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)

Page Range		34876-34879
FR Document		2016-12594

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 Issue 105 (Wednesday, June 1, 2016)

[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.

-----------------------------------------------------------------------

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

34876 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

Service Bulletin 737–53A1279, Revision 2, flight, repair using a method approved in (w) Material Incorporated by Reference
dated April 21, 2015: Except as required by accordance with the procedures specified in (1) The Director of the Federal Register
paragraph (t)(1) of this AD, at the applicable paragraph (u) of this AD. approved the incorporation by reference
time specified in table 3 of paragraph 1.E., (IBR) of the service information listed in this
‘‘Compliance,’’ of Boeing Alert Service (t) New Requirement of This AD: Exceptions
to Service Bulletin Specifications paragraph under 5 U.S.C. 552(a) and 1 CFR
Bulletin 737–53A1279, Revision 2, dated part 51.
April 21, 2015, do HFEC, LFEC, and detailed (1) Where paragraph 1.E., ‘‘Compliance,’’ of (2) You must use this service information
inspections for cracking in accordance with Boeing Alert Service Bulletin 737–53A1279, as applicable to do the actions required by
‘‘Part 7—INSPECTION OF PREVENTATIVE Revision 2, dated April 21, 2015, refers to a this AD, unless the AD specifies otherwise.
MODIFICATION’’ of the Accomplishment compliance time ‘‘after the Revision 2 date of (3) The following service information was
Instructions of Boeing Alert Service Bulletin this service bulletin,’’ this AD requires approved for IBR on July 6, 2016.
737–53A1279, Revision 2, dated April 21, compliance within the specified compliance (i) Boeing Alert Service Bulletin 737–
2015. Repeat the inspections thereafter at the time after the effective date of this AD. 53A1279, Revision 2, dated April 21, 2015.
applicable interval specified in paragraph (2) The ‘‘Condition’’ column in table 1 and (ii) Reserved.
1.E., ‘‘Compliance,’’ of Boeing Alert Service table 2 of paragraph 1.E., ‘‘Compliance,’’ of (4) The following service information was
Bulletin 737–53A1279, Revision 2, dated Boeing Alert Service Bulletin 737–53A1279, approved for IBR on November 16, 2011 (76
April 21, 2015. If any cracking is found Revision 2, dated April 21, 2015, refers to FR 67343, November 1, 2011).
during any inspection required by this total flight cycles ‘‘at the Revision 2 date of (i) Boeing Alert Service Bulletin 737–
paragraph, before further flight, repair using this service bulletin.’’ However, this AD 53A1279, Revision 1, dated September 2,
a method approved in accordance with the applies to the airplanes with the specified 2011.
procedures specified in paragraph (u) of this total flight cycles as of the effective date of (ii) Reserved.
AD. (5) For Boeing service information
this AD.
identified in this AD, contact Boeing
(r) New Requirement of This AD: Inspections (u) Alternative Methods of Compliance Commercial Airplanes, Attention: Data &
of Preventive Modification for Groups 1–6, (AMOCs) Services Management, P. O. Box 3707, MC
Configuration 2, Airplanes 2H–65, Seattle, WA 98124–2207; telephone
(1) The Manager, Los Angeles ACO, FAA,
For airplanes identified as Groups 1 206–544–5000, extension 1; fax 206–766–
has the authority to approve AMOCs for this
through 6, Configuration 2, in Boeing Alert 5680; Internet https://
AD, if requested using the procedures found www.myboeingfleet.com.
Service Bulletin 737–53A1279, Revision 2, in 14 CFR 39.19. In accordance with 14 CFR
dated April 21, 2015: Except as required by (6) You may view this service information
39.19, send your request to your principal at the FAA, Transport Airplane Directorate,
paragraph (t)(1) of this AD, at the applicable
inspector or local Flight Standards District 1601 Lind Avenue SW., Renton, WA. For
time specified in table 4 or table 6 of
Office, as appropriate. If sending information information on the availability of this
paragraph 1.E., ‘‘Compliance,’’ of Boeing
directly to the manager of the ACO, send it material at the FAA, call 425–227–1221.
Alert Service Bulletin 737–53A1279,
to the attention of the person identified in (7) You may view this service information
Revision 2, dated April 21, 2015, do HFEC,
paragraph (v)(1) of this AD. Information may that is incorporated by reference at the
LFEC, and detailed inspections for cracking
in accordance with ‘‘Part 8—INSPECTION be emailed to: 9-ANM-LAACO-AMOC- National Archives and Records
OF PREVENTATIVE MODIFICATION’’ of the Requests@faa.gov. Administration (NARA). For information on
Accomplishment Instructions of Boeing Alert (2) Before using any approved AMOC, the availability of this material at NARA, call
Service Bulletin 737–53A1279, Revision 2, notify your appropriate principal inspector, 202–741–6030, or go to: http://
dated April 21, 2015. Repeat the inspections or lacking a principal inspector, the manager www.archives.gov/federal-register/cfr/ibr-
thereafter at the applicable interval specified of the local flight standards district office/ locations.html.
in table 4 or table 6 of paragraph 1.E., certificate holding district office. Issued in Renton, Washington, on May 18,
‘‘Compliance,’’ of Boeing Alert Service (3) An AMOC that provides an acceptable 2016.
Bulletin 737–53A1279, Revision 2, dated level of safety may be used for any repair, Dionne Palermo,
April 21, 2015. If any cracking is found modification, or alteration required by this
AD if it is approved by the Boeing Acting Manager, Transport Airplane
during any inspection required by this Directorate, Aircraft Certification Service.
paragraph, before further flight, repair using Commercial Airplanes ODA that has been
a method approved in accordance with the authorized by the Manager, Los Angeles [FR Doc. 2016–12329 Filed 5–31–16; 8:45 am]
procedures specified in paragraph (u) of this ACO, to make those findings. To be BILLING CODE 4910–13–P
AD. approved, the repair method, modification
deviation, or alteration deviation must meet
(s) New Requirement of This AD: Inspections the certification basis of the airplane and the
of Preventive Modification for Groups 4–6,
DEPARTMENT OF TRANSPORTATION
approval must specifically refer to this AD.
Configuration 1, Airplanes (4) AMOCs approved for the ADs in Federal Aviation Administration
For airplanes identified as Groups 4 paragraphs (u)(4)(i) through (u)(4)(iii) of this
through 6, Configuration 1, in Boeing Alert AD are approved as AMOCs for the
14 CFR Part 39
Service Bulletin 737–53A1279, Revision 2, corresponding provisions of this AD.
dated April 21, 2015: At the applicable time (i) AD 2009–02–06, Amendment 39–15796 [Docket No. FAA–2015–8465; Directorate
specified in table 5 of paragraph 1.E., (74 FR 10469, March 11, 2009). Identifier 2014–NM–239–AD; Amendment
‘‘Compliance,’’ of Boeing Alert Service (ii) AD 2009–02–06 R1, Amendment 39– 39–18535; AD 2016–11–08]
Bulletin 737–53A1279, Revision 2, dated 16015 (74 FR 45979, September 8, 2009).
April 21, 2015, except as required by (iii) AD 2011–23–05. RIN 2120–AA64
paragraph (t)(1) of this AD: Do HFEC and
detailed inspections for cracking in
(v) Related Information Airworthiness Directives; Airbus
accordance with ‘‘Part 7—INSPECTION OF (1) For more information about this AD, Defense and Space S.A. (Formerly
PREVENTATIVE MODIFICATION’’ of the contact Galib Abumeri, Aerospace Engineer, Known as Construcciones
Accomplishment Instructions of Boeing Alert Airframe Branch, ANM–120L, FAA, Los Aeronauticas, S.A.)
Angeles ACO, 3960 Paramount Boulevard,
sradovich on DSK3TPTVN1PROD with RULES

Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Repeat the inspections Lakewood, CA 90712–4137; phone: 562–627– AGENCY: Federal Aviation
thereafter at the applicable time specified in 5324; fax: 562–627–5210; email: Administration (FAA), Department of
paragraph 1.E., ‘‘Compliance,’’ of Boeing galib.abumeri@faa.gov. Transportation (DOT).
Alert Service Bulletin 737–53A1279, (2) Service information identified in this ACTION: Final rule.
Revision 2, dated April 21, 2015. If any AD that is not incorporated by reference is
cracking is found during any inspection available at the addresses specified in SUMMARY: We are superseding
required by this paragraph, before further paragraphs (w)(5) and (w)(6) of this AD. Airworthiness Directive (AD) 2001–12–

VerDate Sep<11>2014 16:11 May 31, 2016 Jkt 238001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\01JNR1.SGM 01JNR1

Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34877

18 for certain CASA Model CN–235 Operations, M–30, West Building cable (P/N 72830–20) failure was reported,
series airplanes. AD 2001–12–18 Ground Floor, Room W12–140, 1200 where the affected part accumulated 9,936
required modification of the rigging of New Jersey Avenue SE., Washington, FH and 10,552 FC and was part of the Power
the engine control cable assembly and DC 20590. Lever control. Investigation of the latter case
identified again a fatigue nucleation to be the
replacement of either the entire engine FOR FURTHER INFORMATION CONTACT: cause of the cable failure.
control cable assembly or a segment of Shahram Daneshmandi, Aerospace To address this potentially unsafe
the control cables. This new AD would Engineer, International Branch, ANM– condition, Airbus Military issued Alert
retain the requirements of AD 2001–12– 116, Transport Airplane Directorate, Operators Transmission (AOT) AOT–CN235–
18. This new AD also requires repetitive FAA, 1601 Lind Avenue SW., Renton, 76–0001 to provide a repetitive replacement
replacements of each power lever and WA 98057–3356; telephone 425–227– interval and instructions.
condition lever Teleflex cable with a 1112; fax 425–227–1149. For the reasons described above, this
new or serviceable part, and removes [EASA] AD retains the requirements of DGAC
SUPPLEMENTARY INFORMATION: Spain AD No. 03/00, which is superseded,
airplanes from the applicability. This
but requires repetitive replacement [at
AD was prompted by reports of new Discussion
reduced thresholds] of the affected Teleflex
occurrences of cable disruption on a We issued a notice of proposed cables.
certain part number; the disruption is rulemaking (NPRM) to amend 14 CFR
caused by microcracks along the cable You may examine the MCAI in the AD
part 39 to supersede AD 2001–12–18, docket on the Internet at http://
surface. We are issuing this AD to Amendment 39–12274 (66 FR 33014,
prevent fatigue of the engine control www.regulations.gov by searching for
June 20, 2001) (‘‘AD 2001–12–18’’). AD and locating Docket No. FAA–2015–
cables, leading to breakage of the cables, 2001–12–18 applied to certain CASA
which could result in reduced 8465.
Model CN–235 series airplanes. The
controllability of the airplane. NPRM published in the Federal Comments
DATES: This AD is effective July 6, 2016. Register on January 19, 2016 (81 FR We gave the public the opportunity to
The Director of the Federal Register 2783) (‘‘the NPRM’’). participate in developing this AD. We
approved the incorporation by reference The European Aviation Safety Agency received no comments on the NPRM or
of a certain publication listed in this AD (EASA), which is the Technical Agent on the determination of the cost to the
as of July 6, 2016. for the Member States of the European public.
The Director of the Federal Register Union, has issued EASA Airworthiness
approved the incorporation by reference Directive 2014–0262, dated December 5, Clarification of Applicability
of a certain other publication listed in 2014 (referred to after this as the We have clarified the Applicability in
this AD as of July 25, 2001 (66 FR Mandatory Continuing Airworthiness paragraph (c) of this AD. For Model CN–
33014, June 20, 2001). Information, or ‘‘the MCAI’’), to correct 235 airplanes, the affected serial
ADDRESSES: For service information an unsafe condition for certain Airbus numbers (S/N) are C–001 through C–015
identified in this final rule, contact Defense and Space S.A. Model CN–235– inclusive. We have removed S/N C–074
EADS–CASA, Military Transport 100 and -200 airplanes. The MCAI for Model CN–235 airplanes because
Aircraft Division (MTAD), Integrated states: there are no Model CN–235 airplanes
Customer Services (ICS), Technical Three occurrences of cable disruption were with that serial number.
Services, Avenida de Aragón 404, 28022 reported in 1999. The failed parts, having a For Model CN–235–100 and –200
Madrid, Spain; telephone +34 91 585 55 part number (P/N) 7–44728–20, were part of airplanes, the affected serial numbers
84; fax +34 91 585 55 05; email MTA. the engine control system assembly P/N are C–016 through C–073 inclusive. We
TechnicalService@casa.eads.net; 7–44728–12. Two cables were connected to have removed S/Ns C–001 through
Internet http://www.eads.net. You may the Power Lever and one cable to the C–015 inclusive and C–074 for CN–235–
view this referenced service information Condition Lever control. Service records of
100 and –200 airplanes because there
the affected parts showed that each cable
at the FAA, Transport Airplane are no Model CN–235–100 and –200
accumulated more than 14,000 flight cycles
Directorate, 1601 Lind Avenue SW., (FC). with those serial numbers.
Renton, WA. For information on the The subsequent investigation determined
availability of this material at the FAA, Conclusion
that the disruption was attributed to fatigue
call 425–227–1221. It is also available related crack. We reviewed the available data and
on the Internet at http:// This condition, if not corrected, could lead determined that air safety and the
www.regulations.gov by searching for to failure of the engine control system public interest require adopting this AD
and locating Docket No. FAA–2015– resulting in a loss of the affected engine with the changes described previously
8465. control. and minor editorial changes. We have
Prompted by this unsafe condition, DGAC
determined that these minor changes:
Examining the AD Docket [Dirección General de Aviación Civil] Spain
issued AD 03/00 [which corresponds to FAA • Are consistent with the intent that
You may examine the AD docket on AD 2001–12–18] to require rigging of the was proposed in the NPRM for
the Internet at http:// throttle stops, and one-time replacement of correcting the unsafe condition; and
www.regulations.gov by searching for the affected engine control cable assembly • Do not add any additional burden
and locating Docket No. FAA–2015– (P/N 7–44728–12), or the affected cable (P/N upon the public than was already
8465; or in person at the Docket 7–44728–20) before exceeding 12,000 FC. proposed in the NPRM.
Management Facility between 9 a.m. After that [DGAC Spain] AD was issued, a We also determined that these
and 5 p.m., Monday through Friday, new occurrence of cable (P/N 72830–20) changes will not increase the economic
sradovich on DSK3TPTVN1PROD with RULES

except Federal holidays. The AD docket disruption was reported. In that case, the
burden on any operator or increase the
contains this AD, the regulatory affected cable was part of the Condition
Lever control and had accumulated 8,497 scope of this AD.
evaluation, any comments received, and flight hours (FH) and 8,858 FC. Fractographic
other information. The address for the Related Service Information Under
analysis of the affected cable identified that 1 CFR Part 51
Docket Office (telephone 800–647–5527) the fatigue nucleation seemed to have been
is Docket Management Facility, U.S. induced by microcracks along the cable Airbus Defense and Space S.A. has
Department of Transportation, Docket surface. Additionally, another case of control issued Airbus Military Alert Operators

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34878 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

Transmission AOT–CN235–76–0001, for practices, methods, and procedures Aeronauticas, S.A.): Amendment 39–
dated May 27, 2014. This service the Administrator finds necessary for 18535; Docket No. FAA–2015–8465;
information describes repetitive safety in air commerce. This regulation Directorate Identifier 2014–NM–239–AD.
replacements of each power lever and is within the scope of that authority (a) Effective Date
condition lever Teleflex cable having a because it addresses an unsafe condition This AD is effective July 6, 2016.
certain part number with a new or that is likely to exist or develop on
serviceable part. This service products identified in this rulemaking (b) Affected ADs
information also provides a new life action. This AD replaces AD 2001–12–18,
limit of 5,000 flight cycles. This service Amendment 39–12274 (66 FR 33014, June
information is reasonably available Regulatory Findings 20, 2001) (‘‘AD 2001–12–18’’).
because the interested parties have We determined that this AD will not (c) Applicability
access to it through their normal course have federalism implications under
This AD applies to Airbus Defense and
of business or by the means identified Executive Order 13132. This AD will
Space S.A. (formerly known as
in the ADDRESSES section. not have a substantial direct effect on Construcciones Aeronauticas, S.A.) Model
the States, on the relationship between CN–235 airplanes, serial numbers C–001
Costs of Compliance
the national government and the States, through C–015 inclusive; and Model CN–
We estimate that this AD affects 3 or on the distribution of power and 235–100 and –200 airplanes, serial numbers
airplanes of U.S. registry. responsibilities among the various C–016 through C–073 inclusive; certificated
The rigging required by AD 2001–12– levels of government. in any category.
18, and retained in this AD takes about For the reasons discussed above, I
8 work-hours per product, at an average (d) Subject
certify that this AD:
labor rate of $85 per work-hour. Based 1. Is not a ‘‘significant regulatory Air Transport Association (ATA) of
on these figures, the estimated cost of America Code 76, Engine Controls.
action’’ under Executive Order 12866;
the rigging that was required by AD 2. Is not a ‘‘significant rule’’ under the (e) Reason
2001–12–18 is $680 per product. DOT Regulatory Policies and Procedures This AD was prompted by reports of new
The replacement required by AD (44 FR 11034, February 26, 1979); occurrences of cable disruption on a certain
2001–12–18, and retained in this AD 3. Will not affect intrastate aviation in part number; the disruption is caused by
takes about 47 work-hours per product, Alaska; and microcracks along the cable surface. We are
at an average labor rate of $85 per work- 4. Will not have a significant issuing this AD to prevent fatigue of the
hour. Required parts cost about $1,444 economic impact, positive or negative, engine control cables, leading to breakage of
per product. Based on these figures, the on a substantial number of small entities the cables, which could result in reduced
estimated cost of the replacement that under the criteria of the Regulatory controllability of the airplane.
was required by AD 2001–12–18 is Flexibility Act. (f) Compliance
$5,439 per product.
We also estimate that it would take List of Subjects in 14 CFR Part 39 Comply with this AD within the
compliance times specified, unless already
about 47 work-hours per product to Air transportation, Aircraft, Aviation done.
comply with the basic requirements of safety, Incorporation by reference,
this AD. The average labor rate is $85 Safety. (g) Retained Action for the Power Lever and
per work-hour. Required parts would Condition Lever Control Stops, With No
cost about $6,480 per product. Based on Adoption of the Amendment Changes
these figures, we estimate the cost of Accordingly, under the authority This paragraph restates the requirements of
this AD on U.S. operators to be $31,425, delegated to me by the Administrator, paragraph (a) of AD 2001–12–18. Within 15
or $10,475 per product. the FAA amends 14 CFR part 39 as days after July 25, 2001 (the effective date of
follows: AD 2001–12–18): Rig the power lever and
Authority for This Rulemaking condition lever control stops, in accordance
Title 49 of the United States Code PART 39—AIRWORTHINESS with CASA COM 235–140, Revision 01,
dated March 21, 2000.
specifies the FAA’s authority to issue DIRECTIVES
rules on aviation safety. Subtitle I, (h) New Requirement of This AD:
section 106, describes the authority of ■ 1. The authority citation for part 39 Replacement
the FAA Administrator. ‘‘Subtitle VII: continues to read as follows: At the applicable compliance times
Aviation Programs,’’ describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. specified in table 1 to paragraph (h) of this
detail the scope of the Agency’s AD: Replace each power lever and condition
§ 39.13 [Amended] lever Teleflex cable having part number
authority.
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by (P/N) 72830–20 with a new or serviceable
removing Airworthiness Directive (AD) part, in accordance with Airbus Military
the authority described in ‘‘Subtitle VII,
2001–12–18, Amendment 39–12274 (66 Alert Operators Transmission AOT–CN235–
Part A, Subpart III, Section 44701: 76–0001, dated May 27, 2014. Repeat the
General requirements.’’ Under that FR 33014, June 20, 2001), and adding
replacement thereafter at intervals not to
section, Congress charges the FAA with the following new AD: exceed an accumulation of 5,000 total flight
promoting safe flight of civil aircraft in 2016–11–08 Airbus Defense and Space S.A. cycles on each Teleflex cable having P/N
air commerce by prescribing regulations (formerly known as Construcciones 72830–20.

TABLE 1 TO PARAGRAPH (h) OF THIS AD—REPLACEMENT COMPLIANCE TIME
sradovich on DSK3TPTVN1PROD with RULES

Total flight cycles accumulated on the Teleflex cable having P/N
72830–20 (since first installation on an airplane) as of the effective Compliance time
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 flight cycles, but fewer than 6,000 Within 300 flight cycles or 12 months after the effective date of this AD,
total flight cycles. whichever occurs first.

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Document Created: 2018-02-08 07:27:35
Document Modified: 2018-02-08 07:27:35

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective July 6, 2016.
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.
FR Citation		81 FR 34876
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

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

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

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

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration