

wires may lead to arcing, local overheating, 

and AC generator failure. The AC generators 

provide power to the anti-icing heaters, 

including elevator horn heater, engine inlet 

heater and propeller heater. Failure of both 

AC generators would result in the loss of 

these systems and poses a safety concern. 

This [Canadian] AD mandates the 

inspection and rectification of the wiring 

harness installations along the centre wing 

lower flap shroud. 

Required actions include revising the 

maintenance program by incorporating 

electrical wiring interconnection system 

inspection program tasks. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0298- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

Air Line Pilots Association, 

International stated that it supports the 

NPRM (78 FR 21573, April 11, 2013). 

‘‘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, Transport Canada Civil 

Aviation (TCCA), or Bombardier, Inc.’s 

TCCA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

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

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not TCCA-approved, unless TCCA 


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54892 Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 

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. 

Explanation of Changes to This AD 

Paragraph (g) of this AD was revised 

to state that incorporation of tasks into 

the maintenance or inspection program, 

as applicable, must be done in 

accordance with a method approved by 

the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 

FAA; or Transport Canada Civil 

Aviation (TCCA); or Bombardier, Inc.’s 

TCCA DAO. The service information 

previously referenced in paragraph (g) 

of the NPRM (78 FR 21573, April 11, 

2013) is now referenced as guidance 

material in Notes 1, 2, and 3 to 

paragraph (g) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 (78 FR 

21573, April 11, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 21573, 

April 11, 2013). 

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 89 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD to the 

U.S. operators to be $7,565, 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0298; or in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

MCAI, 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 AD: 

2013–15–06 Bombardier, Inc.: Amendment 

39–17522. Docket No. FAA–2013–0298; 

Directorate Identifier 2012–NM–175–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 20, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category, serial numbers 003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by reports of dual 

alternating current (AC) generator failure 

during flight. The failure was attributed to 

wire chafing along the wing lower flap 

shroud. We are issuing this AD to prevent 

failure of both AC generators due to wire 

chafing, which could result in loss of power 

to the anti-icing heaters for the elevator horn, 

engine inlet, and propeller, and consequent 

ice accumulation in these areas, which could 

adversely affect the controllability of the 

airplane. 


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Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 54893 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD: Incorporate tasks for performing a 

general visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components into the airplane 

maintenance or inspection program, as 

applicable, in accordance with a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA. 

Note 1 to paragraph (g) of this AD: For 

Model DHC–8–100 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 100 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 100 Maintenance 

Program Manual PSM 1–8–7, Revision 25, 

dated February 20, 2012, provides guidance 

for revising the maintenance program to 

include general visual inspections of the 

wiring and associated EWIS components. 

This service information is not incorporated 

by reference in this AD. 

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

Model DHC–8–200 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 200 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 200 Maintenance 

Program Manual PSM 1–82–7, Revision 16, 

dated February 20, 2012, provides guidance 

for revising the maintenance program to 

include general visual inspections of the 

wiring and associated EWIS components. 

This service information is not incorporated 

by reference in this AD. 

Note 3 to paragraph (g) of this AD: For 

Model DHC–8–300 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 300 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 300 Bombardier 

Maintenance Program Manual PSM 1–83–7, 

Revision 25, dated February 20, 2012, 

provides guidance for revising the 

maintenance program to include general 

visual inspections of the wiring and 

associated EWIS components. This service 

information is not incorporated by reference 

in this AD. 

(h) Initial Task Compliance Time 

The initial compliance time for the tasks 

incorporated into the maintenance or 

inspection program, as applicable, specified 

in paragraph (g) of this AD, is at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. 

(1) For airplanes with 45,000 total flight 

hours or more as of the effective date of this 

AD: Within 1,000 flight hours after the 

effective date of this AD. 

(2) For airplanes with less than 45,000 total 

flight hours as of the effective date of this 

AD: Within 6,000 flight hours after the 

effective date of this AD, but not to exceed 

46,000 total flight hours. 

(i) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (g) of this AD, no alternative 

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

used, unless the actions and intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–25, dated 

August 28, 2012, 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–2013–0298. 

(2) For service information identified in 

this AD that is not incorporated by reference, 

contact Bombardier, Inc., Q-Series Technical 

Help Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. You may view 

this referenced service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425 227–1221. 

(l) Material Incorporated by Reference 

None 

Issued in Renton, Washington, on July 12, 

2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–21770 Filed 9–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0216; Directorate 

Identifier 2013–SW–045–AD; Amendment 

39–17964; AD 2014–07–04R1] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising 

airworthiness directive (AD) 2014–07– 

04 that published in the Federal 

Register to correct certain errors. AD 

2014–07–04 applied to certain Sikorsky 

Model S–92A helicopters. The range of 

serial numbers in the Applicability 

section and a reference to the service 

information in the Required Actions 

section of the regulatory text are 

incorrect. This document corrects those 

errors. In all other respects, the original 

document remains the same. 

DATES: This final rule is effective 

September 30, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 1, 2014 (79 FR 21385, April 

16, 2014). 

We must receive comments on this 

AD by November 14, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 


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