81 FR 61990 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 174 (September 8, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 174 (September 8, 2016)
| Page Range | 61990-61993 | |
| FR Document | 2016-21283 |
[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)] [Rules and Regulations] [Pages 61990-61993] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-21283] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-AD; Amendment 39-18643; AD 2016-18-12] 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 A300 B4-203 and A300 B4-2C airplanes. This AD was prompted by cracks found on pylon side panels (upper section) at rib 8. This AD requires a detailed inspection for crack indications of the pylon side panels; a high frequency eddy current (HFEC) inspection to confirm any crack indications; and repair of any cracking, or modification of the pylon side panels, and repetitive inspections and repair if necessary. We are issuing this AD to detect and correct cracking of the pylon side panels. Such cracking could result in pylon structural failure and in- flight loss of an engine. DATES: This AD is effective October 13, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 13, 2016. 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 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- 6671. 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- 6671; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: 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 A300 B4-203 and A300 B4-2C airplanes. The NPRM published in the Federal Register on May 23, 2016 (81 FR 32256) (``the NPRM''). The NPRM was prompted by cracks found on pylon side panels (upper section) at rib 8. The NPRM proposed to require a detailed inspection for crack indications of the pylon side panels; an HFEC inspection to confirm any crack indications; and repair of any cracking, or modification of the pylon side panels, and repetitive inspections and repair if necessary. We are issuing this AD to detect and correct [[Page 61991]] cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0201, dated October 7, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-203 and A300 B4-2C airplanes. The MCAI states: Cracks were found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300-600 aeroplanes equipped with General Electric engines. Investigation of these findings indicated that this problem was likely to also affect aeroplanes of this type design with other engine installations. This condition, if not detected and corrected, could lead to reduced strength of the pylon primary structure, possibly resulting in pylon structural failure and in-flight loss of an engine. Prompted by these findings, EASA issued AD 2008-0181 [which corresponded to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428, March 11, 2010; corrected May 4, 2010 (75 FR 23572))] to require repetitive detailed visual inspections and, depending on aeroplane configuration and/or findings, the accomplishment of applicable corrective action(s). Since that [EASA] AD 2008-0181 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the risk for these aeroplanes is higher than initially determined and consequently, the threshold and interval were reduced to allow timely detection of these cracks and the accomplishment of applicable corrective action(s). Consequently, EASA AD 2013-0136 was published to supersede EASA AD 2008-0181 and to require the inspections to be accomplished within reduced thresholds and intervals. Afterwards, [EASA] AD 2013- 0136 was mistakenly revised [EASA AD 2013-0136R1 corresponds to FAA AD 2015-26-06, Amendment 39-18354 (81 FR 1870 January 14, 2016)] to reduce the Applicability, because it was considered at the time that aeroplanes on which Airbus mod 03599 was embodied, were not concerned by the requirements of EASA AD 2013-0136. Since EASA AD 2013-0136R1 was issued, a more thorough analysis determined that post-mod 03599 aeroplanes could be affected by this unsafe condition after all. [During] further deeper review, a list of nineteen A300 aeroplanes was identified as missing in the [EASA] AD 2013-0136R1 applicability (aeroplanes post-mod 03599). For the reasons described above this AD retains the requirements of EASA AD 2013-0136R1 and mandates these requirements for the 19 missing A300 aeroplanes MSNs [manufacturer serial numbers]. 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- 6671. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant 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 NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-54-0075, Revision 04, dated May 26, 2015. The service information describes procedures for an inspection for crack indications of the pylons, a HFEC inspection to confirm cracking, modification of the pylon side panels, and repair if necessary. Airbus has also issued Service Bulletin A300-54-0081, dated August 11, 1993. This service information describes installation of a doubler on the left pylon 1 and right pylon 2, on pylon side panels (upper section) at Rib 8. 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 4 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspection of the pylon side panels.. 30 work-hours x $85 per $2,550 per inspection $10,200 per inspection hour = $2,550 per cycle. cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of determining the number of airplanes that might need this repair. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Crack repair......................... 56 work-hours x $85 per $3,910 per repair...... $8,670 per repair. hour = $4,760 per repair. ---------------------------------------------------------------------------------------------------------------- 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 [[Page 61992]] 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. 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): 2016-18-12 Airbus: Amendment 39-18643; Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-AD. (a) Effective Date This AD is effective October 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4-203 and A300 B4-2C airplanes, certificated in any category, manufacturer serial numbers 210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259, 261, 274, 277, 292, 299, and 302. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/ Pylons. (e) Reason This AD was prompted by cracks found on pylon side panels (upper section) at rib 8. We are issuing this AD to detect and correct cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Detailed Inspection of Pylons and Corrections At the applicable time specified in Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 2015: Do a detailed inspection for crack indications of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 2015. (h) Crack Confirmation If any crack indication is found during the inspection required by paragraph (g) of this AD: Before further flight, do a high frequency eddy current (HFEC) inspection to confirm the crack, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 2015. (i) Follow-on Actions for No Crack/Indication If the inspection required by paragraph (g) of this AD reveals no crack indication, or if the HFEC inspection specified by paragraph (h) of this AD confirms no crack: Do the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Repeat the inspection required by paragraph (g) of this AD at the applicable time specified in Airbus Service Bulletin A300-54- 0075, Revision 04, dated May 26, 2015. (2) At the applicable time specified in Airbus Service Bulletin A300-54-0081, dated August 11, 1993: Modify the pylons, in accordance with Airbus Service Bulletin A300-54-0081, dated August 11, 1993. Thereafter, repeat the HFEC inspection specified in paragraph (h) of this AD at the applicable interval specified in Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 2015, and repair any crack before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) Follow-on Actions for Crack Findings If any crack is confirmed during the inspection required by paragraph (h) of this AD, repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (h), (i), and (j) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraphs (k)(1) through (k)(4) of this AD. (1) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, which was incorporated by referenced in AD 2010-06-04, Amendment 39- 16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). (2) Airbus Service Bulletin A300-54-0075, Revision 01, dated November 9, 2007. (3) Airbus Service Bulletin A300-54-0075, Revision 02, dated June 26, 2008. (4) Airbus Service Bulletin A300-54-0075, Revision 03, dated March 27, 2013. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0201, dated October 7, 2015, 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-2016-6671. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraph (n)(3) 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 A300-54-0075, Revision 04, dated May 26, 2015. [[Page 61993]] (ii) Airbus Service Bulletin A300-54-0081, dated August 11, 1993. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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 August 25, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-21283 Filed 9-7-16; 8:45 am] BILLING CODE 4910-13-P
![61990 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations
CFR 39.19. In accordance with 14 CFR 39.19, (3) For Gulfstream service information of a certain publication listed in this AD
send your request to your principal inspector identified in this AD, contact Gulfstream as of October 13, 2016.
or local Flight Standards District Office, as Aerospace Corporation, Technical
ADDRESSES: For service information
appropriate. If sending information directly Publications Dept., P.O. Box 2206, Savannah,
to the manager of the ACO, send it to the GA 31402–2206; telephone 800–810–4853; identified in this final rule, contact
attention of the person identified in fax 912–965–3520; email pubs@ Airbus SAS, Airworthiness Office—
paragraph (l) of this AD. gulfstream.com; Internet http:// EAW, 1 Rond Point Maurice Bellonte,
(2) Before using any approved AMOC, www.gulfstream.com/product_support/ 31707 Blagnac Cedex, France; telephone
notify your appropriate principal inspector, technical_pubs/pubs/index.htm. +33 5 61 93 36 96; fax +33 5 61 93 44
or lacking a principal inspector, the manager (4) You may view this service information 51; email account.airworth-eas@
of the local flight standards district office/ at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
airbus.com; Internet http://
certificate holding district office. www.airbus.com. You may view this
information on the availability of this
(l) Related Information material at the FAA, call 425–227–1221. referenced service information at the
For more information about this AD, (5) You may view this service information FAA, Transport Airplane Directorate,
contact Gideon Jose, Aerospace Engineer, that is incorporated by reference at the 1601 Lind Avenue SW., Renton, WA.
Systems and Equipment Branch, ACE–119A, National Archives and Records For information on the availability of
FAA, Atlanta Aircraft Certification Office Administration (NARA). For information on this material at the FAA, call 425–227–
(ACO), 1701 Columbia Avenue, College Park, the availability of this material at NARA, call
1221. It is also available on the Internet
Georgia 30337; phone: 404–474–5569; fax: 202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- at http://www.regulations.gov by
404–474–5606; email: Gideon.Jose@faa.gov. searching for and locating Docket No.
locations.html.
(m) Material Incorporated by Reference FAA–2016–6671.
Issued in Renton, Washington, on August
(1) The Director of the Federal Register 24, 2016. Examining the AD Docket
approved the incorporation by reference John P. Piccola, Jr.,
(IBR) of the service information listed in this You may examine the AD docket on
paragraph under 5 U.S.C. 552(a) and 1 CFR Acting Manager, Transport Airplane the Internet at http://
part 51. Directorate, Aircraft Certification Service. www.regulations.gov by searching for
(2) You must use this service information [FR Doc. 2016–21155 Filed 9–7–16; 8:45 am] and locating Docket No. FAA–2016–
as applicable to do the actions required by BILLING CODE 4910–13–P 6671; or in person at the Docket
this AD, unless the AD specifies otherwise. Management Facility between 9 a.m.
(i) Gulfstream G300 Maintenance Manual
and 5 p.m., Monday through Friday,
Temporary Revision (TR) 32–2, dated April DEPARTMENT OF TRANSPORTATION
29, 2016. except Federal holidays. The AD docket
(ii) Gulfstream G300 Maintenance Manual Federal Aviation Administration contains this AD, the regulatory
TR 5–3, dated April 29, 2016. evaluation, any comments received, and
(iii) Gulfstream G350 Maintenance Manual 14 CFR Part 39 other information. The street address for
TR 32–1, dated April 22, 2016. the Docket Office (telephone 800–647–
(iv) Gulfstream G350 Maintenance Manual [Docket No. FAA–2016–6671; Directorate 5527) is Docket Management Facility,
TR 5–2, dated April 22, 2016. Identifier 2015–NM–164–AD; Amendment U.S. Department of Transportation,
(v) Gulfstream G400 Maintenance Manual 39–18643; AD 2016–18–12] Docket Operations, M–30, West
TR 32–2, dated April 29, 2016.
RIN 2120–AA64 Building Ground Floor, Room W12–140,
(vi) Gulfstream G400 Maintenance Manual
TR 5–3, dated April 29, 2016. 1200 New Jersey Avenue SE.,
(vii) Gulfstream G450 Maintenance Manual
Airworthiness Directives; Airbus Washington, DC 20590.
TR 32–1, dated April 22, 2016. Airplanes FOR FURTHER INFORMATION CONTACT: Dan
(viii) Gulfstream G450 Maintenance AGENCY: Federal Aviation Rodina, Aerospace Engineer,
Manual TR 5–2, dated April 22, 2016. Administration (FAA), Department of International Branch, ANM 116,
(ix) Gulfstream G500 Maintenance Manual Transport Airplane Directorate, FAA,
TR 32–1, dated May 20, 2016.
Transportation (DOT).
ACTION: Final rule. 1601 Lind Avenue SW., Renton, WA
(x) Gulfstream G500 Maintenance Manual
TR 5–3, dated May 20, 2016.
98057–3356; telephone 425–227–2125;
(xi) Gulfstream G550 Maintenance Manual SUMMARY: We are adopting a new fax 425–227–1149.
TR 32–1, dated May 20, 2016. airworthiness directive (AD) for certain SUPPLEMENTARY INFORMATION:
(xii) Gulfstream G550 Maintenance Manual Airbus Model A300 B4–203 and A300
TR 5–3, dated May 20, 2016. B4–2C airplanes. This AD was Discussion
(xiii) Gulfstream II Maintenance Manual prompted by cracks found on pylon side We issued a notice of proposed
TR 32–1, dated April 15, 2016. panels (upper section) at rib 8. This AD rulemaking (NPRM) to amend 14 CFR
(xiv) Gulfstream II Maintenance Manual TR requires a detailed inspection for crack part 39 by adding an AD that would
5–3, dated April 15, 2016. indications of the pylon side panels; a apply to certain Airbus Model A300 B4–
(xv) Gulfstream IIB Maintenance Manual
TR 32–3, dated April 15, 2016.
high frequency eddy current (HFEC) 203 and A300 B4–2C airplanes. The
(xvi) Gulfstream IIB Maintenance Manual inspection to confirm any crack NPRM published in the Federal
TR 5–3, dated April 15, 2016. indications; and repair of any cracking, Register on May 23, 2016 (81 FR 32256)
(xvii) Gulfstream III Maintenance Manual or modification of the pylon side panels, (‘‘the NPRM’’). The NPRM was
TR 32–1, dated April 15, 2016. and repetitive inspections and repair if prompted by cracks found on pylon side
(xviii) Gulfstream III Maintenance Manual necessary. We are issuing this AD to panels (upper section) at rib 8. The
TR 5–2, dated April 15, 2016. detect and correct cracking of the pylon NPRM proposed to require a detailed
(xix) Gulfstream IV Maintenance Manual side panels. Such cracking could result inspection for crack indications of the
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TR 32–2, dated April 29, 2016. in pylon structural failure and in-flight pylon side panels; an HFEC inspection
(xx) Gulfstream IV Maintenance Manual
TR 5–7, dated April 29, 2016.
loss of an engine. to confirm any crack indications; and
(xxi) Gulfstream V Maintenance Manual DATES: This AD is effective October 13, repair of any cracking, or modification
TR 32–2, dated May 20, 2016. 2016. of the pylon side panels, and repetitive
(xxii) Gulfstream V Maintenance Manual The Director of the Federal Register inspections and repair if necessary. We
TR 5–3, dated May 20, 2016. approved the incorporation by reference are issuing this AD to detect and correct
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![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 61991
cracking of the pylon side panels. Such were reduced to allow timely detection of public interest require adopting this AD
cracking could result in pylon structural these cracks and the accomplishment of as proposed, except for minor editorial
failure and in-flight loss of an engine. applicable corrective action(s). changes. We have determined that these
Consequently, EASA AD 2013–0136 was
The European Aviation Safety Agency published to supersede EASA AD 2008–0181 minor changes:
(EASA), which is the Technical Agent and to require the inspections to be • Are consistent with the intent that
for the Member States of the European accomplished within reduced thresholds and was proposed in the NPRM for
Union, has issued EASA Airworthiness intervals. Afterwards, [EASA] AD 2013–0136 correcting the unsafe condition; and
Directive 2015–0201, dated October 7, was mistakenly revised [EASA AD 2013–
2015 (referred to after this as the 0136R1 corresponds to FAA AD 2015–26–06, • Do not add any additional burden
Mandatory Continuing Airworthiness Amendment 39–18354 (81 FR 1870 January upon the public than was already
14, 2016)] to reduce the Applicability, proposed in the NPRM.
Information, or ‘‘the MCAI’’), to correct because it was considered at the time that
an unsafe condition for certain Airbus aeroplanes on which Airbus mod 03599 was Related Service Information Under 1
Model A300 B4–203 and A300 B4–2C embodied, were not concerned by the CFR Part 51
airplanes. The MCAI states: requirements of EASA AD 2013–0136.
Cracks were found on pylon side panels Since EASA AD 2013–0136R1 was issued, Airbus has issued Service Bulletin
(upper section) at rib 8 on Airbus A300, A310 a more thorough analysis determined that A300–54–0075, Revision 04, dated May
and A300–600 aeroplanes equipped with post-mod 03599 aeroplanes could be affected 26, 2015. The service information
by this unsafe condition after all.
General Electric engines. Investigation of describes procedures for an inspection
[During] further deeper review, a list of
these findings indicated that this problem for crack indications of the pylons, a
nineteen A300 aeroplanes was identified as
was likely to also affect aeroplanes of this HFEC inspection to confirm cracking,
missing in the [EASA] AD 2013–0136R1
type design with other engine installations. modification of the pylon side panels,
applicability (aeroplanes post-mod 03599).
This condition, if not detected and
corrected, could lead to reduced strength of
For the reasons described above this AD and repair if necessary.
retains the requirements of EASA AD 2013–
the pylon primary structure, possibly 0136R1 and mandates these requirements for Airbus has also issued Service
resulting in pylon structural failure and in- the 19 missing A300 aeroplanes MSNs Bulletin A300–54–0081, dated August
flight loss of an engine. [manufacturer serial numbers]. 11, 1993. This service information
Prompted by these findings, EASA issued describes installation of a doubler on
AD 2008–0181 [which corresponded to FAA You may examine the MCAI in the
AD docket on the Internet at http:// the left pylon 1 and right pylon 2, on
AD 2010–06–04, Amendment 39–16228 (75
FR 11428, March 11, 2010; corrected May 4, www.regulations.gov by searching for pylon side panels (upper section) at Rib
2010 (75 FR 23572))] to require repetitive and locating Docket No. FAA–2016– 8.
detailed visual inspections and, depending 6671. This service information is reasonably
on aeroplane configuration and/or findings, available because the interested parties
the accomplishment of applicable corrective Comments
have access to it through their normal
action(s). We gave the public the opportunity to
Since that [EASA] AD 2008–0181 was
course of business or by the means
participate in developing this AD. We identified in the ADDRESSES section.
issued, a fleet survey and updated Fatigue
and Damage Tolerance analyses have been
received no comments on the NPRM or
on the determination of the cost to the Costs of Compliance
performed in order to substantiate the second
A300–600 Extended Service Goal (ESG2) public.
We estimate that this AD affects 4
exercise. The results of these analyses have Conclusion airplanes of U.S. registry.
shown that the risk for these aeroplanes is
higher than initially determined and We reviewed the relevant data and We estimate the following costs to
consequently, the threshold and interval determined that air safety and the comply with this AD:
ESTIMATED COSTS
Action Labor cost Cost per product Cost on U.S. operators
Inspection of the pylon side panels 30 work-hours × $85 per hour = $2,550 per inspection cycle .......... $10,200 per inspection cycle.
$2,550 per inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary repairs that would be inspection. We have no way of that might need this repair.
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Crack repair ................................... 56 work-hours × $85 per hour = $3,910 per repair .......................... $8,670 per repair.
$4,760 per repair.
Authority for This Rulemaking detail the scope of the Agency’s promoting safe flight of civil aircraft in
authority. air commerce by prescribing regulations
Lhorne on DSK30JT082PROD with RULES
Title 49 of the United States Code
specifies the FAA’s authority to issue We are issuing this rulemaking under for practices, methods, and procedures
rules on aviation safety. Subtitle I, the authority described in ‘‘Subtitle VII, the Administrator finds necessary for
section 106, describes the authority of Part A, Subpart III, Section 44701: safety in air commerce. This regulation
the FAA Administrator. ‘‘Subtitle VII: General requirements.’’ Under that is within the scope of that authority
Aviation Programs,’’ describes in more section, Congress charges the FAA with because it addresses an unsafe condition
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![61992 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations
that is likely to exist or develop on (e) Reason before the effective date of this AD using the
products identified in this rulemaking This AD was prompted by cracks found on service information specified in paragraphs
action. pylon side panels (upper section) at rib 8. We (k)(1) through (k)(4) of this AD.
are issuing this AD to detect and correct (1) Airbus Service Bulletin A300–54–0075,
Regulatory Findings cracking of the pylon side panels. Such dated August 11, 1993, which was
cracking could result in pylon structural incorporated by referenced in AD 2010–06–
We determined that this AD will not 04, Amendment 39–16228 (75 FR 11428,
have federalism implications under failure and in-flight loss of an engine.
March 11, 2010); corrected May 4, 2010 (75
Executive Order 13132. This AD will (f) Compliance FR 23572).
not have a substantial direct effect on Comply with this AD within the (2) Airbus Service Bulletin A300–54–0075,
the States, on the relationship between compliance times specified, unless already Revision 01, dated November 9, 2007.
the national government and the States, done. (3) Airbus Service Bulletin A300–54–0075,
or on the distribution of power and Revision 02, dated June 26, 2008.
(g) Detailed Inspection of Pylons and (4) Airbus Service Bulletin A300–54–0075,
responsibilities among the various Corrections Revision 03, dated March 27, 2013.
levels of government.
At the applicable time specified in Airbus
For the reasons discussed above, I (l) Other FAA AD Provisions
Service Bulletin A300–54–0075, Revision 04,
certify that this AD: dated May 26, 2015: Do a detailed inspection The following provisions also apply to this
1. Is not a ‘‘significant regulatory for crack indications of the pylons 1 and 2 AD:
action’’ under Executive Order 12866; side panels (upper section) at rib 8, in (1) Alternative Methods of Compliance
2. Is not a ‘‘significant rule’’ under the accordance with the Accomplishment (AMOCs): The Manager, International
DOT Regulatory Policies and Procedures Instructions of Airbus Service Bulletin A300– Branch, ANM–116, FAA, has the authority to
(44 FR 11034, February 26, 1979); 54–0075, Revision 04, dated May 26, 2015. approve AMOCs for this AD, if requested
3. Will not affect intrastate aviation in using the procedures found in 14 CFR 39.19.
(h) Crack Confirmation In accordance with 14 CFR 39.19, send your
Alaska; and
4. Will not have a significant If any crack indication is found during the request to your principal inspector or local
inspection required by paragraph (g) of this Flight Standards District Office, as
economic impact, positive or negative, appropriate. If sending information directly
AD: Before further flight, do a high frequency
on a substantial number of small entities eddy current (HFEC) inspection to confirm to the International Branch, send it to ATTN:
under the criteria of the Regulatory the crack, in accordance with the Dan Rodina, Aerospace Engineer,
Flexibility Act. Accomplishment Instructions of Airbus International Branch, ANM–116, Transport
Service Bulletin A300–54–0075, Revision 04, Airplane Directorate, FAA, 1601 Lind
List of Subjects in 14 CFR Part 39 Avenue SW., Renton, WA 98057–3356;
dated May 26, 2015.
Air transportation, Aircraft, Aviation telephone 425–227–2125; fax 425–227–1149.
(i) Follow-on Actions for No Crack/ Information may be emailed to: 9-ANM-116-
safety, Incorporation by reference, Indication
Safety. AMOC-REQUESTS@faa.gov. Before using
If the inspection required by paragraph (g) any approved AMOC, notify your appropriate
Adoption of the Amendment of this AD reveals no crack indication, or if principal inspector, or lacking a principal
the HFEC inspection specified by paragraph inspector, the manager of the local flight
Accordingly, under the authority
(h) of this AD confirms no crack: Do the standards district office/certificate holding
delegated to me by the Administrator, actions specified in either paragraph (i)(1) or district office. The AMOC approval letter
the FAA amends 14 CFR part 39 as (i)(2) of this AD. must specifically reference this AD.
follows: (1) Repeat the inspection required by (2) Contacting the Manufacturer: For any
paragraph (g) of this AD at the applicable requirement in this AD to obtain corrective
PART 39—AIRWORTHINESS time specified in Airbus Service Bulletin actions from a manufacturer, the action must
DIRECTIVES A300–54–0075, Revision 04, dated May 26, be accomplished using a method approved
2015. by the Manager, International Branch, ANM–
■ 1. The authority citation for part 39 (2) At the applicable time specified in 116, Transport Airplane Directorate, FAA; or
continues to read as follows: Airbus Service Bulletin A300–54–0081, the EASA; or Airbus’s EASA DOA. If
dated August 11, 1993: Modify the pylons, in approved by the DOA, the approval must
Authority: 49 U.S.C. 106(g), 40113, 44701.
accordance with Airbus Service Bulletin include the DOA-authorized signature.
§ 39.13 [Amended] A300–54–0081, dated August 11, 1993.
(m) Related Information
Thereafter, repeat the HFEC inspection
■ 2. The FAA amends § 39.13 by adding specified in paragraph (h) of this AD at the (1) Refer to Mandatory Continuing
the following new airworthiness applicable interval specified in Airbus Airworthiness Information (MCAI) EASA
directive (AD): Service Bulletin A300–54–0075, Revision 04, Airworthiness Directive 2015–0201, dated
dated May 26, 2015, and repair any crack October 7, 2015, for related information. This
2016–18–12 Airbus: Amendment 39–18643;
before further flight using a method approved MCAI may be found in the AD docket on the
Docket No. FAA–2016–6671; Directorate
by the Manager, International Branch, ANM– Internet at http://www.regulations.gov by
Identifier 2015–NM–164–AD.
116, Transport Airplane Directorate, FAA; or searching for and locating Docket No. FAA–
(a) Effective Date the European Aviation Safety Agency 2016–6671.
This AD is effective October 13, 2016. (EASA); or Airbus’s EASA Design (2) Service information identified in this
Organization Approval (DOA). AD that is not incorporated by reference is
(b) Affected ADs available at the addresses specified in
(j) Follow-on Actions for Crack Findings paragraph (n)(3) of this AD.
None.
If any crack is confirmed during the
(c) Applicability (n) Material Incorporated by Reference
inspection required by paragraph (h) of this
This AD applies to Airbus Model A300 B4– AD, repair before further flight using a (1) The Director of the Federal Register
203 and A300 B4–2C airplanes, certificated method approved by the Manager, approved the incorporation by reference
in any category, manufacturer serial numbers International Branch, ANM–116, Transport (IBR) of the service information listed in this
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210, 212, 218, 220, 227, 234, 235, 236, 239, Airplane Directorate, FAA; or EASA; or paragraph under 5 U.S.C. 552(a) and 1 CFR
247, 255, 256, 259, 261, 274, 277, 292, 299, Airbus’s EASA DOA. part 51.
and 302. (2) You must use this service information
(k) Credit for Previous Actions as applicable to do the actions required by
(d) Subject This paragraph provides credit for actions this AD, unless this AD specifies otherwise.
Air Transport Association (ATA) of required by paragraphs (g), (h), (i), and (j) of (i) Airbus Service Bulletin A300–54–0075,
America Code 54, Nacelles/Pylons. this AD, if those actions were performed Revision 04, dated May 26, 2015.
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![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 61993
(ii) Airbus Service Bulletin A300–54–0081, DATES: This AD is effective October 13, Airworthiness Information, or ‘‘the
dated August 11, 1993. 2016. MCAI’’), to correct an unsafe condition
(3) For service information identified in The Director of the Federal Register for certain Airbus Model A318, A319,
this AD, contact Airbus SAS, Airworthiness approved the incorporation by reference and A320 series airplanes. The MCAI
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
of certain publications listed in this AD states:
telephone +33 5 61 93 36 96; fax +33 5 61 as of October 13, 2016. An operator reported finding chafing
93 44 51; email account.airworth-eas@ ADDRESSES: For service information damage on the fuselage skin at the bottom of
airbus.com; Internet http://www.airbus.com. identified in this final rule, contact frame (FR) 34 junction between stringer
You may view this service information at the Airbus, Airworthiness Office—EIAS, 1 (STR) 43 left hand (LH) side and right hand
FAA, Transport Airplane Directorate, 1601 Rond Point Maurice Bellonte, 31707 (RH) side on several aeroplanes, underneath
Lind Avenue SW., Renton, WA. For Blagnac Cedex, France; telephone +33 5 the fairing structure.
information on the availability of this After investigation, a contact between the
61 93 36 96; fax +33 5 61 93 44 51; email
material at the FAA, call 425–227–1221. fairing nut plate and the fuselage was
(4) You may view this service information account.airworth-eas@airbus.com; identified, causing damage to the fuselage.
at the FAA, Transport Airplane Directorate, Internet http://www.airbus.com. You This condition, if not detected and
1601 Lind Avenue SW., Renton, WA. For may view this referenced service corrected, could lead to crack initiation and
information on the availability of this information at the FAA, Transport propagation, possibly resulting in reduced
material at the FAA, call 425–227–1221. Airplane Directorate, 1601 Lind Avenue structural integrity of the fuselage.
(5) You may view this service information SW., Renton, WA. For information on For the reason described above, this
that is incorporated by reference at the the availability of this material at the [EASA] AD requires repetitive detailed
National Archives and Records FAA, call 425–227–1221. It is also inspections (DET) of the fuselage [for chafing]
Administration (NARA). For information on at FR 34 and provides an optional
available on the Internet at http://
the availability of this material at NARA, call terminating action [modification of the belly
202–741–6030, or go to: http:// www.regulations.gov by searching for fairing] to the repetitive inspections required
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2015– by this [EASA] AD.
locations.html. 5814.
Related investigative actions include a
Issued in Renton, Washington, on August Examining the AD Docket special detailed inspection of external
25, 2016. fuselage skin panel for any cracking,
You may examine the AD docket on
John P. Piccola, Jr., and measurement of crack length and
the Internet at http://
Acting Manager, Transport Airplane www.regulations.gov by searching for remaining thickness. Corrective actions
Directorate, Aircraft Certification Service. include repair or modification of the
and locating Docket No. FAA–2015–
[FR Doc. 2016–21283 Filed 9–7–16; 8:45 am] 5814; or in person at the Docket fuselage skin panel. You may examine
BILLING CODE 4910–13–P Management Facility between 9 a.m. the MCAI in the AD docket on the
and 5 p.m., Monday through Friday, Internet at http://www.regulations.gov
except Federal holidays. The AD docket by searching for and locating Docket No.
DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory FAA–2015–5814.
Federal Aviation Administration evaluation, any comments received, and Comments
other information. The street address for
We gave the public the opportunity to
14 CFR Part 39 the Docket Office (telephone 800–647–
participate in developing this AD. The
5527) is Docket Management Facility,
[Docket No. FAA–2015–5814; Directorate following presents the comments
U.S. Department of Transportation,
Identifier 2014–NM–247–AD; Amendment received on the NPRM and the FAA’s
Docket Operations, M–30, West
39–18639; AD 2016–18–09] response to each comment.
Building Ground Floor, Room W12–140,
RIN 2120–AA64 1200 New Jersey Avenue SE., Request To Use Latest Service
Washington, DC 20590. Information
Airworthiness Directives; Airbus FOR FURTHER INFORMATION CONTACT: Airbus requested that we revise
Airplanes Sanjay Ralhan, Aerospace Engineer, paragraph (i) of the NPRM to add Airbus
AGENCY: Federal Aviation International Branch, ANM–116, Service Bulletin A320–53–1281,
Administration (FAA), Department of Transport Airplane Directorate, FAA, Revision 02, including Appendix 01,
Transportation (DOT). 1601 Lind Avenue SW., Renton, WA dated October 9, 2015.
ACTION: Final rule. 98057–3356; telephone 425–227–1405; United Airlines also requested that we
fax 425–227–1149. revise paragraph (i) of the NPRM to add
SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION: Airbus Service Bulletin A320–53–1281,
airworthiness directive (AD) for certain Revision 02, including Appendix 01,
Airbus Model A318, A319, and A320 Discussion dated October 9, 2015, and provide
series airplanes. This AD was prompted We issued a notice of proposed credit for Airbus Service Bulletin A320–
by reports of chafing damage on the rulemaking (NPRM) to amend 14 CFR 53–1281, Revision 01, dated December
fuselage skin at the bottom of certain part 39 by adding an AD that would 1, 2014. United Airlines explained that
frames, underneath the fairing structure. apply to certain Airbus Model A318, Airbus Service Bulletin A320–53–1281,
This AD requires repetitive detailed A319, and A320 series airplanes. The Revision 02, including Appendix 01,
inspections for damage on the fuselage NPRM published in the Federal dated October 9, 2015, includes
skin at certain frames, and applicable Register on November 27, 2015 (80 FR numerous configuration additions.
related investigative and corrective 74045) (‘‘the NPRM’’). For the reasons stated by the
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actions. We are issuing this AD to detect The European Aviation Safety Agency commenter, we agree to revise this AD
and correct damage to the fuselage skin, (EASA), which is the Technical Agent to include Airbus Service Bulletin
which could lead to crack initiation and for the Member States of the European A320–53–1281, Revision 02, including
propagation, possibly resulting in Union, has issued EASA AD 2014–0259, Appendix 01, dated October 9, 2015.
reduced structural integrity of the dated December 5, 2014 (referred to Airbus Service Bulletin A320–53–1281,
fuselage. after this as the Mandatory Continuing Revision 02, including Appendix 01,
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Document Created: 2018-02-09 13:12:48
Document Modified: 2018-02-09 13:12:48
| 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 13, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 81 FR 61990 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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