82 FR 12407 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 41 (March 3, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 41 (March 3, 2017)
| Page Range | 12407-12410 | |
| FR Document | 2017-03972 |
[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)] [Rules and Regulations] [Pages 12407-12410] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-03972] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-AD; Amendment 39-18812; AD 2017-05-02] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 7, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 6893. 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- 6893; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318- 112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, - 213, -231, and -232 airplanes. The NPRM published in the Federal Register on May 26, 2016 (81 FR 33438). The NPRM was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. The NPRM proposed to require a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0218, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318-112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321- 211, -212, -213, -231, and -232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that wrong aluminum alloy were delivered [[Page 12408]] by a supplier for several structural parts. The results of the investigations highlighted that 0.04% of the stock could be impacted by this wrong material. Structural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-53-1298 and SB A320-53-1299 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one- time Special Detailed Inspection (SDI) [eddy current conductivity measurements] of certain cabin and cargo compartment parts for material identification and, depending on findings, replacement with serviceable parts. 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- 6893. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM One commenter, Jerry Curtis, expressed support for the NPRM. Request To Refer to the Latest Service Information Airbus requested that we refer to the latest service information: Airbus Service Bulletins A320-53-1298 and A320-53-1299, both Revision 01, both dated June 9, 2016. We referred to Airbus Service Bulletins A320-53-1298 and A320-53-1299, both dated February 16, 2015, as the appropriate sources of service information for accomplishing the actions specified in the NPRM. We agree with the request to refer to the latest service information. Airbus Service Bulletins A320-53-1298 and A320-53-1299, both Revision 01, both dated June 9, 2016, include updated information and specify that no additional work is necessary for airplanes modified by the original issue. We have revised this AD to refer to Airbus Service Bulletins A320-53-1298 and A320-53-1299, both Revision 01, both dated June 9, 2016. We have also added credit for actions done before the effective date of this AD using Airbus Service Bulletins A320-53- 1298 and A320-53-1299, both dated February 16, 2015. Request To Correct a Certain Part Number (P/N) Allegiant Air asked if the part number, P/N D5358526421400, in the ninth row of table 1 to paragraphs (g) and (h) of the proposed AD under ``Affected P/N'' is correct. Allegiant Air stated that the affected part number is the same as the acceptable replacement part number. We acknowledge the commenter's concern; however, we have confirmed that both part numbers in the ninth row of table 1 to paragraphs (g) and (h) of this AD are the same and are correct as written. Therefore, we have not changed this AD in this regard. Additional Change to NPRM We have added paragraph (i) to this AD to clarify that no reporting is required. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletins A320-53-1298 and A320-53-1299, both Revision 01, both including Appendixes 01 through 03, both dated June 9, 2016. The service information describes procedures for a one- time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement of any affected part with a serviceable part. These documents are distinct since they apply to different parts of the airplane (cabin and cargo compartment). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 167 airplanes of U.S. registry. We also estimate that it takes about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $14,195, or $85 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. [[Page 12409]] List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2017-05-02 Airbus: Amendment 39-18812; Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-AD. (a) Effective Date This AD is effective April 7, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category; manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 6159 inclusive, 6161 and 6162. (1) Airbus Model A318-112 airplanes. (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes. (3) Airbus Model A320-214, -232, and -233 airplanes. (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a quality control review of the final assembly line which determined that the wrong aluminum alloy was used to manufacture several structural parts. We are issuing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Measurement Within 6 years after the effective date of this AD, but not exceeding 12 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurement (with 60 kilohertz (kHz) and 480 kHz) of the cabin and cargo compartment structural parts identified in the ``Affected P/N'' column of table 1 to paragraphs (g) and (h) of this AD to determine if an incorrect aluminum alloy was used, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320-53-1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cabin parts); and A320-53-1299, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cargo parts). Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/ Installed ------------------------------------------------------------------------ Affected P/N Acceptable replacement P/N Area ------------------------------------------------------------------------ D5347120720000 D5347120720051 Cabin. D5347120720100 D5347120720151 Cabin. D5347120920000 D5347120920051 Cabin. D5347120920100 D5347120920151 Cabin. D5347118820400 D5347118820451 Cabin. D5347717620000 D5347717620051 Cargo. D5357020620000 D5357020620051 Cargo. D5358526421200 D5358526421251 Cargo. D5358526421400 D5358526421400 Cargo. D5358526421000 D5358526421051 Cargo. D5358513120001 D5358513120051 Cargo. ------------------------------------------------------------------------ (h) Replacement If during the inspection required by paragraph (g) of this AD, any affected part having a part number (P/N) specified in table 1 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A-GFAAA, Sheet 02, ``Inspection Flowchart,'' of the applicable service information identified in paragraph (g) of this AD: Before further flight, replace with an acceptable replacement part having a part number specified in table 1 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320-53-1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cabin parts); and A320-53-1299, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016 (for cargo parts). (i) No Reporting Although reporting of inspection results is specified as a ``Required for Compliance'' (RC) action in Airbus Service Bulletins A320-53-1298, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016; and A320-53-1299, Revision 01, including Appendixes 01, 02, and 03, dated June 9, 2016; this AD does not require any report. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1298, dated February 16, 2015; and Airbus Service Bulletin A320-53-1299, dated February 16, 2015; as applicable. (k) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 provided by paragraph (i) 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0218, dated November 3, 2015, for related information. This MCAI may be found in the AD docket on the Internet at [[Page 12410]] http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6893. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-53-1298, Revision 01, including Appendixes 01 through 03, dated June 9, 2016. (ii) Airbus Service Bulletin A320-53-1299, Revision 01, including Appendixes 01 through 03, dated June 9, 2016. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet: http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on February 16, 2017. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-03972 Filed 3-2-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 12407
telephone: (816) 329–4059; fax: (816) 329– DEPARTMENT OF TRANSPORTATION 6893; or in person at the Docket
4090; email: doug.rudolph@faa.gov. Before Management Facility between 9 a.m.
using any approved AMOC on any airplane Federal Aviation Administration and 5 p.m., Monday through Friday,
to which the AMOC applies, notify your except Federal holidays. The AD docket
appropriate principal inspector (PI) in the 14 CFR Part 39 contains this AD, the regulatory
FAA Flight Standards District Office (FSDO), evaluation, any comments received, and
[Docket No. FAA–2016–6893; Directorate
or lacking a PI, your local FSDO. other information. The street address for
Identifier 2015–NM–181–AD; Amendment
(2) Airworthy Product: For any requirement 39–18812; AD 2017–05–02] the Docket Office (telephone 800–647–
in this AD to obtain corrective actions from 5527) is Docket Management Facility,
a manufacturer or other source, use these RIN 2120–AA64
U.S. Department of Transportation,
actions if they are FAA-approved. Corrective Docket Operations, M–30, West
actions are considered FAA-approved if they Airworthiness Directives; Airbus
Airplanes Building Ground Floor, Room W12–140,
are approved by the State of Design Authority 1200 New Jersey Avenue SE.,
(or their delegated agent). You are required AGENCY: Federal Aviation Washington, DC 20590.
to assure the product is airworthy before it Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT:
is returned to service. Transportation (DOT). Sanjay Ralhan, Aerospace Engineer,
(h) Related Information ACTION: Final rule. International Branch, ANM–116,
Refer to MCAI EASA AD No.: 2016–0183, Transport Airplane Directorate, FAA,
dated September 13, 2016, for related
SUMMARY: We are adopting a new 1601 Lind Avenue SW., Renton, WA
information. The MCAI can be found in the
airworthiness directive (AD) for certain 98057–3356; telephone 425–227–1405;
AD docket on the Internet at: https://
Airbus Model A318–112 airplanes; fax 425–227–1149.
www.regulations.gov/document?D=FAA- Model A319–111, –112, –115, –132, and SUPPLEMENTARY INFORMATION:
2016-9357-0002. –133 airplanes; Model A320–214, –232,
and –233 airplanes; and Model A321– Discussion
(i) Material Incorporated by Reference 211, –212, –213, –231, and –232 We issued a notice of proposed
(1) The Director of the Federal Register airplanes. This AD was prompted by a rulemaking (NPRM) to amend 14 CFR
approved the incorporation by reference quality control review on the final part 39 by adding an AD that would
(IBR) of the service information listed in this assembly line, which determined that apply to certain Airbus Model A318–
paragraph under 5 U.S.C. 552(a) and 1 CFR the wrong aluminum alloy was used to 112 airplanes; Model A319–111, –112,
part 51. manufacture several structural parts. –115, –132, and –133 airplanes; Model
(2) You must use this service information This AD requires a one-time eddy A320–214, –232, and –233 airplanes;
as applicable to do the actions required by current conductivity measurement of and Model A321–211, –212, –213, –231,
this AD, unless the AD specifies otherwise. certain cabin and cargo compartment and –232 airplanes. The NPRM
(i) Pilatus PC–6 Service Bulletin (SB) No. structural parts to determine if an published in the Federal Register on
57–006, dated May 13, 2016. incorrect aluminum alloy was used, and May 26, 2016 (81 FR 33438). The NPRM
(ii) Reserved. replacement if necessary. We are issuing was prompted by a quality control
(3) For Pilatus Aircraft Ltd. service this AD to address the unsafe condition review on the final assembly line, which
information identified in this AD, contact on these products. determined that the wrong aluminum
Pilatus Aircraft Ltd., Customer Technical DATES: This AD is effective April 7, alloy was used to manufacture several
Support (MCC), P.O. Box 992, CH–6371 2017. structural parts. The NPRM proposed to
Stans, Switzerland; phone: +41 (0)41 619 The Director of the Federal Register require a one-time eddy current
3333; fax: +41 (0)41 619 7311; email: approved the incorporation by reference conductivity measurement of certain
supportPC12@pilatus-aircraft.com; Internet:
of certain publications listed in this AD cabin and cargo compartment structural
http://www.pilatus-aircraft.com.
as of April 7, 2017. parts to determine if an incorrect
(4) You may review this referenced service
ADDRESSES: For service information aluminum alloy was used, and
information at the FAA, Small Airplane
identified in this final rule, contact replacement if necessary. We are issuing
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the Airbus, Airworthiness Office—EIAS, 1 this AD to detect and replace structural
availability of this material at the FAA, call Rond Point Maurice Bellonte, 31707 parts made of incorrect aluminum alloy.
(816) 329–4148. In addition, you can access Blagnac Cedex, France; telephone +33 5 This condition could result in reduced
this service information on the Internet at 61 93 36 96; fax +33 5 61 93 44 51; email structural integrity of the airplane.
http://www.regulations.gov by searching for account.airworth-eas@airbus.com; The European Aviation Safety Agency
and locating Docket No. FAA–2016–9357. Internet: http://www.airbus.com. You (EASA), which is the Technical Agent
(5) You may view this service information may view this referenced service for the Member States of the European
that is incorporated by reference at the information at the FAA, Transport Union, has issued EASA Airworthiness
National Archives and Records Airplane Directorate, 1601 Lind Avenue Directive 2015–0218, dated November 3,
Administration (NARA). For information on SW., Renton, WA. For information on 2015 (referred to after this as the
the availability of this material at NARA, call the availability of this material at the Mandatory Continuing Airworthiness
202–741–6030, or go to: http://www.archives. FAA, call 425–227–1221. It is also Information, or ‘‘the MCAI’’), to correct
gov/federal-register/cfr/ibr-locations.html. available on the Internet at http:// an unsafe condition for certain Airbus
www.regulations.gov by searching for Model A318–112 airplanes; Model
Issued in Kansas City, Missouri on A319–111, –112, –115, –132, and –133
February 8, 2016.
and locating Docket No. FAA–2016–
mstockstill on DSK3G9T082PROD with RULES
6893. airplanes; Model A320–214, –232, and
Robert Busto, –233 airplanes; and Model A321–211,
Acting Manager, Small Airplane Directorate, Examining the AD Docket –212, –213, –231, and –232 airplanes.
Aircraft Certification Service. You may examine the AD docket on The MCAI states:
[FR Doc. 2017–03719 Filed 3–2–17; 8:45 am] the Internet at http:// Following an Airbus quality control review
BILLING CODE 4910–13–P www.regulations.gov by searching for on the final assembly line, it was discovered
and locating Docket No. FAA–2016– that wrong aluminum alloy were delivered
VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\03MRR1.SGM 03MRR1](https://thefederalregister.org/doc/82_FR_12448/page/1.svg)
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by a supplier for several structural parts. The Request To Correct a Certain Part We also estimate that it takes about 1
results of the investigations highlighted that Number (P/N) work-hour per product to comply with
0.04% of the stock could be impacted by this the basic requirements of this AD. The
wrong material. Allegiant Air asked if the part
number, P/N D5358526421400, in the average labor rate is $85 per work-hour.
Structural investigations demonstrated the
capability to sustain the static limits loads, ninth row of table 1 to paragraphs (g) Based on these figures, we estimate the
and sufficient fatigue life up to a certain and (h) of the proposed AD under cost of this AD on U.S. operators to be
inspection threshold. ‘‘Affected P/N’’ is correct. Allegiant Air $14,195, or $85 per product.
This condition, if not detected and We have received no definitive data
stated that the affected part number is
corrected, could reduce the structural that would enable us to provide cost
the same as the acceptable replacement
integrity of the aeroplane. estimates for the on-condition actions
To address this potential unsafe condition, part number.
specified in this AD.
Airbus issued Service Bulletin (SB) A320– We acknowledge the commenter’s According to the manufacturer, some
53–1298 and SB A320–53–1299 to provide concern; however, we have confirmed of the costs of this AD may be covered
inspection instructions. that both part numbers in the ninth row under warranty, thereby reducing the
For the reasons described above, this of table 1 to paragraphs (g) and (h) of cost impact on affected individuals. We
[EASA] AD requires a one-time Special this AD are the same and are correct as
Detailed Inspection (SDI) [eddy current do not control warranty coverage for
written. Therefore, we have not changed affected individuals. As a result, we
conductivity measurements] of certain cabin this AD in this regard.
and cargo compartment parts for material have included all available costs in our
identification and, depending on findings, Additional Change to NPRM cost estimate.
replacement with serviceable parts.
We have added paragraph (i) to this Authority for This Rulemaking
You may examine the MCAI in the AD AD to clarify that no reporting is Title 49 of the United States Code
docket on the Internet at http:// required. specifies the FAA’s authority to issue
www.regulations.gov by searching for Conclusion rules on aviation safety. Subtitle I,
and locating Docket No. FAA–2016– section 106, describes the authority of
6893. We reviewed the relevant data, the FAA Administrator. ‘‘Subtitle VII:
considered the comments received, and Aviation Programs,’’ describes in more
Comments determined that air safety and the detail the scope of the Agency’s
We gave the public the opportunity to public interest require adopting this AD authority.
participate in developing this AD. The with the change described previously We are issuing this rulemaking under
following presents the comments and minor editorial changes. We have the authority described in ‘‘Subtitle VII,
received on the NPRM and the FAA’s determined that these minor changes: Part A, Subpart III, Section 44701:
response to each comment. • Are consistent with the intent that General requirements.’’ Under that
was proposed in the NPRM for section, Congress charges the FAA with
Support for the NPRM correcting the unsafe condition; and promoting safe flight of civil aircraft in
One commenter, Jerry Curtis, • Do not add any additional burden air commerce by prescribing regulations
expressed support for the NPRM. upon the public than was already for practices, methods, and procedures
proposed in the NPRM. the Administrator finds necessary for
Request To Refer to the Latest Service We also determined that these safety in air commerce. This regulation
Information changes will not increase the economic is within the scope of that authority
burden on any operator or increase the because it addresses an unsafe condition
Airbus requested that we refer to the scope of this AD.
latest service information: Airbus that is likely to exist or develop on
Service Bulletins A320–53–1298 and Related Service Information Under 1 products identified in this rulemaking
A320–53–1299, both Revision 01, both CFR Part 51 action.
dated June 9, 2016. We referred to We reviewed Airbus Service Bulletins Regulatory Findings
Airbus Service Bulletins A320–53–1298 A320–53–1298 and A320–53–1299, both
and A320–53–1299, both dated We determined that this AD will not
Revision 01, both including Appendixes have federalism implications under
February 16, 2015, as the appropriate 01 through 03, both dated June 9, 2016.
sources of service information for Executive Order 13132. This AD will
The service information describes not have a substantial direct effect on
accomplishing the actions specified in procedures for a one-time eddy current
the NPRM. the States, on the relationship between
conductivity measurement of certain the national government and the States,
We agree with the request to refer to cabin and cargo compartment structural or on the distribution of power and
the latest service information. Airbus parts to determine if an incorrect responsibilities among the various
Service Bulletins A320–53–1298 and aluminum alloy was used, and levels of government.
A320–53–1299, both Revision 01, both replacement of any affected part with a For the reasons discussed above, I
dated June 9, 2016, include updated serviceable part. These documents are certify that this AD:
information and specify that no distinct since they apply to different 1. Is not a ‘‘significant regulatory
additional work is necessary for parts of the airplane (cabin and cargo action’’ under Executive Order 12866;
airplanes modified by the original issue. compartment). This service information 2. Is not a ‘‘significant rule’’ under the
We have revised this AD to refer to is reasonably available because the DOT Regulatory Policies and Procedures
Airbus Service Bulletins A320–53–1298 interested parties have access to it (44 FR 11034, February 26, 1979);
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and A320–53–1299, both Revision 01, through their normal course of business 3. Will not affect intrastate aviation in
both dated June 9, 2016. We have also or by the means identified in the Alaska; and
added credit for actions done before the ADDRESSES section. 4. Will not have a significant
effective date of this AD using Airbus economic impact, positive or negative,
Service Bulletins A320–53–1298 and Costs of Compliance on a substantial number of small entities
A320–53–1299, both dated February 16, We estimate that this AD affects 167 under the criteria of the Regulatory
2015. airplanes of U.S. registry. Flexibility Act.
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![Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 12409
List of Subjects in 14 CFR Part 39 in reduced structural integrity of the including Appendixes 01, 02, and 03, dated
airplane. June 9, 2016; this AD does not require any
Air transportation, Aircraft, Aviation report.
safety, Incorporation by reference, (f) Compliance
Safety. Comply with this AD within the (j) Credit for Previous Actions
compliance times specified, unless already This paragraph provides credit for the
Adoption of the Amendment done. actions required by paragraphs (g) and (h) of
Accordingly, under the authority this AD, if those actions were performed
(g) One-Time Measurement before the effective date of this AD using
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as Within 6 years after the effective date of Airbus Service Bulletin A320–53–1298,
this AD, but not exceeding 12 years since the dated February 16, 2015; and Airbus Service
follows: date of issuance of the original certificate of Bulletin A320–53–1299, dated February 16,
airworthiness or the date of issuance of the 2015; as applicable.
PART 39—AIRWORTHINESS original export certificate of airworthiness:
DIRECTIVES (k) Other FAA AD Provisions
Do a one-time eddy current conductivity
measurement (with 60 kilohertz (kHz) and The following provisions also apply to this
■ 1. The authority citation for part 39 480 kHz) of the cabin and cargo compartment AD:
continues to read as follows: structural parts identified in the ‘‘Affected P/ (1) Alternative Methods of Compliance
Authority: 49 U.S.C. 106(g), 40113, 44701. N’’ column of table 1 to paragraphs (g) and (AMOCs): The Manager, International
(h) of this AD to determine if an incorrect Branch, ANM–116, Transport Airplane
§ 39.13 [Amended] aluminum alloy was used, in accordance Directorate, FAA, has the authority to
with the Accomplishment Instructions of approve AMOCs for this AD, if requested
■ 2. The FAA amends § 39.13 by adding using the procedures found in 14 CFR 39.19.
the following new airworthiness Airbus Service Bulletins A320–53–1298,
Revision 01, including Appendixes 01, 02, In accordance with 14 CFR 39.19, send your
directive (AD): and 03, dated June 9, 2016 (for cabin parts); request to your principal inspector or local
2017–05–02 Airbus: Amendment 39–18812; and A320–53–1299, Revision 01, including Flight Standards District Office, as
Docket No. FAA–2016–6893; Directorate Appendixes 01, 02, and 03, dated June 9, appropriate. If sending information directly
Identifier 2015–NM–181–AD. 2016 (for cargo parts). to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
(a) Effective Date International Branch, ANM–116, Transport
TABLE 1 TO PARAGRAPHS (g) AND (h) Airplane Directorate, FAA, 1601 Lind
This AD is effective April 7, 2017.
OF THIS AD—PARTS TO BE IN- Avenue SW., Renton, WA 98057–3356;
(b) Affected ADs SPECTED/INSTALLED telephone: 425–227–1405; fax: 425–227–
None. 1149. Information may be emailed to: 9-
Acceptable ANM-116-AMOC-REQUESTS@faa.gov.
(c) Applicability Affected P/N replacement Area Before using any approved AMOC, notify
P/N
This AD applies to the Airbus airplanes your appropriate principal inspector, or
identified in paragraphs (c)(1) through (c)(4) D5347120720000 D5347120720051 Cabin. lacking a principal inspector, the manager of
of this AD, certificated in any category; D5347120720100 D5347120720151 Cabin. the local flight standards district office/
manufacturer serial numbers 3586, 3588, D5347120920000 D5347120920051 Cabin. certificate holding district office. The AMOC
3589, 3590, 3595, 3604, 3608, 3614, 3615, D5347120920100 D5347120920151 Cabin. approval letter must specifically reference
3620, 3632, 3634, 3638, 3647, 3651, 3657, D5347118820400 D5347118820451 Cabin. this AD.
3660, 3661, 3663, 3671, 3675, 3680, 3683 D5347717620000 D5347717620051 Cargo. (2) Contacting the Manufacturer: For any
through 3687 inclusive, 3689, 3691, 3694, D5357020620000 D5357020620051 Cargo. requirement in this AD to obtain corrective
D5358526421200 D5358526421251 Cargo.
3700, 3702, 3704, 3705, 3710, 3720, 3727, D5358526421400 D5358526421400 Cargo.
actions from a manufacturer, the action must
3728, 3733, 3735, 3742, 3744, 3746, 3754, D5358526421000 D5358526421051 Cargo. be accomplished using a method approved
3757, 3759, 3763, 3768, 3770, 3772, 3774, D5358513120001 D5358513120051 Cargo. by the Manager, International Branch, ANM–
3775, 3779, 3788, 3790, 3794, 3797, 3799, 116, Transport Airplane Directorate, FAA; or
3801, 3803, 3808, 3810, 3818, 3822, 3824, (h) Replacement the European Aviation Safety Agency
3826 through 4329 inclusive, 4331 through (EASA); or Airbus’s EASA Design
6051 inclusive, 6053 through 6061 inclusive, If during the inspection required by Organization Approval (DOA). If approved by
6063 through 6072 inclusive, 6074 through paragraph (g) of this AD, any affected part the DOA, the approval must include the
6100 inclusive, 6102 through 6115 inclusive, having a part number (P/N) specified in table DOA-authorized signature.
6117 through 6126 inclusive, 6128 through 1 to paragraphs (g) and (h) of this AD is (3) Required for Compliance (RC): Except
6136 inclusive, 6138 through 6143 inclusive, found to have a measured value greater than as provided by paragraph (i) of this AD: If
6145 through 6150 inclusive, 6152 through that specified in Figure A–GFAAA, Sheet 02, any service information contains procedures
6159 inclusive, 6161 and 6162. ‘‘Inspection Flowchart,’’ of the applicable or tests that are identified as RC, those
(1) Airbus Model A318–112 airplanes. service information identified in paragraph procedures and tests must be done to comply
(2) Airbus Model A319–111, –112, –115, (g) of this AD: Before further flight, replace with this AD; any procedures or tests that are
–132, and –133 airplanes. with an acceptable replacement part having not identified as RC are recommended. Those
(3) Airbus Model A320–214, –232, and a part number specified in table 1 to procedures and tests that are not identified
–233 airplanes. paragraphs (g) and (h) of this AD, in as RC may be deviated from using accepted
(4) Airbus Model A321–211, –212, –213, accordance with the Accomplishment methods in accordance with the operator’s
–231, and –232 airplanes. Instructions of Airbus Service Bulletins maintenance or inspection program without
A320–53–1298, Revision 01, including obtaining approval of an AMOC, provided
(d) Subject Appendixes 01, 02, and 03, dated June 9, the procedures and tests identified as RC can
Air Transport Association (ATA) of 2016 (for cabin parts); and A320–53–1299, be done and the airplane can be put back in
America Code 53, Fuselage. Revision 01, including Appendixes 01, 02, an airworthy condition. Any substitutions or
and 03, dated June 9, 2016 (for cargo parts). changes to procedures or tests identified as
(e) Reason
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RC require approval of an AMOC.
This AD was prompted by a quality control (i) No Reporting
review of the final assembly line which Although reporting of inspection results is (l) Related Information
determined that the wrong aluminum alloy specified as a ‘‘Required for Compliance’’ (1) Refer to Mandatory Continuing
was used to manufacture several structural (RC) action in Airbus Service Bulletins Airworthiness Information (MCAI) EASA AD
parts. We are issuing this AD to detect and A320–53–1298, Revision 01, including 2015–0218, dated November 3, 2015, for
replace structural parts made of incorrect Appendixes 01, 02, and 03, dated June 9, related information. This MCAI may be
aluminum alloy. This condition could result 2016; and A320–53–1299, Revision 01, found in the AD docket on the Internet at
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![12410 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations
http://www.regulations.gov by searching for design approval holder (DAH) Discussion
and locating Docket No. FAA–2016–6893. indicating that the frame-to-floor-beam
(2) Service information identified in this We issued a notice of proposed
joints and frames common to shear ties rulemaking (NPRM) to amend 14 CFR
AD that is not incorporated by reference is
at certain locations of fuselage structure part 39 by adding an AD that would
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD. are subject to widespread fatigue apply to all The Boeing Company Model
damage (WFD). This AD requires 767–200 and –300 series airplanes. The
(m) Material Incorporated by Reference inspections for cracking of certain frame NPRM published in the Federal
(1) The Director of the Federal Register inner chords and webs common to the Register on July 7, 2016 (81 FR 44246).
approved the incorporation by reference floor beam joint and at frames common The NPRM was prompted by an
(IBR) of the service information listed in this to the shear ties at certain sections, and
paragraph under 5 U.S.C. 552(a) and 1 CFR evaluation by the DAH indicating that
corrective action if necessary. We are the frame-to-floor-beam joints and
part 51.
(2) You must use this service information issuing this AD to address the unsafe frames common to shear ties at certain
as applicable to do the actions required by condition on these products. locations of fuselage structure are
this AD, unless this AD specifies otherwise. DATES: This AD is effective April 7, subject to WFD. The NPRM proposed to
(i) Airbus Service Bulletin A320–53–1298, 2017. require repetitive inspections for
Revision 01, including Appendixes 01 cracking of the frame inner chords and
through 03, dated June 9, 2016. The Director of the Federal Register
webs common to the floor beam joint
(ii) Airbus Service Bulletin A320–53–1299, approved the incorporation by reference
and at frames common to the shear ties
Revision 01, including Appendixes 01 of a certain publication listed in this AD
through 03, dated June 9, 2016. at certain sections on the left and right
as of April 7, 2017.
(3) For service information identified in fuselage sides, and corrective action if
this AD, contact Airbus, Airworthiness ADDRESSES: For service information necessary. We are issuing this AD to
Office—EIAS, 1 Rond Point Maurice identified in this final rule, contact detect and correct cracking of the frame
Bellonte, 31707 Blagnac Cedex, France; Boeing Commercial Airplanes, inner chords and webs common to the
telephone +33 5 61 93 36 96; fax +33 5 61 Attention: Contractual & Data Services floor beam joint and at frames common
93 44 51; email account.airworth-eas@ (C&DS), 2600 Westminster Blvd., MC to the shear ties at certain sections on
airbus.com; Internet: http://www.airbus.com. 110–SK57, Seal Beach, CA 90740–5600; the left and right fuselage sides, which
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
telephone 562–797–1717; Internet could result in reduced structural
1601 Lind Avenue SW., Renton, WA. For https://www.myboeingfleet.com. You integrity of the airplane.
information on the availability of this may view this referenced service
Comments
material at the FAA, call 425–227–1221. information at the FAA, Transport
(5) You may view this service information Airplane Directorate, 1601 Lind Avenue We gave the public the opportunity to
that is incorporated by reference at the SW., Renton, WA. For information on participate in developing this AD. The
National Archives and Records the availability of this material at the following presents the comments
Administration (NARA). For information on FAA, call 425–227–1221. It is also received on the NPRM and the FAA’s
the availability of this material at NARA, call response to each comment.
202–741–6030, or go to: http://
available on the Internet at http://
www.archives.gov/federal-register/cfr/ibr- www.regulations.gov by searching for Support for the NPRM
locations.html. and locating Docket No. FAA–2016–
7423. Boeing and United Airlines expressed
Issued in Renton, Washington, on February support for the NPRM.
16, 2017. Examining the AD Docket
Thomas Groves,
Effect of Winglets on Accomplishment
You may examine the AD docket on of the Proposed Actions
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
the Internet at http:// Aviation Partners Boeing stated that
www.regulations.gov by searching for accomplishing the Supplemental Type
[FR Doc. 2017–03972 Filed 3–2–17; 8:45 am]
and locating Docket No. FAA–2016– Certificate (STC) ST01920SE does not
BILLING CODE 4910–13–P
7423; or in person at the Docket affect the ability to accomplish the
Management Facility between 9 a.m. actions specified in the NPRM.
and 5 p.m., Monday through Friday, We concur with the commenter. We
DEPARTMENT OF TRANSPORTATION
except Federal holidays. The AD docket have redesignated paragraph (c) of the
Federal Aviation Administration contains this AD, the regulatory proposed AD as (c)(1) and added
evaluation, any comments received, and paragraph (c)(2) to this AD to state that
14 CFR Part 39 other information. The address for the installation of STC ST01920SE does not
Docket Office (phone: 800–647–5527) is affect the ability to accomplish the
[Docket No. FAA–2016–7423; Directorate Docket Management Facility, U.S.
Identifier 2016–NM–034–AD; Amendment actions required by this final rule.
Department of Transportation, Docket Therefore, for airplanes on which STC
39–18816; AD 2017–05–06]
Operations, M–30, West Building ST01920SE is installed, a ‘‘change in
RIN 2120–AA64 Ground Floor, Room W12–140, 1200 product’’ alternative method of
New Jersey Avenue SE., Washington, compliance (AMOC) approval request is
Airworthiness Directives; The Boeing DC 20590. not necessary to comply with the
Company Airplanes
FOR FURTHER INFORMATION CONTACT: requirements of 14 CFR 39.17.
AGENCY: Federal Aviation Wayne Lockett, Aerospace Engineer, Conclusion
Administration (FAA), DOT. Airframe Branch, ANM–120S, FAA,
mstockstill on DSK3G9T082PROD with RULES
ACTION: Final rule. Seattle Aircraft Certification Office, We reviewed the relevant data,
1601 Lind Avenue SW., Renton, WA considered the comments received, and
SUMMARY: We are adopting a new 98057 3356; phone: 425–917–6447; fax: determined that air safety and the
airworthiness directive (AD) for all The 425–917–6590; email: wayne.lockett@ public interest require adopting this AD
Boeing Company Model 767–200 and faa.gov. with the changes described previously
–300 series airplanes. This AD was and minor editorial changes. We have
prompted by an evaluation by the SUPPLEMENTARY INFORMATION: determined that these minor changes:
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Document Created: 2018-02-01 14:46:03
Document Modified: 2018-02-01 14:46:03
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective April 7, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 82 FR 12407 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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