81 FR 34876 - Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 105 (June 1, 2016)

We are superseding Airworthiness Directive (AD) 2001-12- 18 for certain CASA Model CN-235 series airplanes. AD 2001-12-18 required 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. This new AD would retain the requirements of AD 2001-12-18. This new AD also requires repetitive replacements of each power lever and condition lever Teleflex cable with a new or serviceable part, and removes airplanes from the applicability. This AD was prompted by reports of new occurrences of cable disruption on a certain 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.

[Federal Register Volume 81, Number 105 (Wednesday, June 1, 2016)]
[Rules and Regulations]
[Pages 34876-34879]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-12594]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8465; Directorate Identifier 2014-NM-239-AD; 
Amendment 39-18535; AD 2016-11-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Defense and Space S.A. (Formerly 
Known as Construcciones Aeronauticas, S.A.)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2001-12-

[[Page 34877]]

18 for certain CASA Model CN-235 series airplanes. AD 2001-12-18 
required 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. This new AD would retain 
the requirements of AD 2001-12-18. This new AD also requires repetitive 
replacements of each power lever and condition lever Teleflex cable 
with a new or serviceable part, and removes airplanes from the 
applicability. This AD was prompted by reports of new occurrences of 
cable disruption on a certain 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.

DATES: This AD is effective July 6, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 6, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
25, 2001 (66 FR 33014, June 20, 2001).

ADDRESSES: For service information identified in this final rule, 
contact EADS-CASA, Military Transport Aircraft Division (MTAD), 
Integrated Customer Services (ICS), Technical Services, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax 
+34 91 585 55 05; email [email protected]; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8465.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2001-12-18, Amendment 39-12274 (66 FR 33014, 
June 20, 2001) (``AD 2001-12-18''). AD 2001-12-18 applied to certain 
CASA Model CN-235 series airplanes. The NPRM published in the Federal 
Register on January 19, 2016 (81 FR 2783) (``the NPRM'').
    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 [Direcci[oacute]n 
General de Aviaci[oacute]n Civil] Spain issued AD 03/00 [which 
corresponds to FAA AD 2001-12-18] 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.

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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Clarification of Applicability

    We have clarified the Applicability in paragraph (c) of this AD. 
For Model CN-235 airplanes, the affected serial numbers (S/N) are C-001 
through C-015 inclusive. We have removed S/N C-074 for Model CN-235 
airplanes because there are no Model CN-235 airplanes with that serial 
number.
    For Model CN-235-100 and -200 airplanes, the affected serial 
numbers are C-016 through C-073 inclusive. We have removed S/Ns C-001 
through C-015 inclusive and C-074 for CN-235-100 and -200 airplanes 
because there are no Model CN-235-100 and -200 with those serial 
numbers.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    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 Under 1 CFR Part 51

    Airbus Defense and Space S.A. has issued Airbus Military Alert 
Operators

[[Page 34878]]

Transmission AOT-CN235-76-0001, dated May 27, 2014. This service 
information describes repetitive replacements of each power lever and 
condition lever Teleflex cable having a certain part number with a new 
or serviceable part. This service information also provides a new life 
limit of 5,000 flight cycles. 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.

Costs of Compliance

    We estimate that this AD affects 3 airplanes of U.S. registry.
    The rigging required by AD 2001-12-18, and retained in this AD 
takes about 8 work-hours per product, at an average labor rate of $85 
per work-hour. Based on these figures, the estimated cost of the 
rigging that was required by AD 2001-12-18 is $680 per product.
    The replacement required by AD 2001-12-18, and retained in this 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 that was 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 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 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 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.

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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:

2016-11-08 Airbus Defense and Space S.A. (formerly known as 
Construcciones Aeronauticas, S.A.): Amendment 39-18535; Docket No. 
FAA-2015-8465; Directorate Identifier 2014-NM-239-AD.

(a) Effective Date

    This AD is effective July 6, 2016.

(b) Affected ADs

    This AD replaces AD 2001-12-18, Amendment 39-12274 (66 FR 33014, 
June 20, 2001) (``AD 2001-12-18'').

(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 Model CN-235-100 and -200 
airplanes, serial numbers C-016 through C-073 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 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. 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              Compliance time
 airplane) as of the effective date of
                this AD
------------------------------------------------------------------------
Fewer than 4,700 total flight cycles...  Before accumulating 5,000 total
                                          flight cycles.
Equal to or more than 4,700 total        Within 300 flight cycles or 12
 flight cycles, but fewer than 6,000      months after the effective
 total flight cycles.                     date of this AD, whichever
                                          occurs first.

[[Page 34879]]

 
Equal to or more than 6,000 total        Within 200 flight cycles or 6
 flight cycles, but fewer than 7,000      months after the effective
 total flight cycles.                     date of this AD, whichever
                                          occurs first.
Equal to or more than 7,000 total        Within 100 flight cycles or 3
 flight cycles.                           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: [email protected]. 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

    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.

(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.
    (3) The following service information was approved for IBR on 
July 6, 2016.
    (i) Airbus Military Alert Operators Transmission AOT-CN235-76-
0001, dated May 27, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
July 25, 2001 (66 FR 33014, June 20, 2001).
    (i) CASA COM 235-140, Revision 01, dated March 21, 2000.
    (ii) Reserved.
    (5) For service information identified in this AD, contact EADS-
CASA, Military Transport Aircraft Division (MTAD), Integrated 
Customer Services (ICS), Technical Services, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; 
fax +34 91 585 55 05; email [email protected]; 
Internet http://www.eads.net.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 20, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12594 Filed 5-31-16; 8:45 am]
 BILLING CODE 4910-13-P