Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules 2783 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8465; Directorate 

Identifier 2014–NM–239–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2001–12– 

18, for certain CASA Model CN–235 

series airplanes. AD 2001–12–18 

currently requires modification of the 

rigging of the engine control cable 

assembly and replacement of either the 

entire engine control cable assembly or 

a segment of the control cables. Since 

we issued AD 2001–12–18, we have 

received reports of new occurrences of 

cable disruption on a certain part 

number; the disruption is caused by 

microcracks along the cable surface. 

This proposed AD would retain the 

requirements of AD 2001–12–18. This 

proposed AD would also require 

repetitive replacements of each power 

lever and condition lever Teleflex cable 

with a new or serviceable part and 

would remove airplanes from the 

applicability. We are proposing this AD 

to prevent fatigue of the engine control 

cables, leading to breakage of the cables, 

which could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 4, 2016. 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed rule, contact EADS– 

CASA, Military Transport Aircraft 

Division (MTAD), Integrated Customer 

Services (ICS), Technical Services, 

Avenida de Arago ́n 404, 28022 Madrid, 

Spain; telephone +34 91 585 55 84; fax 

+34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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. 

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– 

8465; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone 425–227– 

1112; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–8465; Directorate Identifier 

2014–NM–239–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 11, 2001, we issued AD 

2001–12–18, Amendment 39–12274 (66 

FR 33014, June 20, 2001). AD 2001–12– 

18 requires actions intended to address 

an unsafe condition on certain CASA 

Model CN–235 series airplanes. 

Since we issued AD 2001–12–18, 

Amendment 39–12274 (66 FR 33014, 

June 20, 2001), we have received reports 

of new occurrences of cable disruption 

on part number (P/N) 72830–20; the 

disruption is caused by microcracks 

along the cable surface. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0262, dated December 5, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Defense and Space S.A. Model CN–235– 

100 and –200 airplanes. The MCAI 

states: 

Three occurrences of cable disruption were 

reported in 1999. The failed parts, having a 

part number (P/N) 7–44728–20, were part of 

the engine control system assembly P/N 7– 

44728–12. Two cables were connected to the 

Power Lever and one cable to the Condition 

Lever control. Service records of the affected 

parts showed that each cable accumulated 

more than 14,000 flight cycles (FC). 

The subsequent investigation determined 

that the disruption was attributed to fatigue 

related crack. 

This condition, if not corrected, could lead 

to failure of the engine control system 

resulting in a loss of the affected engine 

control. 

Prompted by this unsafe condition, DGAC 

[Direccio ́n General de Aviacio ́n Civil] Spain 

issued AD 03/00 [which corresponds to FAA 

AD 2001–12–18, Amendment 39–12274 (66 

FR 33014, June 20, 2001] to require rigging 

of the throttle stops, and one-time 

replacement of the affected engine control 

cable assembly (P/N 7–44728–12), or the 

affected cable (P/N 7–44728–20) before 

exceeding 12,000 FC. 

After that [DGAC Spain] AD was issued, a 

new occurrence of cable (P/N 72830–20) 

disruption was reported. In that case, the 

affected cable was part of the Condition 

Lever control and had accumulated 8,497 

flight hours (FH) and 8,858 FC. Fractographic 

analysis of the affected cable identified that 

the fatigue nucleation seemed to have been 

induced by microcracks along the cable 

surface. Additionally, another case of control 

cable (P/N 72830–20) failure was reported, 

where the affected part accumulated 9,936 

FH and 10,552 FC and was part of the Power 

Lever control. Investigation of the latter case 

identified again a fatigue nucleation to be the 

cause of the cable failure. 

To address this potentially unsafe 

condition, Airbus Military issued Alert 

Operators Transmission (AOT) AOT–CN235– 

76–0001 to provide a repetitive replacement 

interval and instructions. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

Spain AD No. 03/00, which is superseded, 

but requires repetitive replacement [at 

reduced thresholds] of the affected Teleflex 

cables. 


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2784 Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8465. 

Related Service Information Under 1 

CFR Part 51 

Airbus Defense and Space S.A. has 

issued Airbus Military Alert Operators 

Transmission, dated May 27, 2014. The 

service information describes repetitive 

replacements of each power lever and 

condition lever Teleflex cable with a 

new or serviceable part. 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. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

EASA Airworthiness Directive 2014– 

0262, dated December 5, 2014, specifies 

an applicability for Airbus Defense and 

Space S.A. Model CN–235–100 and 

–200 airplanes, serial numbers C–016 

through C–073. This AD specifies an 

applicability for Model CN–235 

airplanes, serial numbers C–001 through 

C–015 inclusive and serial number C– 

074; and Model CN–235–100 and –200 

airplanes, serial numbers C–016 through 

C–073 inclusive. The retained one-time 

action in paragraph (g) of this proposed 

AD is also applicable to Model CN–235 

airplanes, serial numbers C–001 through 

C–015 inclusive and serial number C– 

074, which are missing from EASA AD 

2014–0262, dated December 5, 2014. We 

understand EASA considered Model 

CN–235 airplanes with these serial 

numbers that have already performed 

this one-time action. For this reason, 

Model CN–235 airplanes, serial 

numbers C–001 through C–015 

inclusive and serial number C–074 are 

added to this proposed AD. This issue 

has been coordinated with EASA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 3 airplanes of U.S. registry. 

The rigging required by AD 2001–12– 

18, Amendment 39–12274 (66 FR 

33014, June 20, 2001), and retained in 

this proposed AD takes about 8 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

rigging required by AD 2001–12–18 is 

$680 per product. 

The replacement required by AD 

2001–12–18, Amendment 39–12274 (66 

FR 33014, June 20, 2001), and retained 

in this proposed AD takes about 47 

work-hours per product, at an average 

labor rate of $85 per work-hour. 

Required parts cost about $1,444 per 

product. Based on these figures, the 

estimated cost of the replacement 

required by AD 2001–12–18 is $5,439 

per product. 

We also estimate that it would take 

about 47 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $6,480 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $31,425, or $10,475 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Airworthiness Directive (AD) 

2001–12–18, Amendment 39–12274 (66 

FR 33014, June 20, 2001) and adding the 

following new AD: 

Airbus Defense and Space S.A. (Formerly 

Known as Construcciones Aeronauticas, 

S.A.): Docket No. FAA–2015–8465; 

Directorate Identifier 2014–NM–239–AD. 

(a) Comments Due Date 

We must receive comments by March 4, 

2016. 

(b) Affected ADs 

This AD replaces AD 2001–12–18, 

Amendment 39–12274 (66 FR 33014, June 

20, 2001). 

(c) Applicability 

This AD applies to Airbus Defense and 

Space S.A. (Formerly Known as 

Construcciones Aeronauticas, S.A.) Model 

CN–235 airplanes, serial numbers C–001 

through C–015, inclusive and serial number 

C–074; and Model CN–235–100 and –200 

airplanes, serial numbers C–001 through C– 

074, inclusive; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 76, Engine Controls. 

(e) Reason 

This AD was prompted by reports of new 

occurrences of cable disruption on a certain 


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Federal Register / Vol. 81, No. 11 / Tuesday, January 19, 2016 / Proposed Rules 2785 

part number; the disruption is caused by 

microcracks along the cable surface. We are 

issuing this AD to prevent fatigue of the 

engine control cables, leading to breakage of 

the cables, which could result in reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Action for the Power Lever and 

Condition Lever Control Stops, With No 

Changes 

This paragraph restates the requirements of 

paragraph (a) of AD 2001–12–18, 

Amendment 39–12274 (66 FR 33014, June 

20, 2001). Within 15 days after July 25, 2001 

(the effective date of AD 2001–12–18): Rig 

the power lever and condition lever control 

stops, in accordance with CASA COM 235– 

140, Revision 01, dated March 21, 2000. 

(h) New Requirement of This AD: 

Replacement 

At the applicable compliance times 

specified in table 1 to paragraph (h) of this 

AD: Replace each power lever and condition 

lever Teleflex cable having part number (P/ 

N) 72830–20 with a new or serviceable part, 

in accordance with Airbus Military Alert 

Operators Transmission AOT–CN235–76– 

0001, dated May 27, 2014. Repeat the 

replacement thereafter at intervals not to 

exceed an accumulation of 5,000 total flight 

cycles on each Teleflex cable having P/N 

72830–20. 

TABLE 1 TO PARAGRAPH (h) OF THIS AD—REPLACEMENT COMPLIANCE TIME

Total flight cycles accumulated on the Teleflex cable having P/N 

72830–20 (since first installation on an airplane) as of the effective 

date of this AD 

Compliance time 

Fewer than 4,700 total flight cycles ......................................................... Before accumulating 5,000 total flight cycles. 

4,700 or more, but fewer than 6,000 total flight cycles ........................... Within 300 flight cycles or 12 months after the effective date of this AD, 

whichever occurs first. 

Equal to or more than 6,000 total flight cycles but fewer than 7,000 

total flight cycles.

Within 200 flight cycles or 6 months after the effective date of this AD, 

whichever occurs first. 

Equal to or more than 7,000 total flight cycles ........................................ Within 100 flight cycles or 3 months after the effective date of this AD, 

whichever occurs first. 

(i) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install, on any airplane, a 

Teleflex cable having P/N 72830–20, unless 

the cable has accumulated fewer than 5,000 

total flight cycles since its first installation on 

an airplane. 

(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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1112; 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 EADS CASA’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 2014–0262, dated 

December 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–2015–8465. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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. 

Issued in Renton, Washington, on 

December 31, 2015. 

Phil Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00377 Filed 1–15–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8464; Directorate 

Identifier 2015–NM–050–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This proposed AD was 

prompted by a revision by the 

manufacturer to the Certification 

Maintenance Requirements (CMR) of the 

Airworthiness Limitation Items (ALI), in 

the Maintenance Requirement Manual 

(MRM), that introduces a new CMR task 

that requires repetitive operational 

checks of the propeller overspeed 

governor. This proposed AD would 

require revising the airplane 

maintenance program or inspection 

program, as applicable, to incorporate a 

new CMR task. We are proposing this 

AD to prevent dormant failure of the 

propeller overspeed governor, which 

may lead to a loss of propeller 

overspeed protection and result in high 

propeller drag in-flight. 

DATES: We must receive comments on 

this proposed AD by March 4, 2016. 


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