82 FR 43160 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 177 (September 14, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 177 (September 14, 2017)
| Page Range | 43160-43163 | |
| FR Document | 2017-19303 |
[Federal Register Volume 82, Number 177 (Thursday, September 14, 2017)] [Rules and Regulations] [Pages 43160-43163] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-19303] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-0451; Product Identifier 2013-NM-253-AD; Amendment 39-19026; AD 2017-18-17] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2004-23-20, which applied to certain Airbus Model A300, A300 B4-600, and A300 B4- 600R series airplanes; and Model A300 F4-605R and A300 C4-605R Variant F airplanes. AD 2004-23-20 required, for certain airplanes, repetitive inspections for cracking around certain attachment holes, installation of new fasteners for certain airplanes, and follow-on corrective actions if necessary. AD 2004-23-20 also required modifying certain fuselage frames, which terminated certain repetitive inspections. This new AD reduces certain compliance times, expands the applicability, and requires an additional repair on certain modified airplanes. This AD was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 19, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 19, 2017. ADDRESSES: For service information identified in this final rule, 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 Standards Branch, 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- 0451. [[Page 43161]] 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- 0451; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) (``AD 2004-23-20''). AD 2004-23-20 applied to certain Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes; and Model A300 F4-605R and A300 C4-605R Variant F airplanes. The SNPRM published in the Federal Register on June 15, 2017 (82 FR 27444) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on February 1, 2016 (81 FR 5056) (``the NPRM''). The NPRM was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. The NPRM proposed to reduce the compliance times for the initial inspection and the inspection intervals. The NPRM also proposed to expand the applicability and require an additional repair on certain airplanes that have been modified. The SNPRM proposed to reduce the compliance times, require an additional modification, and omit the requirement for the repetitive inspections. We are issuing this AD to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and 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 AD 2016-0249, dated December 14, 2016; corrected January 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''); to correct an unsafe condition for all Airbus Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and A300 C4-605R Variant F airplanes. The MCAI states: During an inspection in accordance with Airworthiness Limitation Item (ALI) 53-15-54 on an A300-600 aeroplane, Frames (FR) 43, FR44, FR45 and FR46 were found cracked between stringer (STGR) 24 and STGR30 on the aeroplane right hand side. FR45 was also found cracked on the aeroplane left hand side. This condition, if not detected and corrected, could reduce the structural integrity of the fuselage. To address this potential unsafe condition and improve the fatigue life of the upper frame feet fittings, Airbus issued Service Bulletin (SB) A300-53-6125 to provide instructions for expansion of the most sensitive fastener holes between FR41 and FR46. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD F-2004-002 (EASA approval 2003-2108) [which corresponds to FAA AD 2004-23-20] to require the structural modification defined in SB A300-53-6125 Revision 03 (Airbus modification 12168). [French] AD F-2004-002 was subsequently superseded by EASA AD 2013-0295 to amend the inspection programme in this area as provided in SB A300-53-6122 (which is now obsolete and replaced by ALI task 531558, published in the [Airworthiness Limitation Section] ALS Part 2 Revision 01 dated 07 August 2015). Since EASA AD 2013-0295 was issued, a new investigation was conducted in the frame of the Widespread Fatigue Damage study. Airbus revised the thresholds for the accomplishment of the instructions defined in SB A300-53-6125 and issued SB A300-53-6178 to provide modification instructions to improve the fatigue life of upper frame feet fittings on aeroplane[s] on which Airbus modification (mod) 12168 or Airbus SB A300-53-6125 was embodied. For the reason described above, this [EASA] AD retains some requirements of EASA AD 2013-0295, which is superseded, and requires modification of the upper frame feet fittings from FR41 to FR46 [repetitive inspections are not retained]. This [EASA] AD is republished to correct a typographical error in the compliance time * * *. 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- 0451. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-53-6125, Revision 04, dated March 17, 2015; and Service Bulletin A300-53-6178, dated March 17, 2015. The service information describes procedures for the modification of certain upper frame feet fittings. These documents are distinct since they apply to airplanes in different configurations. 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 65 airplanes of U.S. registry. We estimate the following costs to comply with this AD: The actions that were required by AD 2004-23-20 and retained in this AD take about 90 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $4,000 per product. Based on these figures, the estimated cost of the actions that were required by AD 2004-23-20 is $11,650 per product. We also estimate that it will take up to 109 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost up to $6,070 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be up to $996,775, or up to $15,335 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this 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 [[Page 43162]] the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), and adding the following new AD: 2017-18-17 Airbus: Amendment 39-19026; Docket No. FAA-2016-0451; Product Identifier 2013-NM-253-AD. (a) Effective Date This AD is effective October 19, 2017. (b) Affected ADs This AD replaces AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) (``AD 2004-23-20''). (c) Applicability This AD applies to Airbus Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and A300 C4-605R Variant F airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. We are issuing this AD to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification of the Upper Frame Feet Fittings (1) Except for airplanes identified in table 2 to paragraphs (g)(1) and (g)(2) of this AD: At the times specified in table 1 to paragraph (g)(1) of this AD, depending on the average flight time (AFT), as defined in paragraph (i) of this AD, modify the upper frame feet fittings, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6125, Revision 04, dated March 17, 2015 (``SB A300-53-6125, Revision 04''). Do all applicable related investigative and corrective actions before further flight. Where Airbus SB A300-53-6125, Revision 04, 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. Table 1 to Paragraph (g)(1) of This AD--Modification SB A300-53-6125, Revision 04 ------------------------------------------------------------------------ Initial compliance time (flight cycles or Airplane usage flight hours, whichever occurs first since first flight) ------------------------------------------------------------------------ AFT greater than 1.5......... Within 10,200 flight cycles or 22,100 flight hours. AFT equal to or less than 1.5 Within 11,000 flight cycles or 16,600 flight hours. ------------------------------------------------------------------------ Table 2 to Paragraphs (g)(1) and (g)(2) of This AD--Modification SB A300- 53-6178 ------------------------------------------------------------------------ Airplane configuration Initial compliance time ------------------------------------------------------------------------ Post-modification 12168...... Within 27,100 flight cycles or 47,300 flight hours since the airplane's first flight, whichever occurs first. Post-SB A300-53-6125......... Within 27,100 flight cycles or 47,300 flight hours after embodiment of SB A300- 53-6125, whichever occurs first. ------------------------------------------------------------------------ (2) For airplanes identified in table 2 to paragraphs (g)(1) and (g)(2) of this AD: At the applicable compliance time specified in table 2 to paragraphs (g)(1) and (g)(2) of this AD, modify the upper frame feet fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6178, dated March 17, 2015. Where Airbus Service Bulletin A300-53-6178, dated March 17, 2015, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'': Before further flight, [[Page 43163]] accomplish corrective actions in accordance with the procedures specified in paragraph (l)(2) of this AD. (h) Additional Post-Modification Actions Prior to exceeding 24,100 total flight cycles or 42,000 total flight hours, whichever occurs first after doing the modification required by paragraph (g)(2) of this AD: Contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); for instructions to do additional actions, and do those actions at the compliance times stated therein. (i) Definition of AFT For the purpose of this AD, to establish the applicable AFT for the actions required by paragraph (g)(1) of this AD, divide the total accumulated flight hours counted from take-off to touch-down by the total accumulated flight cycles as of the effective date of this AD. (j) Credit for Previous Actions This paragraph provides credit for the modification required by paragraph (g)(1) of this AD, if the modification was performed before the effective date of this AD using the service information specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. (1) Airbus Service Bulletin A300-53-6125, dated November 8, 2000, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003, which was incorporated by reference in AD 2004-23-20. (3) Airbus Service Bulletin A300-53-6125, Revision 02, dated February 25, 2005, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A300-53-6125, Revision 03, dated September 13, 2011, which is not incorporated by reference in this AD. (k) Exempt Airplanes For airplanes on which Airbus Modification 12168 has been embodied in production: The modification required by paragraph (g)(1) of this AD is not required by this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (g)(1) and (g)(2) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or 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 Airworthiness Directive 2016-0249, dated December 14, 2016; corrected January 10, 2017; for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA- 2016-0451. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425- 227-2125; fax 425- 227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) 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 A300-53-6125, Revision 04, dated March 17, 2015. (ii) Airbus Service Bulletin A300-53-6178, dated March 17, 2015. (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. (4) You may view this service information at the FAA, Transport Standards Branch, 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 August 29, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-19303 Filed 9-13-17; 8:45 am] BILLING CODE 4910-13-P
![43160 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations
accordance with the procedures specified in (m) Related Information DEPARTMENT OF TRANSPORTATION
paragraph (l)(2) of this AD. (1) Refer to Mandatory Continuing
(i) No Terminating Action for Inspections Airworthiness Information (MCAI) EASA Federal Aviation Administration
Accomplishing corrective actions on an Airworthiness Directive 2016–0196, dated
September 30, 2016, for related information. 14 CFR Part 39
airplane as required by paragraph (g) or (h)(2)
of this AD does not constitute terminating This MCAI may be found in the AD docket [Docket No. FAA–2016–0451; Product
action for the repetitive actions required by on the Internet at http://www.regulations.gov Identifier 2013–NM–253–AD; Amendment
paragraph (g) of this AD. by searching for and locating Docket No. 39–19026; AD 2017–18–17]
FAA–2017–0560.
(j) Terminating Action RIN 2120–AA64
(2) For more information about this AD,
Accomplishment of the initial inspection contact Dan Rodina, Aerospace Engineer,
required by paragraph (g) of this AD Airworthiness Directives; Airbus
International Section, Transport Standards
constitutes terminating action for the actions Airplanes
Branch, FAA, 1601 Lind Avenue SW.,
required by paragraph (h) of AD 2011–10–06. Renton, WA 98057–3356; telephone 425– AGENCY: Federal Aviation
(k) Credit for Previous Actions 227–2125; fax 425–227–1149. Administration (FAA), Department of
This paragraph provides credit for actions (3) Service information identified in this Transportation (DOT).
required by paragraph (g) of this AD, if those AD that is not incorporated by reference is ACTION: Final rule.
actions were performed before the effective available at the addresses specified in
date of this AD using the service information paragraphs (n)(3) and (n)(4) of this AD. SUMMARY: We are superseding
specified in Airbus Service Bulletin A310– Airworthiness Directive (AD) 2004–23–
(n) Material Incorporated by Reference
57–2050, Revision 03, dated December 19, 20, which applied to certain Airbus
2014. (1) The Director of the Federal Register Model A300, A300 B4–600, and A300
approved the incorporation by reference B4–600R series airplanes; and Model
(l) Other FAA AD Provisions
(IBR) of the service information listed in this A300 F4–605R and A300 C4–605R
The following provisions also apply to this paragraph under 5 U.S.C. 552(a) and 1 CFR
AD:
Variant F airplanes. AD 2004–23–20
part 51. required, for certain airplanes, repetitive
(1) Alternative Methods of Compliance (2) You must use this service information
(AMOCs): The Manager, International inspections for cracking around certain
as applicable to do the actions required by attachment holes, installation of new
Section, Transport Standards Branch, FAA,
this AD, unless this AD specifies otherwise.
has the authority to approve AMOCs for this fasteners for certain airplanes, and
(i) Airbus Service Bulletin A310–57–2050,
AD, if requested using the procedures found follow-on corrective actions if
Revision 04, dated March 13, 2015.
in 14 CFR 39.19. In accordance with 14 CFR necessary. AD 2004–23–20 also required
39.19, send your request to your principal (ii) Reserved.
modifying certain fuselage frames,
inspector or local Flight Standards District (3) For service information identified in
which terminated certain repetitive
Office, as appropriate. If sending information this AD, contact Airbus SAS, Airworthiness
inspections. This new AD reduces
directly to the International Section, send it Office—EAW, 1 Rond Point Maurice
certain compliance times, expands the
to the attention of the person identified in Bellonte, 31707 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33 5 61
applicability, and requires an additional
paragraph (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC- 93 44 51; email: account.airworth-eas@
repair on certain modified airplanes.
REQUESTS@faa.gov. Before using any airbus.com; Internet: http://www.airbus.com. This AD was prompted by a report
approved AMOC, notify your appropriate (4) You may view this service information indicating that the material used to
principal inspector, or lacking a principal at the FAA, Transport Standards Branch, manufacture the upper frame feet was
inspector, the manager of the local flight 1601 Lind Avenue SW., Renton, WA. For changed and negatively affected the
standards district office/certificate holding information on the availability of this fatigue life of the frame feet. We are
district office. issuing this AD to address the unsafe
material at the FAA, call 425–227–1221.
(2) Contacting the Manufacturer: For any condition on these products.
(5) You may view this service information
requirement in this AD to obtain corrective
that is incorporated by reference at the DATES: This AD is effective October 19,
actions from a manufacturer, the action must
be accomplished using a method approved National Archives and Records 2017.
by the Manager, International Section, Administration (NARA). For information on The Director of the Federal Register
Transport Standards Branch, FAA; or the the availability of this material at NARA, call approved the incorporation by reference
European Aviation Safety Agency (EASA); or 202–741–6030, or go to: http:// of certain publications listed in this AD
Airbus’s EASA Design Organization www.archives.gov/federal-register/cfr/ibr- as of October 19, 2017.
Approval (DOA). If approved by the DOA, locations.html. ADDRESSES: For service information
the approval must include the DOA- identified in this final rule, contact
authorized signature. Issued in Renton, Washington, on August
(3) Required for Compliance (RC): Except 31, 2017. Airbus SAS, Airworthiness Office—
as required by paragraph (h)(2) of this AD: If Dionne Palermo, EAW, 1 Rond Point Maurice Bellonte,
any service information contains procedures 31707 Blagnac Cedex, France; telephone
Acting Director, System Oversight Division,
or tests that are identified as RC, those Aircraft Certification Service.
+33 5 61 93 36 96; fax +33 5 61 93 44
procedures and tests must be done to comply 51; email account.airworth-eas@
[FR Doc. 2017–19042 Filed 9–13–17; 8:45 am]
with this AD; any procedures or tests that are airbus.com; Internet http://
not identified as RC are recommended. Those BILLING CODE 4910–13–P www.airbus.com. You may view this
procedures and tests that are not identified referenced service information at the
as RC may be deviated from using accepted FAA, Transport Standards Branch, 1601
methods in accordance with the operator’s
rmajette on DSKBCKNHB2PROD with RULES
Lind Avenue SW., Renton, WA. For
maintenance or inspection program without
obtaining approval of an AMOC, provided
information on the availability of this
the procedures and tests identified as RC can material at the FAA, call 425–227–1221.
be done and the airplane can be put back in It is also available on the Internet at
an airworthy condition. Any substitutions or http://www.regulations.gov by searching
changes to procedures or tests identified as for and locating Docket No. FAA–2016–
RC require approval of an AMOC. 0451.
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![Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43161
Examining the AD Docket for the Member States of the European received no comments on the SNPRM or
You may examine the AD docket on Union, has issued EASA AD 2016–0249, on the determination of the cost to the
the Internet at http:// dated December 14, 2016; corrected public.
www.regulations.gov by searching for January 10, 2017 (referred to after this
Conclusion
and locating Docket No. FAA–2016– as the Mandatory Continuing
0451; or in person at the Docket Airworthiness Information, or ‘‘the We reviewed the available data and
Management Facility between 9 a.m. MCAI’’); to correct an unsafe condition determined that air safety and the
and 5 p.m., Monday through Friday, for all Airbus Model A300 B4–603, public interest require adopting this AD
except Federal holidays. The AD docket A300 B4–620, A300 B4–622, A300 B4– as proposed except for minor editorial
contains this AD, the regulatory 605R, A300 B4–622R, A300 F4–605R, changes. We have determined that these
evaluation, any comments received, and A300 F4–622R, and A300 C4–605R minor changes:
other information. The address for the Variant F airplanes. The MCAI states: • Are consistent with the intent that
Docket Office (telephone 800–647–5527) was proposed in the SNPRM for
During an inspection in accordance with
is Docket Management Facility, U.S. Airworthiness Limitation Item (ALI) 53–15– correcting the unsafe condition; and
54 on an A300–600 aeroplane, Frames (FR) • Do not add any additional burden
Department of Transportation, Docket
43, FR44, FR45 and FR46 were found cracked upon the public than was already
Operations, M–30, West Building
between stringer (STGR) 24 and STGR30 on proposed in the SNPRM.
Ground Floor, Room W12–140, 1200
the aeroplane right hand side. FR45 was also
New Jersey Avenue SE., Washington, found cracked on the aeroplane left hand Related Service Information Under 1
DC 20590. side. CFR Part 51
FOR FURTHER INFORMATION CONTACT: Dan This condition, if not detected and Airbus has issued Service Bulletin
Rodina, Aerospace Engineer, corrected, could reduce the structural A300–53–6125, Revision 04, dated
International Section, Transport integrity of the fuselage.
To address this potential unsafe condition
March 17, 2015; and Service Bulletin
Standards Branch, 1601 Lind Avenue A300–53–6178, dated March 17, 2015.
SW., Renton, WA 98057–3356; and improve the fatigue life of the upper
frame feet fittings, Airbus issued Service The service information describes
telephone 425–227–2125; fax 425–227– Bulletin (SB) A300–53–6125 to provide procedures for the modification of
1149. instructions for expansion of the most certain upper frame feet fittings. These
SUPPLEMENTARY INFORMATION: sensitive fastener holes between FR41 and documents are distinct since they apply
FR46. DGAC [Direction Générale de to airplanes in different configurations.
Discussion l’Aviation Civile] France issued AD F–2004– This service information is reasonably
We issued a supplemental notice of 002 (EASA approval 2003–2108) [which available because the interested parties
proposed rulemaking (SNPRM) to corresponds to FAA AD 2004–23–20] to
require the structural modification defined in
have access to it through their normal
amend 14 CFR part 39 to supersede AD course of business or by the means
2004–23–20, Amendment 39–13875 (69 SB A300–53–6125 Revision 03 (Airbus
modification 12168). identified in the ADDRESSES section.
FR 68779, November 26, 2004) (‘‘AD
[French] AD F–2004–002 was subsequently Costs of Compliance
2004–23–20’’). AD 2004–23–20 applied superseded by EASA AD 2013–0295 to
to certain Airbus Model A300 B2, A300 amend the inspection programme in this area We estimate that this AD affects 65
B4, A300 B4–600, and A300 B4–600R as provided in SB A300–53–6122 (which is airplanes of U.S. registry.
series airplanes; and Model A300 F4– now obsolete and replaced by ALI task We estimate the following costs to
605R and A300 C4–605R Variant F 531558, published in the [Airworthiness comply with this AD:
airplanes. The SNPRM published in the Limitation Section] ALS Part 2 Revision 01 The actions that were required by AD
Federal Register on June 15, 2017 (82 dated 07 August 2015). 2004–23–20 and retained in this AD
FR 27444) (‘‘the SNPRM’’). We preceded Since EASA AD 2013–0295 was issued, a
new investigation was conducted in the
take about 90 work-hours per product,
the SNPRM with a notice of proposed at an average labor rate of $85 per work-
frame of the Widespread Fatigue Damage
rulemaking (NPRM) that published in study. Airbus revised the thresholds for the hour. Required parts cost about $4,000
the Federal Register on February 1, accomplishment of the instructions defined per product. Based on these figures, the
2016 (81 FR 5056) (‘‘the NPRM’’). The in SB A300–53–6125 and issued SB A300– estimated cost of the actions that were
NPRM was prompted by a report 53–6178 to provide modification instructions required by AD 2004–23–20 is $11,650
indicating that the material used to to improve the fatigue life of upper frame feet per product.
manufacture the upper frame feet was fittings on aeroplane[s] on which Airbus We also estimate that it will take up
changed and negatively affected the modification (mod) 12168 or Airbus SB to 109 work-hours per product to
fatigue life of the frame feet. The NPRM A300–53–6125 was embodied.
comply with the new basic
For the reason described above, this
proposed to reduce the compliance requirements of this AD. The average
[EASA] AD retains some requirements of
times for the initial inspection and the EASA AD 2013–0295, which is superseded, labor rate is $85 per work-hour.
inspection intervals. The NPRM also and requires modification of the upper frame Required parts will cost up to $6,070
proposed to expand the applicability feet fittings from FR41 to FR46 [repetitive per product. Based on these figures, we
and require an additional repair on inspections are not retained]. estimate the cost of this AD on U.S.
certain airplanes that have been This [EASA] AD is republished to correct operators to be up to $996,775, or up to
modified. The SNPRM proposed to a typographical error in the compliance time $15,335 per product.
reduce the compliance times, require an * * *. We have received no definitive data
additional modification, and omit the You may examine the MCAI in the that will enable us to provide cost
requirement for the repetitive AD docket on the Internet at http:// estimates for the on-condition actions
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inspections. We are issuing this AD to www.regulations.gov by searching for specified in this AD.
prevent cracking of the center section of and locating Docket No. FAA–2016–
the fuselage, which could result in a Authority for This Rulemaking
0451.
ruptured frame foot and reduced Title 49 of the United States Code
structural integrity of the airplane. Comments specifies the FAA’s authority to issue
The European Aviation Safety Agency We gave the public the opportunity to rules on aviation safety. Subtitle I,
(EASA), which is the Technical Agent participate in developing this AD. We section 106, describes the authority of
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![43162 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations
the FAA Administrator. ‘‘Subtitle VII: 1. Is not a ‘‘significant regulatory (c) Applicability
Aviation Programs,’’ describes in more action’’ under Executive Order 12866; This AD applies to Airbus Model A300 B4–
detail the scope of the Agency’s 2. Is not a ‘‘significant rule’’ under the 603, A300 B4–620, A300 B4–622, A300 B4–
authority. DOT Regulatory Policies and Procedures 605R, A300 B4–622R, A300 F4–605R, A300
We are issuing this rulemaking under (44 FR 11034, February 26, 1979); F4–622R, and A300 C4–605R Variant F
the authority described in ‘‘Subtitle VII, 3. Will not affect intrastate aviation in airplanes; certificated in any category; all
Alaska; and manufacturer serial numbers.
Part A, Subpart III, Section 44701:
4. Will not have a significant (d) Subject
General requirements.’’ Under that
economic impact, positive or negative,
section, Congress charges the FAA with on a substantial number of small entities Air Transport Association (ATA) of
promoting safe flight of civil aircraft in under the criteria of the Regulatory
America Code 53, Fuselage.
air commerce by prescribing regulations Flexibility Act. (e) Reason
for practices, methods, and procedures
List of Subjects in 14 CFR Part 39 This AD was prompted by a report
the Administrator finds necessary for indicating that the material used to
safety in air commerce. This regulation Air transportation, Aircraft, Aviation manufacture the upper frame feet was
is within the scope of that authority safety, Incorporation by reference, changed and negatively affected the fatigue
because it addresses an unsafe condition Safety. life of the frame feet. We are issuing this AD
that is likely to exist or develop on to prevent cracking of the center section of
products identified in this rulemaking Adoption of the Amendment the fuselage, which could result in a ruptured
action. Accordingly, under the authority frame foot and reduced structural integrity of
delegated to me by the Administrator, the airplane.
This AD is issued in accordance with
authority delegated by the Executive the FAA amends 14 CFR part 39 as (f) Compliance
Director, Aircraft Certification Service, follows: Comply with this AD within the
as authorized by FAA Order 8000.51C. compliance times specified, unless already
In accordance with that order, issuance PART 39—AIRWORTHINESS done.
of ADs is normally a function of the DIRECTIVES
(g) Modification of the Upper Frame Feet
Compliance and Airworthiness ■ 1. The authority citation for part 39 Fittings
Division, but during this transition continues to read as follows: (1) Except for airplanes identified in table
period, the Executive Director has 2 to paragraphs (g)(1) and (g)(2) of this AD:
Authority: 49 U.S.C. 106(g), 40113, 44701.
delegated the authority to issue ADs At the times specified in table 1 to paragraph
applicable to transport category § 39.13 [Amended] (g)(1) of this AD, depending on the average
airplanes to the Director of the System flight time (AFT), as defined in paragraph (i)
■ 2. The FAA amends § 39.13 by of this AD, modify the upper frame feet
Oversight Division.
removing Airworthiness Directive (AD) fittings, including doing all applicable
Regulatory Findings 2004–23–20, Amendment 39–13875 (69 related investigative and corrective actions,
FR 68779, November 26, 2004), and in accordance with the Accomplishment
We determined that this AD will not adding the following new AD: Instructions of Airbus Service Bulletin A300–
have federalism implications under 53–6125, Revision 04, dated March 17, 2015
Executive Order 13132. This AD will 2017–18–17 Airbus: Amendment 39–19026;
Docket No. FAA–2016–0451; Product (‘‘SB A300–53–6125, Revision 04’’). Do all
not have a substantial direct effect on Identifier 2013–NM–253–AD. applicable related investigative and
the States, on the relationship between corrective actions before further flight. Where
the national government and the States, (a) Effective Date Airbus SB A300–53–6125, Revision 04,
or on the distribution of power and This AD is effective October 19, 2017. specifies to contact Airbus for appropriate
responsibilities among the various action, and specifies that action as ‘‘RC’’
(b) Affected ADs (Required for Compliance): Before further
levels of government. flight, accomplish corrective actions in
This AD replaces AD 2004–23–20,
For the reasons discussed above, I Amendment 39–13875 (69 FR 68779, accordance with the procedures specified in
certify that this AD: November 26, 2004) (‘‘AD 2004–23–20’’). paragraph (l)(2) of this AD.
TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—MODIFICATION SB A300–53–6125, REVISION 04
Initial compliance time
Airplane usage (flight cycles or flight hours, whichever occurs first since first flight)
AFT greater than 1.5 .......................................... Within 10,200 flight cycles or 22,100 flight hours.
AFT equal to or less than 1.5 ............................. Within 11,000 flight cycles or 16,600 flight hours.
TABLE 2 TO PARAGRAPHS (g)(1) AND (g)(2) OF THIS AD—MODIFICATION SB A300–53–6178
Airplane configuration Initial compliance time
Post-modification 12168 ..................................... Within 27,100 flight cycles or 47,300 flight hours since the airplane’s first flight, whichever oc-
curs first.
Post-SB A300–53–6125 ..................................... Within 27,100 flight cycles or 47,300 flight hours after embodiment of SB A300–53–6125,
whichever occurs first.
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(2) For airplanes identified in table 2 to modify the upper frame feet fittings, in Airbus Service Bulletin A300–53–6178,
paragraphs (g)(1) and (g)(2) of this AD: At the accordance with the Accomplishment dated March 17, 2015, specifies to contact
applicable compliance time specified in table Instructions of Airbus Service Bulletin A300– Airbus for appropriate action, and specifies
2 to paragraphs (g)(1) and (g)(2) of this AD, 53–6178, dated March 17, 2015. Where that action as ‘‘RC’’: Before further flight,
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![Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43163
accomplish corrective actions in accordance (2) Contacting the Manufacturer: As of the National Archives and Records
with the procedures specified in paragraph effective date of this AD, for any requirement Administration (NARA). For information on
(l)(2) of this AD. in this AD to obtain corrective actions from the availability of this material at NARA, call
a manufacturer, the action must be 202–741–6030, or go to: http://
(h) Additional Post-Modification Actions accomplished using a method approved by www.archives.gov/federal-register/cfr/ibr-
Prior to exceeding 24,100 total flight cycles the Manager, International Section, Transport locations.html.
or 42,000 total flight hours, whichever occurs Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the Issued in Renton, Washington, on August
first after doing the modification required by
DOA, the approval must include the DOA- 29, 2017.
paragraph (g)(2) of this AD: Contact the
Manager, International Section, Transport authorized signature. Jeffrey E. Duven,
Standards Branch, FAA; or the European (3) Required for Compliance (RC): Except Director, System Oversight Division, Aircraft
Aviation Safety Agency (EASA); or Airbus’s as required by paragraphs (g)(1) and (g)(2) of Certification Service.
EASA Design Organization Approval (DOA); this AD: If any service information contains [FR Doc. 2017–19303 Filed 9–13–17; 8:45 am]
for instructions to do additional actions, and procedures or tests that are identified as RC,
BILLING CODE 4910–13–P
do those actions at the compliance times those procedures and tests must be done to
stated therein. comply with this AD; any procedures or tests
that are not identified as RC are
(i) Definition of AFT recommended. Those procedures and tests DEPARTMENT OF TRANSPORTATION
For the purpose of this AD, to establish the that are not identified as RC may be deviated
applicable AFT for the actions required by from using accepted methods in accordance Federal Aviation Administration
paragraph (g)(1) of this AD, divide the total with the operator’s maintenance or
accumulated flight hours counted from take- inspection program without obtaining 14 CFR Part 39
off to touch-down by the total accumulated approval of an AMOC, provided the
procedures and tests identified as RC can be [Docket No. FAA–2017–0524; Product
flight cycles as of the effective date of this Identifier 2016–NM–122–AD; Amendment
done and the airplane can be put back in an
AD. 39–19034; AD 2017–19–04]
airworthy condition. Any substitutions or
(j) Credit for Previous Actions changes to procedures or tests identified as
RC require approval of an AMOC. RIN 2120–AA64
This paragraph provides credit for the
modification required by paragraph (g)(1) of (m) Related Information Airworthiness Directives; Dassault
this AD, if the modification was performed (1) Refer to Mandatory Continuing Aviation Airplanes
before the effective date of this AD using the Airworthiness Information (MCAI) EASA
service information specified in paragraph Airworthiness Directive 2016–0249, dated AGENCY: Federal Aviation
(j)(1), (j)(2), (j)(3), or (j)(4) of this AD. December 14, 2016; corrected January 10, Administration (FAA), Department of
(1) Airbus Service Bulletin A300–53–6125, 2017; for related information. This MCAI Transportation (DOT).
dated November 8, 2000, which is not may be found in the AD docket on the
incorporated by reference in this AD. ACTION: Final rule.
Internet at http://www.regulations.gov by
(2) Airbus Service Bulletin A300–53–6125, searching for and locating Docket No. FAA–
Revision 01, dated June 13, 2003, which was SUMMARY: We are adopting a new
2016–0451. airworthiness directive (AD) for certain
incorporated by reference in AD 2004–23–20. (2) For more information about this AD,
(3) Airbus Service Bulletin A300–53–6125, contact Dan Rodina, Aerospace Engineer,
Dassault Aviation Model FALCON
Revision 02, dated February 25, 2005, which International Section, Transport Standards 900EX airplanes. This AD was
is not incorporated by reference in this AD. Branch, 1601 Lind Avenue SW., Renton, WA prompted by a determination that new
(4) Airbus Service Bulletin A300–53–6125, 98057–3356; telephone 425–227–2125; fax or more restrictive maintenance
Revision 03, dated September 13, 2011, 425- 227–1149. requirements and/or airworthiness
which is not incorporated by reference in this (3) Service information identified in this limitations are necessary. This AD
AD. AD that is not incorporated by reference is requires revising the maintenance or
(k) Exempt Airplanes available at the addresses specified in inspection program, as applicable, to
paragraphs (n)(3) and (n)(4) of this AD.
For airplanes on which Airbus incorporate new or more restrictive
Modification 12168 has been embodied in (n) Material Incorporated by Reference maintenance requirements and/or
production: The modification required by (1) The Director of the Federal Register airworthiness limitations. We are
paragraph (g)(1) of this AD is not required by approved the incorporation by reference issuing this AD to address the unsafe
this AD. (IBR) of the service information listed in this condition on these products.
paragraph under 5 U.S.C. 552(a) and 1 CFR
(l) Other FAA AD Provisions DATES: This AD is effective October 19,
part 51.
The following provisions also apply to this (2) You must use this service information 2017.
AD: as applicable to do the actions required by The Director of the Federal Register
(1) Alternative Methods of Compliance this AD, unless this AD specifies otherwise. approved the incorporation by reference
(AMOCs): The Manager, International (i) Airbus Service Bulletin A300–53–6125, of a certain publication listed in this AD
Section, Transport Standards Branch, FAA, Revision 04, dated March 17, 2015. as of October 19, 2017.
has the authority to approve AMOCs for this (ii) Airbus Service Bulletin A300–53–6178, ADDRESSES: For service information
AD, if requested using the procedures found dated March 17, 2015.
in 14 CFR 39.19. In accordance with 14 CFR (3) For service information identified in
identified in this final rule, contact
39.19, send your request to your principal this AD, contact Airbus SAS, Airworthiness Dassault Falcon Jet Corporation,
inspector or local Flight Standards District Office—EAW, 1 Rond Point Maurice Teterboro Airport, P.O. Box 2000, South
Office, as appropriate. If sending information Bellonte, 31707 Blagnac Cedex, France; Hackensack, NJ 07606; telephone 201–
directly to the International Section, send it telephone +33 5 61 93 36 96; fax +33 5 61 440–6700; Internet http://
to the attention of the person identified in 93 44 51; email account.airworth-eas@ www.dassaultfalcon.com. You may
paragraph (m)(2) of this AD. Information may airbus.com; Internet http://www.airbus.com.
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view this referenced service information
be emailed to: 9-ANM-116-AMOC- (4) You may view this service information at the FAA, Transport Standards
REQUESTS@faa.gov. Before using any at the FAA, Transport Standards Branch,
approved AMOC, notify your appropriate 1601 Lind Avenue SW., Renton, WA. For
Branch, 1601 Lind Avenue SW., Renton,
principal inspector, or lacking a principal information on the availability of this WA. For information on the availability
inspector, the manager of the local flight material at the FAA, call 425–227–1221. of this material at the FAA, call 425–
standards district office/certificate holding (5) You may view this service information 227–1221. It is also available on the
district office. that is incorporated by reference at the Internet at http://www.regulations.gov
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Document Created: 2017-09-13 23:49:34
Document Modified: 2017-09-13 23:49:34
| 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 October 19, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 82 FR 43160 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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