83_FR_29598 83 FR 29476 - Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A. (CASA)) Airplanes

83 FR 29476 - Airworthiness Directives; Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A. (CASA)) Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 122 (June 25, 2018)

Page Range29476-29479
FR Document2018-13342

We propose to adopt a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212- CD, C-212-CE, and C-212-DF airplanes. This proposed AD was prompted by reports of failures of the rudder pedal control system support. This proposed AD would require repetitive detailed visual inspections of the rudder pedal control system support box and shaft and applicable corrective actions. We are proposing this AD to address the unsafe condition on these products.

Federal Register, Volume 83 Issue 122 (Monday, June 25, 2018) 
[Federal Register Volume 83, Number 122 (Monday, June 25, 2018)]
[Proposed Rules]
[Pages 29476-29479]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-13342]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0552; Product Identifier 2018-NM-049-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 29477]]

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212-
CD, C-212-CE, and C-212-DF airplanes. This proposed AD was prompted by 
reports of failures of the rudder pedal control system support. This 
proposed AD would require repetitive detailed visual inspections of the 
rudder pedal control system support box and shaft and applicable 
corrective actions. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by August 9, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
Defense and Space, Services/Engineering support, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; 
fax: +34 91 585 31 27; email: [email protected]. 
You may view this service information at the FAA, Transport Standards 
Branch, 2200 South 216th St., Des Moines, WA. For information on the 
availability of this material at the FAA, call 206-231-3195.

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-2018-
0552; 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 NPRM, 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 Section, Transport Standards Branch, FAA, 2200 
South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3220.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0552; 
Product Identifier 2018-NM-049-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0051, dated March 2, 2018 (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 C-212-
CB, C-212-CC, C-212-CD, C-212-CE, and C-212-DF airplanes. The MCAI 
states:

    Failures were reported of the rudder pedal control system 
support on CASA C-212 aeroplanes. Subsequent investigation revealed 
that the welding area of the affected support structure had broken.
    This condition, if not corrected, could lead to failure of the 
rudder [pedal] control system, possibly resulting in reduced control 
of the aeroplane.
    To address this potential unsafe condition, EADS-CASA issued the 
SB [EADS-CASA Service Bulletin SB-212-27-0057, dated May 21, 2014] 
to provide modification instructions and EASA issued AD 2017-0036 
[which corresponds to FAA AD 2017-19-08, Amendment 39-19038 (82 FR 
43835, September 20 2017) (``AD 2017-19-08'')] to require that 
modification [of the rudder pedal adjustment system]. During 
accomplishment of that modification, several operators reported 
difficulties or impossibility to follow the accomplishment 
instruction. Consequently, EASA and Airbus D&S [Defense and Space 
S.A.] reviewed the difficulty reports and decided that the 
modification instructions have to be improved.
    Pending the improvement of the instructions of the SB [EADS-CASA 
Service Bulletin SB-212-27-0057, dated May 21, 2014] and in order to 
reduce the risk of failure of the [rudder] pedal adjustment system 
to an acceptable level, Airbus D&S issued the inspection AOT [Airbus 
Alert Operators Transmission AOT-C212-27-0002, dated February 28, 
2018] to provide instructions to repetitively inspect the affected 
parts [rudder pedal support box Part Number (P/N) 212-46195.1 and 
shaft P/N 212-46120-20].
    For the reasons described above, this [EASA] AD cancels the 
requirements of EASA AD 2017-0036, which is superseded, and requires 
repetitive [detailed visual] inspections of the rudder pedal 
adjustment system [rudder pedal support box P/N 212-46195.1 and 
shaft P/N 212-46120-20] and, depending on findings, accomplishment 
of applicable corrective action(s).
    This [EASA] AD is considered to be an interim action and further 
[EASA] AD action may follow.

    Corrective actions include obtaining corrective actions approved by 
the Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus Defense and Space S.A.'s EASA Design Organization 
Approval (DOA); and accomplishing the corrective actions within the 
compliance time specified therein. 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-2018-0552.

Relationship Between Proposed AD and AD 2017-19-08

    This NPRM does not propose to supersede AD 2017-19-08. Rather, we 
have determined that a stand-alone AD would be more appropriate to 
address the changes in the MCAI. This proposed AD would require 
repetitive detailed visual inspections of the rudder pedal control 
system support box and shaft and applicable corrective actions. 
Accomplishment of the proposed actions would then terminate all of the 
requirements of AD 2017-19-08.

Related Service Information Under 1 CFR Part 51

    Airbus Defense and Space S.A. has issued Airbus Alert Operators 
Transmission AOT-C212-27-0002, dated February 28, 2018. The service 
information describes procedures for repetitive detailed visual 
inspections of the rudder pedal control system support box and shaft. 
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

[[Page 29478]]

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.

Costs of Compliance

    We estimate that this proposed AD affects 36 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
               Labor cost                   Parts cost         Cost per  product        Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Up to 8 work[dash]hours x $85 per hour =              $0  Up to $680................  Up to $24,480.
 Up to $680.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repair specified in this proposed 
AD.

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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

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

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 adding the following new airworthiness 
directive (AD):

Airbus Defense and Space S.A. (Formerly Known as Construcciones 
Aeronauticas, S.A. (CASA)): Docket No. FAA-2018-0552; Product 
Identifier 2018-NM-049-AD.

(a) Comments Due Date

    We must receive comments by August 9, 2018.

(b) Affected ADs

    This AD affects AD 2017-19-08, Amendment 39-19038 (82 FR 43835, 
September 20 2017) (``AD 2017-19-08'').

(c) Applicability

    This AD applies to Airbus Defense and Space S.A. Model C-212-CB, 
C-212-CC, C-212-CD, C-212-CE, and C-212-DF airplanes; manufacturer 
serial numbers 009, 034, 039, 089, 092, 119, 125, 133, 138, 149, 
150, 154, 159, 161, 162, 164, 165, 167 through 169 inclusive, 171, 
172, 174, 175, 178, 180, 181, 190, 192, 193, 195, 209 through 212 
inclusive, 214 through 216 inclusive, 219 through 222 inclusive, 224 
through 227 inclusive, 229, 235, 236, 238, 240, 242, 247 through 257 
inclusive, 261 through 263 inclusive, 265, 272 through 282 
inclusive, 286, 287, 289 through 292 inclusive, 294, 308, 311, 320, 
322 through 324 inclusive, 328, 332, 336, 343, 347 through 349 
inclusive, 356, 359, 363, 371, 379, 393, 397, 398, 405, 410, 411, 
413, 465, 470, 472, 474, 475, 478, and 480 through 482 inclusive; 
certificated in any category; except airplanes modified in 
accordance with the Accomplishment Instructions of EADS-CASA Service 
Bulletin SB-212-27-0057, dated May 21, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by reports of failures of the rudder pedal 
control system support. We are issuing this AD to prevent failure of 
the rudder control system, which could result in reduced 
controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definitions

    (1) For the purposes of this AD, an affected part is defined as 
a rudder pedal support box having Part Number (P/N) 212-46195.1 and 
shaft P/N 212-46120-20.
    (2) For the purposes of this AD, a discrepancy or defect of the 
rudder pedal support box P/N 212-46195.1 is defined as any crack or 
deformation on any welded area.
    (3) For the purposes of this AD, a discrepancy or defect of the 
shaft P/N 212-46120-20 is defined as any crack or deformation.

(h) Repetitive Detailed Visual Inspections

    Within 3 months or during the next scheduled A-check 
maintenance, whichever occurs first after the effective date of this 
AD, and thereafter, at intervals not to exceed 150 flight hours, do 
a detailed visual inspection of each affected part in accordance 
with the instructions of Airbus Alert Operators Transmission AOT-
C212-27-0002, dated February 28, 2018.

[[Page 29479]]

(i) Corrective Action for Any Discrepancy or Defect

    If any discrepancy or defect is detected during any inspection 
required by paragraph (h) of this AD: Before further flight, obtain 
corrective actions approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus Defense and Space S.A.'s EASA Design 
Organization Approval (DOA); and accomplish the corrective actions 
within the compliance time specified therein. If approved by the 
DOA, the approval must include the DOA-authorized signature. 
Accomplishment of a repair, as required by this paragraph, does not 
constitute terminating action for the repetitive inspections 
required by paragraph (h) of this AD.

(j) Parts Installation Limitation

    As of the effective date of this AD, an affected part may be 
installed on any airplane provided that it is a new part or that, 
before installation, the visual inspection required by paragraph (h) 
of this AD has been accomplished on that part and the part passed 
the inspection (no discrepancy or defect detected), as required by 
paragraph (h) of this AD.

(k) Terminating Action for AD 2017-19-08

    Accomplishing the actions required by this AD terminates all of 
the requirements of AD 2017-19-08.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (m)(2) of this AD. 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.
    (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, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus Defense 
and Space S.A.'s EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0051, dated March 2, 2018, 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-2018-0552.
    (2) For more information about this AD, contact Shahram 
Daneshmandi, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3220.
    (3) For service information identified in this AD, contact 
Airbus Defense and Space, Services/Engineering support, Avenida de 
Arag[oacute]n 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; 
fax: +34 91 585 31 27; email: 
[email protected]. You may view this service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.
    Issued in Des Moines, Washington, on June 14, 2018.

Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-13342 Filed 6-22-18; 8:45 am]
 BILLING CODE 4910-13-P

29476 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules implications under Executive Order R01, dated February 18, 2016, or in HPC rotor stage 2–5 spool listed in paragraph 13132. This proposed AD would not paragraph 4, Appendix A, of GE SB GE90– (c)(2) of this AD, or HPC rotor stage 2–5 spool have a substantial direct effect on the 100 SB 72–0714 R01, dated February 16, with a serial number listed in paragraph 4, 2018. Appendix A, of GE SB GE90–100 SB 72–0714 States, on the relationship between the (2) A part number (P/N) 351–103–109–0, P/ R01, dated February 16, 2018, that exceeds national Government and the States, or N 351–103–110–0, P/N 351–103–147–0 or P/ 8,200 CSN. on the distribution of power and N 351–103–152–0, with any serial number. responsibilities among the various (i) Alternative Methods of Compliance levels of government. (d) Subject (AMOCs) For the reasons discussed above, I Joint Aircraft System Component (JASC) (1) The Manager, ECO Branch, FAA, has certify that the proposed regulation: Code 7230, Turbine Engine Compressor the authority to approve AMOCs for this AD, (1) Is not a ‘‘significant regulatory Section. if requested using the procedures found in 14 action’’ under Executive Order 12866, CFR 39.19. In accordance with 14 CFR 39.19, (e) Unsafe Condition send your request to your principal inspector (2) Is not a ‘‘significant rule’’ under This AD was prompted by reports of cracks or local Flight Standards District Office, as the DOT Regulatory Policies and in HPC rotor stage 2–5 spool aft spacer arms. appropriate. If sending information directly Procedures (44 FR 11034, February 26, We are issuing this AD to prevent failure of to the manager of the certification office, 1979), the HPC rotor stage 2–5 spools. The unsafe send it to the attention of the person (3) Will not affect intrastate aviation condition, if not addressed, could result in identified in paragraph (j)(1) of this AD. You in Alaska, and uncontained spool release, damage to the may email your request to: ANE-AD-AMOC@ engine, and damage to the airplane. faa.gov. (4) Will not have a significant economic impact, positive or negative, (f) Compliance (2) Before using any approved AMOC, on a substantial number of small entities notify your appropriate principal inspector, Comply with this AD within the or lacking a principal inspector, the manager under the criteria of the Regulatory compliance times specified, unless already of the local flight standards district office/ Flexibility Act. done. certificate holding district office. List of Subjects in 14 CFR Part 39 (g) Required Actions (j) Related Information Air transportation, Aircraft, Aviation (1) Remove from service HPC rotor stage 2– (1) For more information about this AD, 5 spools with serial numbers listed in safety, Incorporation by reference, paragraph 4, Appendix A, of GE SB GE90– contact David Bethka, Aerospace Engineer, Safety. ECO Branch, FAA, 1200 District Avenue, 100 SB 72–0659 R01, dated February 18, Burlington, MA 01803; phone: 781–238– The Proposed Amendment 2016, as follows, or before further flight, 7129; fax: 781–238–7199; email: whichever occurs later: Accordingly, under the authority david.bethka@faa.gov. (i) For spools with fewer than 4,500 flight (2) For service information identified in delegated to me by the Administrator, CSN as of April 21, 2017, remove before exceeding 5,000 CSN. this AD, contact General Electric Company, the FAA proposes to amend 14 CFR part One Neumann Way, Room 285, Cincinnati, 39 as follows: (ii) For spools with 4,500 CSN or more but fewer than 5,200 CSN as of April 21, 2017, OH; phone: 513–552–3272; email: geae.aoc@ remove within 500 CIS but not to exceed ge.com. You may view this referenced service PART 39—AIRWORTHINESS information at the FAA, Engine and Propeller DIRECTIVES 5,500 CSN. (iii) For spools with 5,200 CSN or more but Standards Branch, 1200 District Avenue, fewer than 5,600 CSN as of April 21, 2017, Burlington, MA 01803. For information on ■ 1. The authority citation for part 39 the availability of this material at the FAA, remove within 300 CIS but not to exceed continues to read as follows: 5,800 CSN. call 781–238–7759. Authority: 49 U.S.C. 106(g), 40113, 44701. (iv) For spools with 5,600 CSN or more but Issued in Burlington, Massachusetts, on fewer than 5,800 CSN as of April 21, 2017, June 19, 2018. § 39.13 [Amended] remove within 200 CIS but not to exceed Robert J. Ganley, ■ 2. The FAA amends § 39.13 by 5,850 CSN. (v) For spools with 5,800 CSN or more but Manager, Engine and Propeller Standards removing Airworthiness Directive (AD) Branch, Aircraft Certification Service. 2017–07–04, Amendment 39–18842 (82 fewer than 6,000 CSN as of April 21, 2017, remove within 50 CIS but not to exceed 6,000 [FR Doc. 2018–13444 Filed 6–22–18; 8:45 am] FR 16728, April 6, 2017), and adding CSN. BILLING CODE 4910–13–P the following new AD: (vi) For spools with 6,000 CSN or more as General Electric Company: Docket No. of April 21, 2017, remove before the next FAA–2018–0406; Product Identifier 2013– flight. DEPARTMENT OF TRANSPORTATION NE–30–AD. (2) Remove from service HPC rotor stage 2– 5 spools listed in paragraph (c)(2) of this AD Federal Aviation Administration (a) Comments Due Date and HPC rotor stage 2–5 spools with serial The FAA must receive comments on this numbers listed in paragraph 4, Appendix A, of GE SB GE90–100 SB 72–0714 R01, dated 14 CFR Part 39 AD action by August 9, 2018. February 16, 2018, before exceeding 8,200 (b) Affected ADs CSN, or before further flight, whichever [Docket No. FAA–2018–0552; Product This AD replaces AD 2017–07–04, occurs later. Identifier 2018–NM–049–AD] Amendment 39–18842 (82 FR 16728, April 6, (h) Installation Prohibition RIN 2120–AA64 2017) (‘‘AD 2017–07–04’’). (1) After the effective date of this AD, do (c) Applicability not install or reinstall onto any engine, any Airworthiness Directives; Airbus amozie on DSK3GDR082PROD with PROPOSALS1 This AD applies to General Electric HPC rotor stage 2–5 spool with a serial Defense and Space S.A. (Formerly Company (GE) GE90–110B1 and GE90–115B number listed in paragraph 4, Appendix A, Known as Construcciones turbofan engines with HPC rotor stage 2–5 of GE SB No. GE90–100 SB 72–0499 R01, Aeronauticas, S.A. (CASA)) Airplanes spools, with: dated February 5, 2014, or paragraph 4, (1) A serial number listed in either, Appendix A, of GE SB GE90–100 SB72–0659 AGENCY: Federal Aviation paragraph 4, Appendix A of GE Service R01, dated February 18, 2016, that exceeds Administration (FAA), DOT. Bulletin (SB) No. GE90–100 SB 72–0499 R01, 5,000 CSN. ACTION: Notice of proposed rulemaking dated February 5, 2014, in paragraph 4, (2) After the effective date of this AD, do (NPRM). Appendix A of GE SB GE90–100 SB 72–0659 not install or reinstall onto any engine, any VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1

Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 29477 SUMMARY: We propose to adopt a new SUPPLEMENTARY INFORMATION: Operators Transmission AOT–C212–27– airworthiness directive (AD) for certain 0002, dated February 28, 2018] to provide Comments Invited instructions to repetitively inspect the Airbus Defense and Space S.A. Model C–212–CB, C–212–CC, C–212–CD, C– We invite you to send any written affected parts [rudder pedal support box Part relevant data, views, or arguments about Number (P/N) 212–46195.1 and shaft P/N 212–CE, and C–212–DF airplanes. This 212–46120–20]. proposed AD was prompted by reports this proposal. Send your comments to For the reasons described above, this of failures of the rudder pedal control an address listed under the ADDRESSES [EASA] AD cancels the requirements of system support. This proposed AD section. Include ‘‘Docket No. FAA– EASA AD 2017–0036, which is superseded, would require repetitive detailed visual 2018–0552; Product Identifier 2018– and requires repetitive [detailed visual] inspections of the rudder pedal control NM–049–AD’’ at the beginning of your inspections of the rudder pedal adjustment system support box and shaft and comments. We specifically invite system [rudder pedal support box P/N 212– applicable corrective actions. We are comments on the overall regulatory, 46195.1 and shaft P/N 212–46120–20] and, proposing this AD to address the unsafe economic, environmental, and energy depending on findings, accomplishment of condition on these products. aspects of this NPRM. We will consider applicable corrective action(s). This [EASA] AD is considered to be an DATES: We must receive comments on all comments received by the closing interim action and further [EASA] AD action this proposed AD by August 9, 2018. date and may amend this NPRM based may follow. ADDRESSES: You may send comments, on those comments. We will post all comments we Corrective actions include obtaining using the procedures found in 14 CFR receive, without change, to http:// corrective actions approved by the 11.43 and 11.45, by any of the following www.regulations.gov, including any Manager, International Section, methods: • Federal eRulemaking Portal: Go to personal information you provide. We Transport Standards Branch, FAA; or http://www.regulations.gov. Follow the will also post a report summarizing each EASA; or Airbus Defense and Space instructions for submitting comments. substantive verbal contact we receive S.A.’s EASA Design Organization • Fax: 202–493–2251. about this NPRM. Approval (DOA); and accomplishing the • Mail: U.S. Department of corrective actions within the Discussion compliance time specified therein. You Transportation, Docket Operations, M– 30, West Building Ground Floor, Room The European Aviation Safety Agency may examine the MCAI in the AD W12–140, 1200 New Jersey Avenue SE, (EASA), which is the Technical Agent docket on the internet at http:// Washington, DC 20590. for the Member States of the European www.regulations.gov by searching for • Hand Delivery: Deliver to Mail Union, has issued EASA AD 2018–0051, and locating Docket No. FAA–2018– address above between 9 a.m. and 5 dated March 2, 2018 (referred to after 0552. p.m., Monday through Friday, except this as the Mandatory Continuing Relationship Between Proposed AD and Federal holidays. Airworthiness Information, or ‘‘the AD 2017–19–08 For service information identified in MCAI’’), to correct an unsafe condition this NPRM, contact Airbus Defense and for certain Airbus Defense and Space This NPRM does not propose to Space, Services/Engineering support, S.A. Model C–212–CB, C–212–CC, C– supersede AD 2017–19–08. Rather, we Avenida de Aragón 404, 28022 Madrid, 212–CD, C–212–CE, and C–212–DF have determined that a stand-alone AD Spain; telephone: +34 91 585 55 84; fax: airplanes. The MCAI states: would be more appropriate to address +34 91 585 31 27; email: Failures were reported of the rudder pedal the changes in the MCAI. This proposed MTA.TechnicalService@ control system support on CASA C–212 AD would require repetitive detailed military.airbus.com. You may view this aeroplanes. Subsequent investigation visual inspections of the rudder pedal service information at the FAA, revealed that the welding area of the affected control system support box and shaft Transport Standards Branch, 2200 support structure had broken. and applicable corrective actions. South 216th St., Des Moines, WA. For This condition, if not corrected, could lead Accomplishment of the proposed information on the availability of this to failure of the rudder [pedal] control actions would then terminate all of the system, possibly resulting in reduced control requirements of AD 2017–19–08. material at the FAA, call 206–231–3195. of the aeroplane. Examining the AD Docket To address this potential unsafe condition, Related Service Information Under 1 EADS–CASA issued the SB [EADS–CASA CFR Part 51 You may examine the AD docket on Service Bulletin SB–212–27–0057, dated May the internet at http:// 21, 2014] to provide modification Airbus Defense and Space S.A. has www.regulations.gov by searching for instructions and EASA issued AD 2017–0036 issued Airbus Alert Operators and locating Docket No. FAA–2018– [which corresponds to FAA AD 2017–19–08, Transmission AOT–C212–27–0002, 0552; or in person at the Docket Amendment 39–19038 (82 FR 43835, dated February 28, 2018. The service Management Facility between 9 a.m. September 20 2017) (‘‘AD 2017–19–08’’)] to information describes procedures for and 5 p.m., Monday through Friday, require that modification [of the rudder pedal repetitive detailed visual inspections of except Federal holidays. The AD docket adjustment system]. During accomplishment of that modification, several operators the rudder pedal control system support contains this NPRM, the regulatory reported difficulties or impossibility to box and shaft. This service information evaluation, any comments received, and follow the accomplishment instruction. is reasonably available because the other information. The street address for Consequently, EASA and Airbus D&S interested parties have access to it the Docket Operations office (telephone: [Defense and Space S.A.] reviewed the through their normal course of business 800–647–5527) is in the ADDRESSES difficulty reports and decided that the or by the means identified in the amozie on DSK3GDR082PROD with PROPOSALS1 section. Comments will be available in modification instructions have to be ADDRESSES section. the AD docket shortly after receipt. improved. FOR FURTHER INFORMATION CONTACT: Pending the improvement of the FAA’s Determination and Requirements instructions of the SB [EADS–CASA Service of This Proposed AD Shahram Daneshmandi, Aerospace Bulletin SB–212–27–0057, dated May 21, Engineer, International Section, 2014] and in order to reduce the risk of This product has been approved by Transport Standards Branch, FAA, 2200 failure of the [rudder] pedal adjustment the aviation authority of another South 216th St., Des Moines, WA 98198; system to an acceptable level, Airbus D&S country, and is approved for operation telephone and fax 206–231–3220. issued the inspection AOT [Airbus Alert in the United States. Pursuant to our VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1

29478 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules bilateral agreement with the State of AD because we evaluated all pertinent Costs of Compliance Design Authority, we have been notified information and determined an unsafe We estimate that this proposed AD of the unsafe condition described in the condition exists and is likely to exist or affects 36 airplanes of U.S. registry. We MCAI and service information develop on other products of the same estimate the following costs to comply referenced above. We are proposing this type design. with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Cost per Cost on U.S. Labor cost Parts cost product operators Up to 8 work-hours × $85 per hour = Up to $680 .................................................... $0 Up to $680 .............. Up to $24,480. We have received no definitive data For the reasons discussed above, I 089, 092, 119, 125, 133, 138, 149, 150, 154, that would enable us to provide cost certify this proposed regulation: 159, 161, 162, 164, 165, 167 through 169 estimates for the on-condition repair 1. Is not a ‘‘significant regulatory inclusive, 171, 172, 174, 175, 178, 180, 181, 190, 192, 193, 195, 209 through 212 specified in this proposed AD. action’’ under Executive Order 12866; inclusive, 214 through 216 inclusive, 219 2. Is not a ‘‘significant rule’’ under the through 222 inclusive, 224 through 227 Authority for This Rulemaking DOT Regulatory Policies and Procedures inclusive, 229, 235, 236, 238, 240, 242, 247 Title 49 of the United States Code (44 FR 11034, February 26, 1979); through 257 inclusive, 261 through 263 specifies the FAA’s authority to issue 3. Will not affect intrastate aviation in inclusive, 265, 272 through 282 inclusive, rules on aviation safety. Subtitle I, Alaska; and 286, 287, 289 through 292 inclusive, 294, section 106, describes the authority of 4. Will not have a significant 308, 311, 320, 322 through 324 inclusive, economic impact, positive or negative, 328, 332, 336, 343, 347 through 349 the FAA Administrator. Subtitle VII: inclusive, 356, 359, 363, 371, 379, 393, 397, Aviation Programs, describes in more on a substantial number of small entities 398, 405, 410, 411, 413, 465, 470, 472, 474, detail the scope of the Agency’s under the criteria of the Regulatory 475, 478, and 480 through 482 inclusive; authority. Flexibility Act. certificated in any category; except airplanes We are issuing this rulemaking under List of Subjects in 14 CFR Part 39 modified in accordance with the the authority described in Subtitle VII, Accomplishment Instructions of EADS– Part A, Subpart III, Section 44701: Air transportation, Aircraft, Aviation CASA Service Bulletin SB–212–27–0057, safety, Incorporation by reference, dated May 21, 2014. ‘‘General requirements.’’ Under that section, Congress charges the FAA with Safety. (d) Subject promoting safe flight of civil aircraft in The Proposed Amendment Air Transport Association (ATA) of air commerce by prescribing regulations America Code 27, Flight controls. Accordingly, under the authority for practices, methods, and procedures delegated to me by the Administrator, (e) Reason the Administrator finds necessary for the FAA proposes to amend 14 CFR part This AD was prompted by reports of safety in air commerce. This regulation 39 as follows: failures of the rudder pedal control system is within the scope of that authority support. We are issuing this AD to prevent because it addresses an unsafe condition PART 39—AIRWORTHINESS failure of the rudder control system, which that is likely to exist or develop on DIRECTIVES could result in reduced controllability of the products identified in this rulemaking airplane. action. ■ 1. The authority citation for part 39 (f) Compliance This proposed AD is issued in continues to read as follows: Comply with this AD within the accordance with authority delegated by Authority: 49 U.S.C. 106(g), 40113, 44701. compliance times specified, unless already the Executive Director, Aircraft done. Certification Service, as authorized by § 39.13 [Amended] (g) Definitions FAA Order 8000.51C. In accordance ■ 2. The FAA amends § 39.13 by adding with that order, issuance of ADs is the following new airworthiness (1) For the purposes of this AD, an affected directive (AD): part is defined as a rudder pedal support box normally a function of the Compliance having Part Number (P/N) 212–46195.1 and and Airworthiness Division, but during Airbus Defense and Space S.A. (Formerly shaft P/N 212–46120–20. this transition period, the Executive Known as Construcciones Aeronauticas, (2) For the purposes of this AD, a Director has delegated the authority to S.A. (CASA)): Docket No. FAA–2018– discrepancy or defect of the rudder pedal issue ADs applicable to transport 0552; Product Identifier 2018–NM–049– support box P/N 212–46195.1 is defined as category airplanes to the Director of the AD. any crack or deformation on any welded area. System Oversight Division. (3) For the purposes of this AD, a (a) Comments Due Date discrepancy or defect of the shaft P/N 212– Regulatory Findings We must receive comments by August 9, 46120–20 is defined as any crack or 2018. deformation. We determined that this proposed AD would not have federalism implications (b) Affected ADs (h) Repetitive Detailed Visual Inspections amozie on DSK3GDR082PROD with PROPOSALS1 under Executive Order 13132. This This AD affects AD 2017–19–08, Within 3 months or during the next proposed AD would not have a Amendment 39–19038 (82 FR 43835, scheduled A-check maintenance, whichever substantial direct effect on the States, on September 20 2017) (‘‘AD 2017–19–08’’). occurs first after the effective date of this AD, and thereafter, at intervals not to exceed 150 the relationship between the national (c) Applicability flight hours, do a detailed visual inspection Government and the States, or on the This AD applies to Airbus Defense and of each affected part in accordance with the distribution of power and Space S.A. Model C–212–CB, C–212–CC, C– instructions of Airbus Alert Operators responsibilities among the various 212–CD, C–212–CE, and C–212–DF airplanes; Transmission AOT–C212–27–0002, dated levels of government. manufacturer serial numbers 009, 034, 039, February 28, 2018. VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1

Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 29479 (i) Corrective Action for Any Discrepancy or (2) For more information about this AD, address the unsafe condition on these Defect contact Shahram Daneshmandi, Aerospace products. If any discrepancy or defect is detected Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th DATES: We must receive comments on during any inspection required by paragraph (h) of this AD: Before further flight, obtain St., Des Moines, WA 98198; telephone and this proposed AD by August 9, 2018. corrective actions approved by the Manager, fax 206–231–3220. ADDRESSES: You may send comments, International Section, Transport Standards (3) For service information identified in using the procedures found in 14 CFR Branch, FAA; or the European Aviation this AD, contact Airbus Defense and Space, 11.43 and 11.45, by any of the following Safety Agency (EASA); or Airbus Defense Services/Engineering support, Avenida de methods: Aragón 404, 28022 Madrid, Spain; telephone: and Space S.A.’s EASA Design Organization • Federal eRulemaking Portal: Go to Approval (DOA); and accomplish the +34 91 585 55 84; fax: +34 91 585 31 27; email: MTA.TechnicalService@ http://www.regulations.gov. Follow the corrective actions within the compliance military.airbus.com. You may view this instructions for submitting comments. time specified therein. If approved by the DOA, the approval must include the DOA- service information at the FAA, Transport • Fax: 202–493–2251. authorized signature. Accomplishment of a Standards Branch, 2200 South 216th St., Des • Mail: U.S. Department of repair, as required by this paragraph, does Moines, WA. For information on the Transportation, Docket Operations, M– not constitute terminating action for the availability of this material at the FAA, call 30, West Building Ground Floor, Room repetitive inspections required by paragraph 206–231–3195. W12–140, 1200 New Jersey Avenue SE, (h) of this AD. Issued in Des Moines, Washington, on Washington, DC 20590. (j) Parts Installation Limitation June 14, 2018. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 As of the effective date of this AD, an Michael Kaszycki, p.m., Monday through Friday, except affected part may be installed on any airplane Acting Director, System Oversight Division, provided that it is a new part or that, before Federal holidays. Aircraft Certification Service. installation, the visual inspection required by For service information identified in [FR Doc. 2018–13342 Filed 6–22–18; 8:45 am] paragraph (h) of this AD has been this NPRM, contact Honeywell BILLING CODE 4910–13–P International Inc., 111 S 34th Street, accomplished on that part and the part passed the inspection (no discrepancy or Phoenix, AZ 85034–2802; phone: 800– defect detected), as required by paragraph (h) 601–3099; internet: https:// of this AD. DEPARTMENT OF TRANSPORTATION myaerospace.honeywell.com/wps/ (k) Terminating Action for AD 2017–19–08 Federal Aviation Administration portal. You may view this service information at the FAA, Engine and Accomplishing the actions required by this AD terminates all of the requirements of AD 14 CFR Part 39 Propeller Standards Branch, 1200 2017–19–08. District Avenue, Burlington, MA. For [Docket No. FAA–2018–0479; Product information on the availability of this (l) Other FAA AD Provisions Identifier 2016–NE–23–AD] material at the FAA, call 781–238–7759. The following provisions also apply to this AD: RIN 2120–AA64 Examining the AD Docket (1) Alternative Methods of Compliance You may examine the AD docket on (AMOCs): The Manager, International Airworthiness Directives; Honeywell the internet at http:// Section, Transport Standards Branch, FAA, International Inc. Turboprop and www.regulations.gov by searching for has the authority to approve AMOCs for this Turboshaft Engines AD, if requested using the procedures found and locating Docket No. FAA–2018– in 14 CFR 39.19. In accordance with 14 CFR AGENCY: Federal Aviation 0479; or in person at Docket Operations 39.19, send your request to your principal Administration (FAA), DOT. between 9 a.m. and 5 p.m., Monday inspector or local Flight Standards District ACTION: Notice of proposed rulemaking through Friday, except Federal holidays. Office, as appropriate. If sending information (NPRM). The AD docket contains this NPRM, the directly to the International Section, send it regulatory evaluation, any comments to the attention of the person identified in SUMMARY: We propose to supersede received, and other information. The paragraph (m)(2) of this AD. Information may street address for Docket Operations Airworthiness Directive (AD) 2018–02– be emailed to: 9-ANM-116-AMOC- (phone: 800–647–5527) is listed above. REQUESTS@faa.gov. Before using any 14, which applies to certain Honeywell approved AMOC, notify your appropriate International Inc. (Honeywell) TPE331 Comments will be available in the AD principal inspector, or lacking a principal turboprop and TSE331 turboshaft docket shortly after receipt. inspector, the manager of the local flight engines. AD 2018–02–14 requires FOR FURTHER INFORMATION CONTACT: standards district office/certificate holding inspection of the affected combustion Joseph Costa, Aerospace Engineer, Los district office. chamber case assembly, replacement of Angeles ACO Branch, FAA, 3960 (2) Contacting the Manufacturer: For any those assemblies found cracked, and Paramount Blvd., Lakewood, CA 90712– requirement in this AD to obtain corrective removal of affected assemblies on 4137; phone: 562–627–5246; fax: 562– actions from a manufacturer, the action must certain TPE331 and TSE331 engines. 627–5210; email: joseph.costa@faa.gov. be accomplished using a method approved by the Manager, International Section, Since we issued AD 2018–02–14, we SUPPLEMENTARY INFORMATION: Transport Standards Branch, FAA; or EASA; received comments to revise the applicability of that AD to include the Comments Invited or Airbus Defense and Space S.A.’s EASA DOA. If approved by the DOA, the approval TPE331–12B engine model, correct We invite you to send any written must include the DOA-authorized signature. certain TPE engine model typographical relevant data, views, or arguments about amozie on DSK3GDR082PROD with PROPOSALS1 (m) Related Information errors, and to allow certain weld repair this proposed AD. Send your comments procedures. This proposed AD would to an address listed under the (1) Refer to Mandatory Continuing expand the applicability of AD 2018– ADDRESSES section. Include ‘‘Docket No. Airworthiness Information (MCAI) EASA AD 2018–0051, dated March 2, 2018, for related 02–14 to include the TPE331–12B FAA–2018–0479; Product Identifier information. This MCAI may be found in the engine model, correct certain engine 2016–NE–23–AD’’ at the beginning of AD docket on the internet at http:// model typographical errors, and allow your comments. We specifically invite www.regulations.gov by searching for and certain weld repair procedures after comments on the overall regulatory, locating Docket No. FAA–2018–0552. approval. We are proposing this AD to economic, environmental, and energy VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1


Document Created: 2018-06-23 02:29:21
Document Modified: 2018-06-23 02:29:21
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by August 9, 2018.
ContactShahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3220.
FR Citation83 FR 29476 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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