82 FR 28030 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 117 (June 20, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 117 (June 20, 2017)
| Page Range | 28030-28033 | |
| FR Document | 2017-12613 |
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)] [Proposed Rules] [Pages 28030-28033] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-12613] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0560; Directorate Identifier 2016-NM-172-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 all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. This proposed AD was prompted by reports of cracking in the drainage holes on the lower skin panel in the center wing box between frames (FR) 42 and FR 46. This proposed AD would require repetitive rotating probe inspections for cracking of the trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 4, 2017. 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 [[Page 28031]] 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--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; 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-2017- 0560; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; 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-2017-0560; Directorate Identifier 2016-NM-172-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage (WFD). It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. On April 22, 2011, we issued AD 2011-10-06, Amendment 39-16687 (76 FR 27227, May 11, 2011) (``AD 2011-10-06''), applicable to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. That AD currently requires: Cold working of trellis boom drainage holes; Repetitive detailed or rotating probe inspections for cracking in the drainage holes on the lower skin panel in the center wing box between FR 42 and FR 46, and corrective actions if necessary, including repair; and Repetitive eddy current inspections for cracking of the upper corner angle fitting and the vertical tee fitting at left and right FR 40, and corrective actions if necessary, including repair and replacement of the internal angle fitting. AD 2011-10-06 was prompted by European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, AD 2009-0057 to identify and correct an unsafe condition. The identified unsafe condition is cracking of trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, which could result in reduced structural integrity of the wings. Since issuance of AD 2011-10-06, EASA has issued EASA AD 2016-0196, dated September 30, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. The MCAI states: DGAC France issued AD F-1992-106-132R7 to require certain inspections and modifications which addressed JAR/FAR [Joint Aviation Requirements/Federal Aviation Regulations] 25-571 requirements, related to damage-tolerance and fatigue evaluation of structure. Following the Extended Design Service Goal activities as part of the Structure Task Group for the Airbus A310 program, EASA published AD 2007-0053, which replaced DGAC France AD F-1992-106- 132R7. After EASA issued AD 2007-0053R1, the thresholds and the intervals of Airbus Service Bulletins (SB) A310-57-2050 and A310-57- 2064 were updated, prompting EASA to issue AD 2009-0057 [which corresponds to FAA AD 2011-10-06] and [EASA] AD 2007-0053 was revised (R2) accordingly. EASA AD 2009-0057 also required the accomplishment of the actions specified in Airbus SB A310-57-2048 at Revision 01. After EASA issued AD 2009-0057, in the frame of the Widespread Fatigue Damage campaign, new analysis has indicated the need for additional work included in Revision 03 of Airbus SB A310-57-2050. [[Page 28032]] For the reason described above, this new [EASA] AD retains the requirements of EASA AD 2009-0057, which is superseded, and requires inspection and corrective actions as specified in Airbus SB A310-57- 2050 Revision 04. Required actions include a repetitive rotating probe inspection for cracking of certain holes in the stringers bottom, inner pumps, and the trellis boom; and corrective actions, i.e., repair of holes where cracks are discovered. The compliance times vary depending on airplane configuration. The earliest initial inspection compliance time is 11,400 total flight cycles or 57,300 total flight hours, whichever occurs first. The latest initial compliance time is 38,700 total flight cycles or 77,500 total flight hours, whichever occurs first. The shortest repetitive interval is 6,200 flight cycles or 31,200 flight hours, whichever occurs first. 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-2017- 0560. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015. This service information describes procedures for repetitive rotating probe inspections for cracking of the trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, and corrective actions. 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 the same type design. This proposed AD would not supersede AD 2011-10-06. 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 rotating probe inspections for cracking of the trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, and corrective actions, if necessary. Accomplishment of the proposed actions would then terminate the actions required by paragraph (h) of AD 2011-10-06. Costs of Compliance We estimate that this proposed AD affects 8 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........................ 84 work-hours x $85 per hour $5,890 $13,030 $104,240 = $7,140. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions 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. 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-2017-0560; Directorate Identifier 2016-NM- 172-AD. (a) Comments Due Date We must receive comments by August 4, 2017. (b) Affected ADs This AD affects AD 2011-10-06, Amendment 39-16687 (76 FR 27227, May 11, 2011) (``AD 2011-10-06''). (c) Applicability This AD applies to Airbus Model A310-203, -204, -221, -222, - 304, -322, -324, and -325 airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. [[Page 28033]] (e) Reason This AD was prompted by reports of cracking in the drainage holes on the lower skin panel in the center wing box between frames (FR) 42 and FR 46. We are issuing this AD to detect and correct cracking of trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, which could result in reduced structural integrity of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Rotating Probe Inspections and Corrective Actions Except as provided by paragraph (h)(1) of this AD, before exceeding the applicable threshold or grace period, whichever occurs later, as defined in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015, accomplish the rotating probe inspection for cracking of the trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, as applicable, and do all applicable corrective actions, as specified in, and in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015, except as required by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed those defined in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015. (h) Exceptions to Service Information (1) Where Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015, specifies a grace period ``after receipt of the Service Bulletin without exceeding previous Service Bulletin revision values,'' this AD requires compliance within the specified grace period after the effective date of this AD. (2) Where Airbus Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (l)(2) of this AD. (i) No Terminating Action for Inspections Accomplishing corrective actions on an airplane as required by paragraph (g) or (h)(2) of this AD does not constitute terminating action for the repetitive actions required by paragraph (g) of this AD. (j) Terminating Action Accomplishment of the initial inspection required by paragraph (g) of this AD constitutes terminating action for the actions required by paragraph (h) of AD 2011-10-06. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information specified in Airbus Service Bulletin A310-57-2050, Revision 03, dated December 19, 2014. (l) 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 manager of the International Branch, 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: Except as required by paragraph (h)(2) 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 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 (h)(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 changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0196, dated September 30, 2016, 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-2017-0560. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-2125; fax: 425-227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; 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 June 9, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-12613 Filed 6-19-17; 8:45 am] BILLING CODE 4910-13-P
![28030 Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
(4) Will not have a significant (3) If the measured wear and/or fretting of information in paragraph (j)(3) of this
economic impact, positive or negative, any Z gap contact area is greater than 0.005 proposed AD.
on a substantial number of small entities inch, replace the LPT2 rotor assembly with (3) For service information identified in
a part eligible for installation before further this proposed AD, contact Honeywell
under the criteria of the Regulatory
flight. International Inc., 111 S 34th Street, Phoenix,
Flexibility Act. (4) Do the following actions within 200 AZ 85034–2802; phone: 800–601–3099;
List of Subjects in 14 CFR Part 39 hours time in service after the effective date Internet: https://
of this AD: myaerospace.honeywell.com/wps/portal/!ut/.
Air transportation, Aircraft, Aviation (i) Using a borescope make a clear digital (4) You may view this service information
safety, Incorporation by reference, image of the Z gap contact area at the blade at the FAA, Engine & Propeller Directorate,
Safety. tip shroud of the 62 LPT2 rotor blades. 1200 District Avenue, Burlington, MA. For
(ii) Identify the three Z gap contact areas information on the availability of this
The Proposed Amendment with the greatest amount of wear and/or material at the FAA, call 781–238–7125.
Accordingly, under the authority fretting. Issued in Burlington, Massachusetts, on
delegated to me by the Administrator, (iii) Record the blade position on the LPT2 June 13, 2017.
rotor assembly and the measured wear of the
the FAA proposes to amend 14 CFR part Robert J. Ganley,
three Z gap contact areas with the greatest
39 as follows: amount of wear and/or fretting. Acting Manager, Engine & Propeller
(iv) Send the results to Honeywell at Directorate, Aircraft Certification Service.
PART 39—AIRWORTHINESS engine.reliability@honeywell.com within 30 [FR Doc. 2017–12561 Filed 6–19–17; 8:45 am]
DIRECTIVES days after completing these actions. BILLING CODE 4910–13–P
■ 1. The authority citation for part 39 (g) Credit for Previous Actions
continues to read as follows: You may take credit for the actions DEPARTMENT OF TRANSPORTATION
required by paragraphs (f)(1) and (4) of this
Authority: 49 U.S.C. 106(g), 40113, 44701.
AD, if you performed these actions before the Federal Aviation Administration
§ 39.13 [Amended] effective date of this AD using Honeywell SB
AS907–72–9067, Revision 0, dated December
■ 2. The FAA amends § 39.13 by adding 12, 2016. 14 CFR Part 39
the following new airworthiness [Docket No. FAA–2017–0560; Directorate
directive (AD): (h) Paperwork Reduction Act Burden
Statement Identifier 2016–NM–172–AD]
Honeywell International Inc.: Docket No.
A federal agency may not conduct or RIN 2120–AA64
FAA–2017–0034; Directorate Identifier
sponsor, and a person is not required to
2016–NE–32–AD.
respond to, nor shall a person be subject to Airworthiness Directives; Airbus
(a) Comments Due Date a penalty for failure to comply with a Airplanes
We must receive comments by August 4, collection of information subject to the
requirements of the Paperwork Reduction AGENCY: Federal Aviation
2017.
Act unless that collection of information Administration (FAA), DOT.
(b) Affected ADs displays a current valid OMB Control ACTION: Notice of proposed rulemaking
None. Number. The OMB Control Number for this (NPRM).
information collection is 2120–0056. Public
(c) Applicability reporting for this collection of information is SUMMARY: We propose to adopt a new
This AD applies to Honeywell estimated to be approximately 5 minutes per airworthiness directive (AD) for all
International Inc. (Honeywell) AS907–1–1A response, including the time for reviewing Airbus Model A310–203, –204, –221,
turbofan engines with second stage low- instructions, completing and reviewing the
–222, –304, –322, –324, and –325
pressure turbine (LPT2) rotor blades, part collection of information. All responses to
this collection of information are mandatory. airplanes. This proposed AD was
number (P/N) 3035602–1, installed.
Comments concerning the accuracy of this prompted by reports of cracking in the
(d) Subject burden and suggestions for reducing the drainage holes on the lower skin panel
Joint Aircraft System Component (JASC) burden should be directed to the FAA at: 800 in the center wing box between frames
Code 7250, Turbine Section. Independence Ave. SW., Washington, DC (FR) 42 and FR 46. This proposed AD
20591, Attn: Information Collection would require repetitive rotating probe
(e) Unsafe Condition Clearance Officer, AES–200. inspections for cracking of the trellis
This AD was prompted by reports of loss boom drainage holes, the holes in the
of power due to failure of the LPT2 blade. We (i) Alternative Methods of Compliance
are issuing this AD to prevent failure of the (AMOCs) stringers bottom, and the holes of the
LPT2 blades, failure of one or more engines, The Manager, Los Angeles Aircraft inner pump, and corrective actions if
and loss of the airplane. Certification Office, FAA, may approve necessary. We are proposing this AD to
AMOCs for this AD. Use the procedures address the unsafe condition on these
(f) Compliance found in 14 CFR 39.19 to make your request. products.
Comply with this AD within the
compliance times specified, unless already (j) Related Information DATES: We must receive comments on
done. (1) For more information about this this proposed AD by August 4, 2017.
(1) For LPT2 rotor blades, P/N 3035602–1 proposed AD, contact Joseph Costa, ADDRESSES: You may send comments,
that have more than 8,000 hours since new Aerospace Engineer, Los Angeles Aircraft
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
using the procedures found in 14 CFR
on the effective date of this AD, perform a Certification Office, FAA, Transport Airplane 11.43 and 11.45, by any of the following
one-time borescope inspection for wear of the Directorate, 3960 Paramount Blvd., methods:
Z gap contact area at the blade tip shroud for Lakewood, CA 90712–4137; phone: 562–627– • Federal eRulemaking Portal: Go to
each of the 62 LPT2 rotor blades within 200 5246; fax: 562–627–5210; email:
hours time in service after the effective date joseph.costa@faa.gov.
http://www.regulations.gov. Follow the
of this AD. (2) Honeywell SBs AS907–72–9067, instructions for submitting comments.
(2) Use the Accomplishment Instructions, Revision 0, dated December 12, 2016 and • Fax: 202–493–2251.
Paragraph 3.B.(1), of Honeywell Service AS907–72–9067, Revision 1, dated March 20, • Mail: U.S. Department of
Bulletin (SB) AS907–72–9067, Revision 1, 2017, can be obtained from Honeywell Transportation, Docket Operations, M–
dated March 20, 2017, to do the inspection. International Inc., using the contact 30, West Building Ground Floor, Room
VerDate Sep<11>2014 17:28 Jun 19, 2017 Jkt 241001 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 E:\FR\FM\20JNP1.SGM 20JNP1](https://thefederalregister.org/doc/82_FR_28147/page/1.svg)
![Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules 28031
W12–140, 1200 New Jersey Avenue SE., Discussion regarding the LOV applicable to their
Washington, DC 20590. Fatigue damage can occur locally, in airplanes.
• Hand Delivery: Deliver to Mail small areas or structural design details, On April 22, 2011, we issued AD
address above between 9 a.m. and 5 2011–10–06, Amendment 39–16687 (76
or globally, in widespread areas.
p.m., Monday through Friday, except FR 27227, May 11, 2011) (‘‘AD 2011–
Multiple-site damage is widespread
Federal holidays. 10–06’’), applicable to all Airbus Model
damage that occurs in a large structural
For service information identified in A310–203, –204, –221, –222, –304,
this NPRM, contact Airbus SAS, element such as a single rivet line of a
–322, –324, and –325 airplanes. That
Airworthiness Office—EAW, 1 Rond lap splice joining two large skin panels.
AD currently requires:
Point Maurice Bellonte, 31707 Blagnac Widespread damage can also occur in • Cold working of trellis boom
Cedex, France; telephone: +33 5 61 93 multiple elements such as adjacent drainage holes;
36 96; fax: +33 5 61 93 44 51; email: frames or stringers. Multiple-site • Repetitive detailed or rotating probe
account.airworth-eas@airbus.com; damage and multiple-element damage inspections for cracking in the drainage
Internet: http://www.airbus.com. You cracks are typically too small initially to holes on the lower skin panel in the
may view this referenced service be reliably detected with normal center wing box between FR 42 and FR
information at the FAA, Transport inspection methods. Without 46, and corrective actions if necessary,
Airplane Directorate, 1601 Lind Avenue intervention, these cracks will grow, including repair; and
SW., Renton, WA. For information on and eventually compromise the • Repetitive eddy current inspections
the availability of this material at the structural integrity of the airplane. This for cracking of the upper corner angle
FAA, call 425–227–1221. condition is known as widespread fitting and the vertical tee fitting at left
fatigue damage (WFD). It is associated and right FR 40, and corrective actions
Examining the AD Docket with general degradation of large areas if necessary, including repair and
You may examine the AD docket on of structure with similar structural replacement of the internal angle fitting.
the Internet at http:// details and stress levels. As an airplane AD 2011–10–06 was prompted by
www.regulations.gov by searching for ages, WFD will likely occur, and will European Aviation Safety Agency
and locating Docket No. FAA–2017– certainly occur if the airplane is (EASA), which is the Technical Agent
0560; or in person at the Docket operated long enough without any for the Member States of the European
Management Facility between 9 a.m. intervention. Union, AD 2009–0057 to identify and
and 5 p.m., Monday through Friday, The FAA’s WFD final rule (75 FR correct an unsafe condition. The
except Federal holidays. The AD docket 69746, November 15, 2010) became identified unsafe condition is cracking
contains this proposed AD, the effective on January 14, 2011. The WFD of trellis boom drainage holes, the holes
regulatory evaluation, any comments rule requires certain actions to prevent in the stringers bottom, and the holes of
received, and other information. The structural failure due to WFD the inner pump, which could result in
street address for the Docket Operations throughout the operational life of reduced structural integrity of the
office (telephone: 800–647–5527) is in certain existing transport category wings.
the ADDRESSES section. Comments will airplanes and all of these airplanes that Since issuance of AD 2011–10–06,
be available in the AD docket shortly will be certificated in the future. For EASA has issued EASA AD 2016–0196,
after receipt. existing and future airplanes subject to dated September 30, 2016 (referred to
FOR FURTHER INFORMATION CONTACT: Dan the WFD rule, the rule requires that after this as the Mandatory Continuing
Rodina, Aerospace Engineer, DAHs establish a limit of validity (LOV) Airworthiness Information, or ‘‘the
International Branch, ANM–116, of the engineering data that support the MCAI’’), to correct an unsafe condition
Transport Airplane Directorate, FAA, structural maintenance program. for all Airbus Model A310–203, –204,
1601 Lind Avenue SW., Renton, WA Operators affected by the WFD rule may –221, –222, –304, –322, –324, and –325
98057–3356; telephone: 425–227–2125; not fly an airplane beyond its LOV, airplanes. The MCAI states:
fax: 425–227–1149. unless an extended LOV is approved. DGAC France issued AD F–1992–106–
SUPPLEMENTARY INFORMATION: The WFD rule (75 FR 69746, 132R7 to require certain inspections and
November 15, 2010) does not require modifications which addressed JAR/FAR
Comments Invited identifying and developing maintenance [Joint Aviation Requirements/Federal
We invite you to send any written actions if the DAHs can show that such Aviation Regulations] 25–571 requirements,
related to damage-tolerance and fatigue
relevant data, views, or arguments about actions are not necessary to prevent
evaluation of structure. Following the
this proposed AD. Send your comments WFD before the airplane reaches the Extended Design Service Goal activities as
to an address listed under the LOV. Many LOVs, however, do depend part of the Structure Task Group for the
ADDRESSES section. Include ‘‘Docket No. on accomplishment of future Airbus A310 program, EASA published AD
FAA–2017–0560; Directorate Identifier maintenance actions. As stated in the 2007–0053, which replaced DGAC France AD
2016–NM–172–AD’’ at the beginning of WFD rule, any maintenance actions F–1992–106–132R7.
your comments. We specifically invite necessary to reach the LOV will be After EASA issued AD 2007–0053R1, the
comments on the overall regulatory, mandated by airworthiness directives thresholds and the intervals of Airbus
Service Bulletins (SB) A310–57–2050 and
economic, environmental, and energy through separate rulemaking actions. A310–57–2064 were updated, prompting
aspects of this proposed AD. We will In the context of WFD, this action is EASA to issue AD 2009–0057 [which
consider all comments received by the necessary to enable DAHs to propose
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
corresponds to FAA AD 2011–10–06] and
closing date and may amend this LOVs that allow operators the longest [EASA] AD 2007–0053 was revised (R2)
proposed AD based on those comments. operational lives for their airplanes, and accordingly. EASA AD 2009–0057 also
We will post all comments we still ensure that WFD will not occur. required the accomplishment of the actions
receive, without change, to http:// This approach allows for an specified in Airbus SB A310–57–2048 at
www.regulations.gov, including any implementation strategy that provides Revision 01.
After EASA issued AD 2009–0057, in the
personal information you provide. We flexibility to DAHs in determining the frame of the Widespread Fatigue Damage
will also post a report summarizing each timing of service information campaign, new analysis has indicated the
substantive verbal contact we receive development (with FAA approval), need for additional work included in
about this proposed AD. while providing operators with certainty Revision 03 of Airbus SB A310–57–2050.
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![28032 Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
For the reason described above, this new Related Service Information Under 1 referenced above. We are proposing this
[EASA] AD retains the requirements of EASA CFR Part 51 AD because we evaluated all pertinent
AD 2009–0057, which is superseded, and information and determined an unsafe
requires inspection and corrective actions as We reviewed Airbus Service Bulletin
specified in Airbus SB A310–57–2050 A310–57–2050, Revision 04, dated condition exists and is likely to exist or
Revision 04. March 13, 2015. This service develop on other products the same
information describes procedures for type design.
Required actions include a repetitive
rotating probe inspection for cracking of repetitive rotating probe inspections for This proposed AD would not
certain holes in the stringers bottom, cracking of the trellis boom drainage supersede AD 2011–10–06. Rather, we
inner pumps, and the trellis boom; and holes, the holes in the stringers bottom, have determined that a stand-alone AD
corrective actions, i.e., repair of holes and the holes of the inner pump, and would be more appropriate to address
where cracks are discovered. corrective actions. This service the changes in the MCAI. This proposed
The compliance times vary depending information is reasonably available AD would require repetitive rotating
on airplane configuration. The earliest because the interested parties have probe inspections for cracking of the
initial inspection compliance time is access to it through their normal course trellis boom drainage holes, the holes in
11,400 total flight cycles or 57,300 total of business or by the means identified the stringers bottom, and the holes of
flight hours, whichever occurs first. The in the ADDRESSES section. the inner pump, and corrective actions,
latest initial compliance time is 38,700 if necessary. Accomplishment of the
FAA’s Determination and Requirements
total flight cycles or 77,500 total flight proposed actions would then terminate
of This Proposed AD
hours, whichever occurs first. The the actions required by paragraph (h) of
shortest repetitive interval is 6,200 flight This product has been approved by AD 2011–10–06.
cycles or 31,200 flight hours, whichever the aviation authority of another
occurs first. country, and is approved for operation Costs of Compliance
You may examine the MCAI in the in the United States. Pursuant to our
AD docket on the Internet at http:// bilateral agreement with the State of We estimate that this proposed AD
www.regulations.gov by searching for Design Authority, we have been notified affects 8 airplanes of U.S. registry.
and locating Docket No. FAA–2017– of the unsafe condition described in the We estimate the following costs to
0560. MCAI and service information comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection ................... 84 work-hours × $85 per hour = $7,140 ............................................. $5,890 $13,030 $104,240
We have received no definitive data under Executive Order 13132. This PART 39—AIRWORTHINESS
that would enable us to provide cost proposed AD would not have a DIRECTIVES
estimates for the on-condition actions substantial direct effect on the States, on
specified in this proposed AD. the relationship between the national ■ 1. The authority citation for part 39
Government and the States, or on the continues to read as follows:
Authority for This Rulemaking
distribution of power and
Title 49 of the United States Code responsibilities among the various Authority: 49 U.S.C. 106(g), 40113, 44701.
specifies the FAA’s authority to issue levels of government.
rules on aviation safety. Subtitle I, § 39.13 [Amended]
For the reasons discussed above, I
section 106, describes the authority of certify this proposed regulation: ■ 2. The FAA amends § 39.13 by adding
the FAA Administrator. ‘‘Subtitle VII: 1. Is not a ‘‘significant regulatory the following new airworthiness
Aviation Programs,’’ describes in more action’’ under Executive Order 12866; directive (AD):
detail the scope of the Agency’s 2. Is not a ‘‘significant rule’’ under the
authority. Airbus: Docket No. FAA–2017–0560;
DOT Regulatory Policies and Procedures
We are issuing this rulemaking under Directorate Identifier 2016–NM–172–AD.
(44 FR 11034, February 26, 1979);
the authority described in ‘‘Subtitle VII, 3. Will not affect intrastate aviation in (a) Comments Due Date
Part A, Subpart III, Section 44701: Alaska; and We must receive comments by August 4,
General requirements.’’ Under that 4. Will not have a significant 2017.
section, Congress charges the FAA with economic impact, positive or negative,
promoting safe flight of civil aircraft in on a substantial number of small entities (b) Affected ADs
air commerce by prescribing regulations under the criteria of the Regulatory This AD affects AD 2011–10–06,
for practices, methods, and procedures Flexibility Act. Amendment 39–16687 (76 FR 27227, May 11,
the Administrator finds necessary for 2011) (‘‘AD 2011–10–06’’).
List of Subjects in 14 CFR Part 39
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
safety in air commerce. This regulation
is within the scope of that authority Air transportation, Aircraft, Aviation (c) Applicability
because it addresses an unsafe condition safety, Incorporation by reference, This AD applies to Airbus Model A310–
that is likely to exist or develop on Safety. 203, –204, –221, –222, –304, –322, –324, and
products identified in this rulemaking –325 airplanes, certificated in any category,
The Proposed Amendment all serial numbers.
action.
Accordingly, under the authority
Regulatory Findings (d) Subject
delegated to me by the Administrator,
We determined that this proposed AD the FAA proposes to amend 14 CFR part Air Transport Association (ATA) of
would not have federalism implications 39 as follows: America Code 57, Wings.
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![Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules 28033
(e) Reason specified in Airbus Service Bulletin A310– telephone: +33 5 61 93 36 96; fax: +33 5 61
This AD was prompted by reports of 57–2050, Revision 03, dated December 19, 93 44 51; email: account.airworth-eas@
cracking in the drainage holes on the lower 2014. airbus.com; Internet: http://www.airbus.com.
skin panel in the center wing box between You may view this service information at the
(l) Other FAA AD Provisions
frames (FR) 42 and FR 46. We are issuing this FAA, Transport Airplane Directorate, 1601
AD to detect and correct cracking of trellis The following provisions also apply to this Lind Avenue SW., Renton, WA. For
boom drainage holes, the holes in the AD: information on the availability of this
stringers bottom, and the holes of the inner (1) Alternative Methods of Compliance material at the FAA, call 425 227–1221.
pump, which could result in reduced (AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane Issued in Renton, Washington, on June 9,
structural integrity of the wings. 2017.
Directorate, FAA, has the authority to
(f) Compliance approve AMOCs for this AD, if requested Michael Kaszycki,
Comply with this AD within the using the procedures found in 14 CFR 39.19. Acting Manager, Transport Airplane
compliance times specified, unless already In accordance with 14 CFR 39.19, send your Directorate, Aircraft Certification Service.
done. request to your principal inspector or local [FR Doc. 2017–12613 Filed 6–19–17; 8:45 am]
Flight Standards District Office, as
(g) Rotating Probe Inspections and appropriate. If sending information directly
BILLING CODE 4910–13–P
Corrective Actions to the manager of the International Branch,
Except as provided by paragraph (h)(1) of send it to the attention of the person
this AD, before exceeding the applicable identified in paragraph (m)(2) of this AD. DEPARTMENT OF TRANSPORTATION
threshold or grace period, whichever occurs Information may be emailed to: 9-ANM-116-
later, as defined in paragraph 1.E., AMOC-REQUESTS@faa.gov. Before using Federal Aviation Administration
‘‘Compliance,’’ of Airbus Service Bulletin any approved AMOC, notify your appropriate
A310–57–2050, Revision 04, dated March 13, principal inspector, or lacking a principal 14 CFR Part 71
2015, accomplish the rotating probe inspector, the manager of the local flight
inspection for cracking of the trellis boom [Docket No. FAA–2017–0458; Airspace
standards district office/certificate holding Docket No. 17–ASW–8]
drainage holes, the holes in the stringers district office.
bottom, and the holes of the inner pump, as (2) Contacting the Manufacturer: Except as
applicable, and do all applicable corrective Proposed Amendment of Class E
required by paragraph (h)(2) of this AD: For
actions, as specified in, and in accordance any requirement in this AD to obtain
Airspace; Canadian, TX; and Wheeler,
with the Accomplishment Instructions of corrective actions from a manufacturer, the TX
Airbus Service Bulletin A310–57–2050, action must be accomplished using a method
Revision 04, dated March 13, 2015, except as AGENCY: Federal Aviation
approved by the Manager, International
required by paragraph (h)(2) of this AD. Do Branch, ANM–116, Transport Airplane
Administration (FAA), DOT.
all applicable corrective actions before Directorate, FAA; or the European Aviation ACTION: Notice of proposed rulemaking
further flight. Repeat the inspection Safety Agency (EASA); or Airbus’s EASA (NPRM).
thereafter at intervals not to exceed those Design Organization Approval (DOA). If
defined in paragraph 1.E., ‘‘Compliance,’’ of approved by the DOA, the approval must SUMMARY: This action proposes to
Airbus Service Bulletin A310–57–2050, include the DOA-authorized signature. modify Class E airspace extending
Revision 04, dated March 13, 2015. (3) Required for Compliance (RC): Except upward from 700 feet above the surface
(h) Exceptions to Service Information as required by paragraph (h)(2) of this AD: If at Hemphill County Airport, Canadian,
any service information contains procedures TX, and Wheeler Municipal Airport,
(1) Where Airbus Service Bulletin A310– or tests that are identified as RC, those
57–2050, Revision 04, dated March 13, 2015, Wheeler, TX. The FAA is proposing this
procedures and tests must be done to comply
specifies a grace period ‘‘after receipt of the action due to the decommissioning of
with this AD; any procedures or tests that are
Service Bulletin without exceeding previous
not identified as RC are recommended. Those the Sayre co-located VHF
Service Bulletin revision values,’’ this AD omnidirectional range and tactical air
procedures and tests that are not identified
requires compliance within the specified navigation system (VORTAC) facility,
as RC may be deviated from using accepted
grace period after the effective date of this which provided navigation guidance for
methods in accordance with the operator’s
AD.
(2) Where Airbus Service Bulletin A310–
maintenance or inspection program without the instrument procedures to these
obtaining approval of an AMOC, provided airports. The VORTAC is being
57–2050, Revision 04, dated March 13, 2015,
the procedures and tests identified as RC can decommissioned as part of the VHF
specifies to contact Airbus for appropriate
be done and the airplane can be put back in omnidirectional range (VOR) Minimum
action, and specifies that action as ‘‘RC’’
an airworthy condition. Any substitutions or
(Required for Compliance): Before further Operational Network (MON) Program.
flight, accomplish corrective actions in changes to procedures or tests identified as
RC require approval of an AMOC. This action would enhance the safety
accordance with the procedures specified in and management of instrument flight
paragraph (l)(2) of this AD. (m) Related Information rules (IFR) operations at these airports.
(i) No Terminating Action for Inspections (1) Refer to Mandatory Continuing Additionally, the geographic
Accomplishing corrective actions on an Airworthiness Information (MCAI) EASA AD coordinates of the airports would be
airplane as required by paragraph (g) or (h)(2) 2016–0196, dated September 30, 2016, for adjusted to coincide with the FAA’s
of this AD does not constitute terminating related information. This MCAI may be aeronautical database.
action for the repetitive actions required by found in the AD docket on the Internet at
http://www.regulations.gov by searching for DATES: Comments must be received on
paragraph (g) of this AD. or before August 4, 2017.
and locating Docket No. FAA–2017–0560.
(j) Terminating Action (2) For more information about this AD, ADDRESSES: Send comments on this
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Accomplishment of the initial inspection contact Dan Rodina, Aerospace Engineer, proposal to the U.S. Department of
required by paragraph (g) of this AD International Branch, ANM–116, Transport Transportation, Docket Operations, 1200
constitutes terminating action for the actions Airplane Directorate, FAA, 1601 Lind New Jersey Avenue SE., West Building
required by paragraph (h) of AD 2011–10–06. Avenue SW., Renton, WA 98057–3356;
Ground Floor, Room W12–140,
telephone: 425–227–2125; fax: 425–227–
(k) Credit for Previous Actions 1149. Washington, DC 20590; telephone (202)
This paragraph provides credit for actions (3) For service information identified in 366–9826, or 1–800–647–5527. You
required by paragraph (g) of this AD, if those this AD, contact Airbus SAS, Airworthiness must identify FAA Docket No. FAA–
actions were performed before the effective Office—EAW, 1 Rond Point Maurice 2017–0458; Airspace Docket No. 17–
date of this AD using the service information Bellonte, 31707 Blagnac Cedex, France; ASW–8 at the beginning of your
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Document Created: 2017-06-20 02:21:10
Document Modified: 2017-06-20 02:21:10
| 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 August 4, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. | |
| FR Citation | 82 FR 28030 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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