81 FR 73357 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 206 (October 25, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 206 (October 25, 2016)
| Page Range | 73357-73360 | |
| FR Document | 2016-25352 |
[Federal Register Volume 81, Number 206 (Tuesday, October 25, 2016)] [Proposed Rules] [Pages 73357-73360] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25352] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This proposed AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This proposed AD would require repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct cracking on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. DATES: We must receive comments on this proposed AD by December 9, 2016. 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 SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. 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-2016- 9192; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330, A340-200, and A340-300 series airplanes. The MCAI states: During A330/A340 aeroplanes full scale fatigue test specimen in the FR40-to-fuselage skin panel junction, fatigue damage has been found. Corrective actions consisted of the following actions: --In-service installation of an internal reinforcing strap on related junction required by DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and AD 2001- 070(B), --retrofit improvement of internal reinforcing strap fatigue life through recommended Airbus Service Bulletin (SB) A330-53-3145, and --new design in production through Airbus modification 44360. The aeroplanes listed in the Applicability section of this AD are all aeroplanes post-mod 44360 and pre-mod 55792 (fuselage reinforcement at FR40 in production). Recently, during embodiment of a FR40 web repair on an A330 aeroplane and during FR40 keel beam fitting replacement on an A340 aeroplane, the internal strap was removed and rototest inspection was performed on several holes. Cracks were found on both left-hand (LH) and right-hand (RH) sides on internal strap, or butt strap, or keel beam fitting, or forward fitting FR40 flange. This condition, if not detected and corrected, could lead to crack propagation, possibly resulting in reduced structural integrity of the fuselage. For the reasons described above, this [EASA] AD requires repetitive rototest inspections of 10 fastener holes located at FR40 lower shell panel junction on both LH and RH sides, and, depending on findings, accomplishment of the applicable corrective actions [which include oversizing, installing [[Page 73358]] fasteners and repair; and accomplishment of applicable related investigative actions, which include a rototest inspection for cracking after oversizing]. The compliance time ranges between 20,000 flight cycles or 65,400 flight hours and 20,800 flight cycles or 68,300 flight hours, depending on airplane utilization and configuration. The repetitive inspection interval ranges between 14,000 flight cycles or 95,200 flight hours and 24,600 flight cycles or 98,700 flight hours, depending on airplane configuration. 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-2016-9192. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; and Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014. The service information describes procedures for repetitive rototest inspections of certain fastener holes, and corrective actions if necessary. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 41 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection............................... 41 work-hours x $85 per hour = $0 $3,485 $142,885 per inspection cycle. $3,485 per inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair..................................... 46 work-hours x $85 per hour = $4,186 $8,096 $3,910. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 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: Docket No. FAA-2016-9192; Directorate Identifier 2016-NM- 038-AD. [[Page 73359]] (a) Comments Due Date We must receive comments by December 9, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, having serial numbers 0176 through 0915 inclusive. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking at fastener holes located at frame (FR)40 on the lower shell panel junction. We are issuing this AD to detect and correct cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Related Investigative and Corrective Actions Within the compliance times defined in table 1 to paragraph (g) of this AD, and, thereafter, at intervals not to exceed the compliance times defined in Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340- 53-4215, Revision 01, dated April 17, 2014; as applicable, depending on airplane utilization and configuration: Accomplish a special detailed inspection of fastener holes located at FR40 lower shell panel junction on both left-hand (LH) and right-side (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014; as applicable. Table 1 to Paragraph (g) of This AD--Compliance Time for Initial Inspection ------------------------------------------------------------------------ Compliance time (whichever occurs later, A or B) ------------------------------------------------------------------------ A................................ Before exceeding the compliance time ``threshold'' defined in table 1 of Airbus Service Bulletin A330-53- 3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014; as applicable, depending on airplane utilization and configuration and to be counted from airplane first flight. B................................ For Model A330 airplanes: Within 2,400 flight cycles or 24 months, whichever occurs first after the effective date of this AD. For Model A340 airplanes: Within 1,300 flight cycles or 24 months, whichever occurs first after the effective date of this AD. ------------------------------------------------------------------------ (1) If, during any inspection required by paragraph (g) of this AD, any crack is detected, before further flight, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014; as applicable, except where Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340- 53-4215, Revision 01, dated April 17, 2014, specifies to contact Airbus for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (2) If, during any inspection required by paragraph (g) of this AD, the hole diameter is not within tolerance of the transition fit as nominal, or first oversize, or second oversize, or next nominal, as applicable, and Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014, specifies to contact Airbus for repair instructions, and specifies that action as ``RC'' (Required for Compliance), before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (3) Accomplishment of corrective actions, as required by paragraph (g)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD. (4) Accomplishment of a repair on an airplane, as required by paragraph (g)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD for that airplane, unless the method approved in accordance with the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates otherwise. (h) Credit for Previous Actions (1) This paragraph provides credit for actions required by the introductory text of paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330-53-3215, dated June 21, 2013; or Airbus Service Bulletin A340-53-4215, dated June 21, 2013; as applicable. (2) This paragraph provides credit for the inspections and corrective actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B, dated July 12, 2011. (i) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 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: 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 Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (g)(1) and (g)(2) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or [[Page 73360]] changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 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-2016-9192. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on October 12, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-25352 Filed 10-24-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 206 / Tuesday, October 25, 2016 / Proposed Rules 73357
of 1982, secs. 117(a), 132, 133, 134, 135, 137, this AD to detect and correct cracking to an address listed under the
141, 145(g), 148, 218(a) (42 U.S.C. 10137(a), on the lower shell panel junction; such ADDRESSES section. Include ‘‘Docket No.
10152, 10153, 10154, 10155, 10157, 10161, cracking could lead to reduced FAA–2016–9192; Directorate Identifier
10165(g), 10168, 10198(a)); 44 U.S.C. 3504 structural integrity of the fuselage. 2016–NM–038–AD’’ at the beginning of
note.
DATES: We must receive comments on your comments. We specifically invite
■ 2. In § 72.214, Certificate of this proposed AD by December 9, 2016. comments on the overall regulatory,
Compliance 1040 is revised to read as economic, environmental, and energy
ADDRESSES: You may send comments,
follows: aspects of this proposed AD. We will
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following consider all comments received by the
§ 72.214 List of approved spent fuel
storage casks. methods: closing date and may amend this
• Federal eRulemaking Portal: Go to proposed AD based on those comments.
* * * * * We will post all comments we
Certificate Number: 1040. http://www.regulations.gov. Follow the
instructions for submitting comments. receive, without change, to http://
Initial Certificate Effective Date: April www.regulations.gov, including any
6, 2015. • Fax: 202–493–2251.
• Mail: U.S. Department of personal information you provide. We
Amendment Number 1 Effective Date: will also post a report summarizing each
September 8, 2015. Transportation, Docket Operations, M–
30, West Building Ground Floor, Room substantive verbal contact we receive
Amendment Number 2, Effective
W12–140, 1200 New Jersey Avenue SE., about this proposed AD.
Date: January 9, 2017.
SAR Submitted by: Holtec Washington, DC 20590. Discussion
International, Inc. • Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5 The European Aviation Safety Agency
SAR Title: Final Safety Analysis (EASA), which is the Technical Agent
Report for the Holtec International HI– p.m., Monday through Friday, except
Federal holidays. for the Member States of the European
STORM UMAX Canister Storage Union, has issued EASA Airworthiness
System. For service information identified in
this NPRM, contact Airbus SAS, Directive 2014–0136, dated June 13,
Docket Number: 72–1040. 2014 (referred to after this as the
Certificate Expiration Date: April 6, Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac Mandatory Continuing Airworthiness
2035. Information, or ‘‘the MCAI’’), to correct
Model Number: MPC–37, MPC–89. Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email an unsafe condition for certain Airbus
* * * * * Model A330, A340–200, and A340–300
airworthiness.A330-A340@airbus.com;
Dated at Rockville, Maryland, this 4th day Internet http://www.airbus.com. You series airplanes. The MCAI states:
of October, 2016. may view this referenced service During A330/A340 aeroplanes full scale
For the Nuclear Regulatory Commission. information at the FAA, Transport fatigue test specimen in the FR40-to-fuselage
Michael R. Johnson, Airplane Directorate, 1601 Lind Avenue skin panel junction, fatigue damage has been
found. Corrective actions consisted of the
Acting Executive Director for Operations. SW., Renton, WA. For information on
following actions:
[FR Doc. 2016–25409 Filed 10–24–16; 8:45 am] the availability of this material at the
—In-service installation of an internal
BILLING CODE 7575–01–P FAA, call 425–227–1221. reinforcing strap on related junction
Examining the AD Docket required by DGAC [Direction Générale de
l’Aviation Civile (DGAC)] France AD 1999–
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on 448–126(B) and AD 2001–070(B),
the Internet at http:// —retrofit improvement of internal reinforcing
Federal Aviation Administration www.regulations.gov by searching for strap fatigue life through recommended
and locating Docket No. FAA–2016– Airbus Service Bulletin (SB) A330–53–
14 CFR Part 39 9192; or in person at the Docket 3145, and
Management Facility between 9 a.m. —new design in production through Airbus
[Docket No. FAA–2016–9192; Directorate modification 44360.
and 5 p.m., Monday through Friday,
Identifier 2016–NM–038–AD] The aeroplanes listed in the Applicability
except Federal holidays. The AD docket
section of this AD are all aeroplanes post-
RIN 2120–AA64 contains this proposed AD, the mod 44360 and pre-mod 55792 (fuselage
regulatory evaluation, any comments reinforcement at FR40 in production).
Airworthiness Directives; Airbus received, and other information. The Recently, during embodiment of a FR40
Airplanes street address for the Docket Operations web repair on an A330 aeroplane and during
AGENCY: Federal Aviation office (telephone 800–647–5527) is in FR40 keel beam fitting replacement on an
the ADDRESSES section. Comments will A340 aeroplane, the internal strap was
Administration (FAA), DOT.
be available in the AD docket shortly removed and rototest inspection was
ACTION: Notice of proposed rulemaking performed on several holes.
after receipt.
(NPRM). Cracks were found on both left-hand (LH)
FOR FURTHER INFORMATION CONTACT: and right-hand (RH) sides on internal strap,
SUMMARY: We propose to adopt a new Vladimir Ulyanov, Aerospace Engineer, or butt strap, or keel beam fitting, or forward
airworthiness directive (AD) for certain International Branch, ANM–116, fitting FR40 flange.
Airbus Model A330–200, A330–300, Transport Airplane Directorate, FAA, This condition, if not detected and
A340–200, and A340–300 series 1601 Lind Avenue SW., Renton, WA corrected, could lead to crack propagation,
mstockstill on DSK3G9T082PROD with PROPOSALS
airplanes. This proposed AD was 98057–3356; telephone 425–227–1138; possibly resulting in reduced structural
prompted by a report of cracking at fax 425–227–1149. integrity of the fuselage.
For the reasons described above, this
fastener holes located at a certain frame SUPPLEMENTARY INFORMATION: [EASA] AD requires repetitive rototest
on the lower shell panel junction. This inspections of 10 fastener holes located at
proposed AD would require repetitive Comments Invited
FR40 lower shell panel junction on both LH
inspections of certain fastener holes, We invite you to send any written and RH sides, and, depending on findings,
and related investigative and corrective relevant data, views, or arguments about accomplishment of the applicable corrective
actions if necessary. We are proposing this proposed AD. Send your comments actions [which include oversizing, installing
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fasteners and repair; and accomplishment of Related Service Information Under FAA’s Determination and Requirements
applicable related investigative actions, 1 CFR Part 51 of This Proposed AD
which include a rototest inspection for
cracking after oversizing]. We reviewed Airbus Service Bulletin This product has been approved by
A330–53–3215, Revision 01, dated April the aviation authority of another
The compliance time ranges between 17, 2014; and Airbus Service Bulletin country, and is approved for operation
20,000 flight cycles or 65,400 flight in the United States. Pursuant to our
A340–53–4215, Revision 01, dated April
hours and 20,800 flight cycles or 68,300 bilateral agreement with the State of
17, 2014. The service information
flight hours, depending on airplane Design Authority, we have been notified
describes procedures for repetitive of the unsafe condition described in the
utilization and configuration. The rototest inspections of certain fastener
repetitive inspection interval ranges MCAI and service information
holes, and corrective actions if referenced above. We are proposing this
between 14,000 flight cycles or 95,200 necessary. These documents are distinct
flight hours and 24,600 flight cycles or AD because we evaluated all pertinent
since they apply to different airplane information and determined an unsafe
98,700 flight hours, depending on models. This service information is condition exists and is likely to exist or
airplane configuration. You may reasonably available because the develop on other products of these same
examine the MCAI in the AD docket on interested parties have access to it type designs.
the Internet at http:// through their normal course of business
www.regulations.gov by searching for or by the means identified in the Costs of Compliance
and locating Docket No. FAA–2016– ADDRESSES section. We estimate that this proposed AD
9192. affects 41 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection .................. 41 work-hours × $85 per hour = $3,485 per inspection $0 $3,485 $142,885 per inspection
cycle. cycle.
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary repairs that would be proposed inspection. We have no way of that might need these repairs:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair .............................................. 46 work-hours × $85 per hour = $3,910 ................................................... $4,186 $8,096
Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39
Title 49 of the United States Code We determined that this proposed AD Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue would not have federalism implications safety, Incorporation by reference,
rules on aviation safety. Subtitle I, under Executive Order 13132. This Safety.
section 106, describes the authority of proposed AD would not have a
substantial direct effect on the States, on The Proposed Amendment
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more the relationship between the national
Accordingly, under the authority
Government and the States, or on the
detail the scope of the Agency’s delegated to me by the Administrator,
distribution of power and
authority. the FAA proposes to amend 14 CFR part
responsibilities among the various
We are issuing this rulemaking under 39 as follows:
levels of government.
the authority described in ‘‘Subtitle VII, For the reasons discussed above, I PART 39—AIRWORTHINESS
Part A, Subpart III, Section 44701: certify this proposed regulation: DIRECTIVES
General requirements.’’ Under that 1. Is not a ‘‘significant regulatory
section, Congress charges the FAA with action’’ under Executive Order 12866; ■ 1. The authority citation for part 39
promoting safe flight of civil aircraft in 2. Is not a ‘‘significant rule’’ under the continues to read as follows:
air commerce by prescribing regulations DOT Regulatory Policies and Procedures
mstockstill on DSK3G9T082PROD with PROPOSALS
for practices, methods, and procedures (44 FR 11034, February 26, 1979); Authority: 49 U.S.C. 106(g), 40113, 44701.
the Administrator finds necessary for 3. Will not affect intrastate aviation in § 39.13 [Amended]
safety in air commerce. This regulation Alaska; and
is within the scope of that authority 4. Will not have a significant ■ 2. The FAA amends § 39.13 by adding
because it addresses an unsafe condition economic impact, positive or negative, the following new airworthiness
that is likely to exist or develop on on a substantial number of small entities directive (AD):
products identified in this rulemaking under the criteria of the Regulatory Airbus: Docket No. FAA–2016–9192;
action. Flexibility Act. Directorate Identifier 2016–NM–038–AD.
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changes to procedures or tests identified as ADDRESSES: You may send comments by economic, environmental, and energy
RC require approval of an AMOC. any of the following methods: aspects of this proposed AD. We will
(j) Related Information • Federal eRulemaking Portal: Go to consider all comments received by the
(1) Refer to Mandatory Continuing
http://www.regulations.gov. Follow the closing date and may amend this
Airworthiness Information (MCAI) EASA instructions for submitting comments. proposed AD because of those
Airworthiness Directive 2014–0136, dated • Fax: (202) 493–2251. comments.
June 13, 2014, for related information. This • Mail: U.S. Department of We will post all comments we
MCAI may be found in the AD docket on the Transportation, Docket Operations, M– receive, without change, to http://
Internet at http://www.regulations.gov by 30, West Building Ground Floor, Room regulations.gov, including any personal
searching for and locating Docket No. FAA– W12–140, 1200 New Jersey Avenue SE., information you provide. We will also
2016–9192. Washington, DC 20590. post a report summarizing each
(2) For service information identified in • Hand Delivery: U.S. Department of substantive verbal contact we receive
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
Transportation, Docket Operations, M– about this proposed AD.
31707 Blagnac Cedex, France; telephone +33 30, West Building Ground Floor, Room
Discussion
5 61 93 36 96; fax +33 5 61 93 45 80; email W12–140, 1200 New Jersey Avenue SE.,
airworthiness.A330-A340@airbus.com; Washington, DC 20590, between 9 a.m. The European Aviation Safety Agency
Internet http://www.airbus.com. You may and 5 p.m., Monday through Friday, (EASA), which is the Technical Agent
view this service information at the FAA, except Federal holidays. for the Member States of the European
Transport Airplane Directorate, 1601 Lind For service information identified in Community, has issued AD No. 2016–
Avenue SW., Renton, WA. For information this proposed AD, contact Diamond 0156, dated August 2, 2016 (referred to
on the availability of this material at the Aircraft Industries GmbH, N.A. Otto- after this as ‘‘the MCAI’’), to correct an
FAA, call 425–227–1221. unsafe condition for the specified
Stra+e 5, A–2700 Wiener Neustadt,
Issued in Renton, Washington, on October Austria, telephone: +43 2622 26700; fax: products. The MCAI states:
12, 2016. +43 2622 26780; email: office@ Two cases were reported of uncommanded
Michael Kaszycki, diamond-air.at; Internet: http:// engine in-flight shutdown (IFSD) on DA 42
Acting Manager, Transport Airplane www.diamondaircraft.com. You may aeroplanes. Subsequent investigations
Directorate, Aircraft Certification Service. review this referenced service identified these occurrences were due to
information at the FAA, Small Airplane failure of the propeller regulating valve,
[FR Doc. 2016–25352 Filed 10–24–16; 8:45 am]
Directorate, 901 Locust, Kansas City, caused by hot exhaust gases coming from
BILLING CODE 4910–13–P fractured engine exhaust pipes. The initiating
Missouri 64106. For information on the
cracks on the exhaust pipes were not
availability of this material at the FAA, detected during previous inspections, since
DEPARTMENT OF TRANSPORTATION call (816) 329–4148. those exhaust pipes are equipped with non-
Examining the AD Docket removable heat shields that do not allow
Federal Aviation Administration inspection for certain sections of the exhaust
You may examine the AD docket on pipe.
14 CFR Part 39 the Internet at http:// This condition, if not corrected, could lead
www.regulations.gov by searching for to further cases of IFSD or overheat damage,
[Docket No. FAA–2016–9317; Directorate possibly resulting in a forced landing, with
and locating Docket No. FAA–2016–
Identifier 2016–CE–029–AD] consequent damage to the aeroplane and
9317; or in person at the Docket
RIN 2120–AA64 Management Facility between 9 a.m. injury to occupants.
To address this potential unsafe condition,
and 5 p.m., Monday through Friday, Diamond Aircraft Industries (DAI) developed
Airworthiness Directives; Diamond except Federal holidays. The AD docket an exhaust pipe without a directly attached
Aircraft Industries GmbH Airplanes contains this proposed AD, the integral heat shield that allows visual
AGENCY: Federal Aviation regulatory evaluation, any comments inspection over the entire exhaust pipe
Administration (FAA), Department of received, and other information. The length. DAI issued Mandatory Service
Transportation (DOT). street address for the Docket Office Bulletin (MSB) 42–120 and relevant Working
(telephone (800) 647–5527) is in the Instruction (WI) WI–MSB 42–120, providing
ACTION: Notice of proposed rulemaking instructions to install the modified exhaust
ADDRESSES section. Comments will be
(NPRM). pipes. As an interim measure, an additional
available in the AD docket shortly after
bracket was designed to hold the exhaust
SUMMARY: We propose to adopt a new receipt. pipe in place in case of a pipe fracture.
airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT: For the reasons described above, this AD
Diamond Aircraft Industries GmbH Mike Kiesov, Aerospace Engineer, FAA, requires replacement of the exhaust pipes
Model DA 42 airplanes. This proposed Small Airplane Directorate, 901 Locust, with pipes having new design, and prohibits
AD results from mandatory continuing Room 301, Kansas City, Missouri 64106; (re)installation of the previous design pipes.
airworthiness information (MCAI) telephone: (816) 329–4144; fax: (816) You may examine the MCAI on the
originated by an aviation authority of 329–4090; email: mike.kiesov@faa.gov. Internet at http://www.regulations.gov
another country to identify and correct SUPPLEMENTARY INFORMATION: by searching for and locating Docket No.
an unsafe condition on an aviation FAA–2016–9317.
product. The MCAI describes the unsafe Comments Invited
condition as an uncommanded engine We invite you to send any written Related Service Information Under 1
mstockstill on DSK3G9T082PROD with PROPOSALS
shutdown during flight due to failure of relevant data, views, or arguments about CFR Part 51
the propeller regulating valve caused by this proposed AD. Send your comments Diamond Aircraft Industries GmbH
hot exhaust gases escaping from to an address listed under the has issued Mandatory Service Bulletin
fractured engine exhaust pipes. We are ADDRESSES section. Include ‘‘Docket No. MSB 42–120, dated June 24, 2016, and
issuing this AD to correct the unsafe FAA–2016–9317; Directorate Identifier Work Instruction WI–MSB 42–120,
condition on these products. 2016–CE–029–AD’’ at the beginning of dated June 24, 2016. In combination,
DATES: We must receive comments on your comments. We specifically invite this service information describes
this proposed AD by December 9, 2016. comments on the overall regulatory, procedures for replacing the exhaust
VerDate Sep<11>2014 16:53 Oct 24, 2016 Jkt 241001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\25OCP1.SGM 25OCP1](https://thefederalregister.org/doc/81_FR_73563/page/4.svg)
Document Created: 2018-02-13 16:38:28
Document Modified: 2018-02-13 16:38:28
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by December 9, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 81 FR 73357 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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