83 FR 52126 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 200 (October 16, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 200 (October 16, 2018)
| Page Range | 52126-52131 | |
| FR Document | 2018-22147 |
[Federal Register Volume 83, Number 200 (Tuesday, October 16, 2018)] [Rules and Regulations] [Pages 52126-52131] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-22147] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0583; Product Identifier 2018-NM-019-AD; Amendment 39-19453; AD 2018-20-19] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2017-16-07, which applied to certain Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-500, and A340-600 series airplanes; and Model A340-313 airplanes. AD 2017-16-07 required inspection of the fuselage bulk cargo door frames at specific locations, and corrective action if necessary. This AD requires new inspections of certain attachment holes for residual surface treatment and cracking, and corrective action if necessary; and provides an optional terminating action for the inspections. This AD also revises the applicability to add certain airplanes and remove others. This AD was prompted by a determination that only airplanes having certain manufacturer serial numbers (MSNs) are affected by tartaric sulfuric anodizing (TSA)/chromic acid anodizing (CAA) surface treatment in the door fitting attachment holes, and that airplanes having certain MSNs were excluded. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 20, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 20, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0583. 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-2018- 0583; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017-16-07, Amendment 39-18984 (82 FR 41874, September 5, 2017) (``AD 2017-16-07''). AD 2017-16-07 applied certain Airbus Model A330-200, A330-200 Freighter, A330-300, A340-500, and A340-600 series airplanes; and Model A340-313 airplanes. The NPRM published in the Federal Register on July 6, 2018 (83 FR 31499). The NPRM was prompted by a determination that only airplanes having certain MSNs are affected by TSA/CAA surface treatment in the door fitting attachment holes, and that airplanes having certain MSNs were excluded. The NPRM was intended to complete certain mandated programs intended to support the airplane reaching its LOV of the engineering data that support the established structural maintenance program. The NPRM proposed to require new inspections of certain attachment holes for residual surface treatment and cracking, and corrective action if necessary; and to provide an optional terminating action for the inspections. The NPRM also proposed to revise the applicability to add certain airplanes and remove others. We are issuing this AD to address fatigue cracks in the bulk cargo door frames, caused by TSA/CAA surface treatment in certain bulk cargo door frame holes. Cracks in the bulk cargo door frames can cause the in-flight loss of a bulk cargo door, damage to the airplane, and subsequent reduced control 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 2018-0005, dated January 10, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes, and Airbus SAS Model A340-200 and A340-300 series airplanes. The MCAI states: In the frame of the certification of the A330 Extended Service Goal exercise, it was [[Page 52127]] identified that Tartaric Sulfuric Anodising (TSA) or Chromic Acid Anodising (CAA) surface treatment is present in some frame holes, from aeroplane MSN [manufacturer serial number] 0400 and later MSN, following production process modification. On bulk cargo door frames (FR) 67 and FR 69 right hand (RH) side, the door fitting attachment holes have this TSA or CAA treatment, which leads to a detrimental effect on fatigue behaviour. This condition, if not detected and corrected, could lead to cracks in the primary structure, possibly resulting in in-flight loss of a bulk cargo door, consequent decompression and potential damage to, and reduced control of, the aeroplane. To initially address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A53L012-16 to provide instructions to inspect the fuselage bulk cargo door frames at specific locations. Consequently, EASA issued AD 2016-0102 [which corresponds to FAA AD 2017-16-07], requiring repetitive non- destructive test (rototest and high-frequency eddy-current (HFEC)) inspection or visual detailed (DET) inspections [to detect cracking] of the affected areas, and, depending on findings, accomplishment of a repair. Since that [EASA] AD was issued, it was determined that only aeroplanes from MSN 0400 to MSN 1779 are affected by CAA or TSA surface treatment issue in the door fitting attachment holes. However, it was also determined that aeroplanes MSN 0001 to MSN 0399 are affected in the same attachment holes due to a fatigue issue, therefore, the same inspections must also be accomplished on these aeroplanes. In addition, based on inspection results and calculation, Airbus redefined inspection thresholds and intervals, depending on aeroplane type, model and utilisation. Airbus published SB A330-53-3278 and SB A340-53-4239 providing the inspection instructions at the specific locations with extended inspection thresholds and intervals. Airbus also determined that the actions should not be required for A340-500 and -600 models, as for these aeroplanes, the unsafe condition would only develop beyond the Design Service Goal of these aeroplanes. Finally, Airbus developed modification (mod) 206409 and published associated SB A330-53-3275 and SB A340-53-4238, as applicable, as optional terminating action. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016-0102, which is superseded, expands the Applicability and requires redefined repetitive inspections of the holes at the upper and lower door support fittings of FR 67 and FR 69 RH and the holes at door latch fitting of FR 69 RH. This [EASA] AD also introduces an optional modification, which constitutes terminating action for the repetitive inspections as required by this [EASA] AD. The optional modification involves related investigative actions of eddy current rotating probe testing for cracks of the support fittings and the frame holes at frame (FR) 67 and FR 69. 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-2018-0583. Comments We gave the public the opportunity to participate in developing this final rule. 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 final rule 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 addressing 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 SAS has issued the following service information. Service Bulletin A330-53-3275, dated September 8, 2017. Service Bulletin A330-53-3278, dated August 22, 2017. Service Bulletin A340-53-4238, dated September 8, 2017. Service Bulletin A340-53-4239, dated September 5, 2017. Airbus Service Bulletins A330-53-3278 and A340-53-4239 describe procedures for rototest, HFEC/ultrasonic and detailed inspections for residual surface treatment and cracking of the upper and lower right- hand fuselage bulk cargo door support fitting attachment holes at FR 67 and FR 69 and the right-hand fuselage bulk cargo door latch fitting attachment holes at FR 69. Airbus Service Bulletins A330-53-3275 and A340-53-4238 describe procedures for a modification, which includes eddy current rotating probe testing for cracks of the support fittings and the frame holes at FR 67 and FR 69, and removal of TSA or CAA in the final holes of the bulk door frames FR 67 and FR 69. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 102 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspections and modification Up to 40 $5,100 Up to $8,500... Up to $867,000. work[dash]hour s x $85 per hour = $3,400. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that enables 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 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 [[Page 52128]] delegated the authority to issue ADs applicable to transport category airplanes and associated appliances 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) 2017-16-07, Amendment 39-18984 (82 FR 41874, September 5, 2017), and adding the following new AD: 2018-20-19 Airbus SAS: Amendment 39-19453; Docket No. FAA-2018-0583; Product Identifier 2018-NM-019-AD. (a) Effective Date This AD is effective November 20, 2018. (b) Affected ADs This AD replaces AD 2017-16-07, Amendment 39-18984 (82 FR 41874, September 5, 2017) (``AD 2017-16-07''). (c) Applicability This AD applies to the following Airbus SAS airplanes, certificated in any category, manufacturer serial numbers (MSNs) 0001 to 1779 inclusive; except airplanes on which Airbus Service Bulletin A330-53-3275 or Airbus Service Bulletin A340-53-4238 has been embodied. (1) Model A330-201, -202, -203, -223, and -243 airplanes. (2) Model A330-223F and -243F airplanes. (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (4) Model A340-211, -212, and -213 airplanes. (5) Model A340-311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD is prompted by a determination that only airplanes having certain MSNs are affected by tartaric sulfuric anodizing (TSA)/chromic acid anodizing (CAA) surface treatment in the door fitting attachment holes, and that airplanes having certain MSNs were excluded from AD 2017-16-07. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct fatigue cracks in the bulk cargo door frames, caused by TSA/CAA surface treatment in certain bulk cargo door frame holes. Cracks in the bulk cargo door frames can cause the in-flight loss of a bulk cargo door, damage to the airplane, and subsequent reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before exceeding the thresholds specified in table 1 to paragraph (g) of this AD, or within the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, whichever is later: Do a rototest, high frequency eddy current (HFEC), ultrasonic, or detailed inspection, as applicable, for residual surface treatment and cracking of the upper and lower right-hand fuselage bulk cargo door support fitting attachment holes at FR 67 and FR 69 and the right-hand fuselage bulk cargo door latch fitting attachment holes at FR 69, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3278, dated August 22, 2017; or Airbus Service Bulletin A340-53-4239, dated September 5, 2017; as applicable. Thereafter, depending on the areas and inspection methods as defined in table 2 to paragraph (g) of this AD, repeat the inspection at intervals not exceeding those specified in table 3 to paragraph (g) of this AD. (1) For airplanes having MSN 0001 through 0399 inclusive: Within 200 flight cycles after the effective date of this AD. (2) For airplanes having MSN 0400 through 1779 inclusive: Within 800 flight cycles after the effective date of this AD. BILLING CODE 4910-13-P [[Page 52129]] [GRAPHIC] [TIFF OMITTED] TR16OC18.003 [[Page 52130]] [GRAPHIC] [TIFF OMITTED] TR16OC18.004 BILLING CODE 4910-13-C (h) Corrective Action If any discrepancy is found during any inspection required by paragraph (g) of this AD, before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Non-Terminating Action for Repairs Accomplishment of a repair on an airplane, as required by paragraph (h) of this AD, does not constitute terminating action for the inspections required by paragraph (g) of this AD for that airplane, unless otherwise specified in repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (j) Optional Terminating Action Accomplishment of the modification, including applicable related investigative and corrective actions and removal of TSA or CAA in the final holes of the bulk door frames FR 67 and FR 69, as applicable, specified in, and in accordance with the AI of Airbus Service Bulletin A330-53-3275, dated September 8, 2017; or Airbus Service Bulletin A340-53-4238, dated September 8, 2017; as applicable; constitutes terminating action for the inspections required by paragraph (g) of this AD for that airplane, unless otherwise specified in the repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Alert Operators Transmission (AOT) A53L012-16, dated May 30, 2016; or Rev 01, dated March 9, 2017. (l) Other FAA AD Provisions (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 manager of the International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 the EASA; or Airbus SAS'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 AD 2018-0005, dated January 10, 2018, 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-2018-0583. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229. (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 A330-53-3275, dated September 8, 2017. (ii) Airbus Service Bulletin A330-53-3278, dated August 22, 2017. (iii) Airbus Service Bulletin A340-53-4238, dated September 8, 2017. (iv) Airbus Service Bulletin A340-53-4239, dated September 5, 2017. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France, France; [[Page 52131]] telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (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 Des Moines, Washington, on September 26, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-22147 Filed 10-15-18; 8:45 am] BILLING CODE 4910-13-P
![52126 Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations
Standards Branch, FAA, 2200 South 216th series airplanes; and Model A340–313 Docket Operations, M–30, West
St., Des Moines, WA 98198; telephone and airplanes. AD 2017–16–07 required Building Ground Floor, Room W12–140,
fax 206–231–3220. inspection of the fuselage bulk cargo 1200 New Jersey Avenue SE,
(m) Material Incorporated by Reference door frames at specific locations, and Washington, DC 20590.
(1) The Director of the Federal Register corrective action if necessary. This AD FOR FURTHER INFORMATION CONTACT:
approved the incorporation by reference requires new inspections of certain Vladimir Ulyanov, Aerospace Engineer,
(IBR) of the service information listed in this attachment holes for residual surface International Section, Transport
paragraph under 5 U.S.C. 552(a) and 1 CFR treatment and cracking, and corrective Standards Branch, FAA, 2200 South
part 51. action if necessary; and provides an 216th St., Des Moines, WA 98198;
(2) You must use this service information optional terminating action for the telephone and fax 206–231–3229.
as applicable to do the actions required by inspections. This AD also revises the
this AD, unless this AD specifies otherwise. SUPPLEMENTARY INFORMATION:
applicability to add certain airplanes
(i) ATR ATR42–400/–500, Time Limits Discussion
Document (TL), Revision 11, dated May 5,
and remove others. This AD was
2015. prompted by a determination that only We issued a notice of proposed
(ii) ATR ATR42–400/–500 Time Limits airplanes having certain manufacturer rulemaking (NPRM) to amend 14 CFR
Temporary Revision TR01/17, dated May 3, serial numbers (MSNs) are affected by part 39 to supersede AD 2017–16–07,
2017. tartaric sulfuric anodizing (TSA)/ Amendment 39–18984 (82 FR 41874,
(3) For service information identified in chromic acid anodizing (CAA) surface September 5, 2017) (‘‘AD 2017–16–07’’).
this AD, contact ATR GIE Avions de treatment in the door fitting attachment AD 2017–16–07 applied certain Airbus
Transport Régional, 1, Allée Pierre Nadot, holes, and that airplanes having certain Model A330–200, A330–200 Freighter,
31712 Blagnac Cedex, France; telephone +33 MSNs were excluded. This AD is
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
A330–300, A340–500, and A340–600
email continued.airworthiness@atr
intended to complete certain mandated series airplanes; and Model A340–313
aircraft.com; internet http://www.atr- programs intended to support the airplanes. The NPRM published in the
aircraft.com. airplane reaching its limit of validity Federal Register on July 6, 2018 (83 FR
(4) You may view this service information (LOV) of the engineering data that 31499). The NPRM was prompted by a
at the FAA, Transport Standards Branch, support the established structural determination that only airplanes
2200 South 216th St., Des Moines, WA. For maintenance program. We are issuing having certain MSNs are affected by
information on the availability of this this AD to address the unsafe condition TSA/CAA surface treatment in the door
material at the FAA, call 206–231–3195. on these products. fitting attachment holes, and that
(5) You may view this service information
that is incorporated by reference at the DATES: This AD is effective November airplanes having certain MSNs were
National Archives and Records 20, 2018. excluded. The NPRM was intended to
Administration (NARA). For information on The Director of the Federal Register complete certain mandated programs
the availability of this material at NARA, call approved the incorporation by reference intended to support the airplane
202–741–6030, or go to: http:// of certain publications listed in this AD reaching its LOV of the engineering data
www.archives.gov/federal-register/cfr/ibr- as of November 20, 2018. that support the established structural
locations.html. maintenance program. The NPRM
ADDRESSES: For service information
Issued in Des Moines, Washington, on identified in this final rule, contact proposed to require new inspections of
September 25, 2018. Airbus SAS, Airworthiness Office— certain attachment holes for residual
John P. Piccola, EAL, Rond-Point Emile Dewoitine No: surface treatment and cracking, and
Acting Director, System Oversight Division, 2, 31700 Blagnac Cedex, France, France; corrective action if necessary; and to
Aircraft Certification Service. telephone +33 5 61 93 36 96; fax +33 5 provide an optional terminating action
[FR Doc. 2018–22140 Filed 10–15–18; 8:45 am] 61 93 45 80; email airworthiness.A330- for the inspections. The NPRM also
BILLING CODE 4910–13–P A340@airbus.com; internet http:// proposed to revise the applicability to
www.airbus.com. You may view this add certain airplanes and remove
referenced service information at the others. We are issuing this AD to
DEPARTMENT OF TRANSPORTATION FAA, Transport Standards Branch, 2200 address fatigue cracks in the bulk cargo
South 216th St., Des Moines, WA. For door frames, caused by TSA/CAA
Federal Aviation Administration information on the availability of this surface treatment in certain bulk cargo
material at the FAA, call 206–231–3195. door frame holes. Cracks in the bulk
14 CFR Part 39 It is also available on the internet at cargo door frames can cause the in-flight
http://www.regulations.gov by searching loss of a bulk cargo door, damage to the
[Docket No. FAA–2018–0583; Product
Identifier 2018–NM–019–AD; Amendment for and locating Docket No. FAA–2018– airplane, and subsequent reduced
39–19453; AD 2018–20–19] 0583. control of the airplane.
The European Aviation Safety Agency
RIN 2120–AA64 Examining the AD Docket (EASA), which is the Technical Agent
You may examine the AD docket on for the Member States of the European
Airworthiness Directives; Airbus SAS Union, has issued EASA AD 2018–0005,
the internet at http://
Airplanes dated January 10, 2018 (referred to after
www.regulations.gov by searching for
AGENCY: Federal Aviation and locating Docket No. FAA–2018– this as the Mandatory Continuing
Administration (FAA), Department of 0583; or in person at Docket Operations Airworthiness Information, or ‘‘the
Transportation (DOT). between 9 a.m. and 5 p.m., Monday MCAI’’), to correct an unsafe condition
through Friday, except Federal holidays. for certain Airbus SAS Model A330–
amozie on DSK3GDR082PROD with RULES
ACTION: Final rule.
The AD docket contains this final rule, 200, A330–200 Freighter, and A330–300
SUMMARY: We are superseding the regulatory evaluation, any series airplanes, and Airbus SAS Model
Airworthiness Directive (AD) 2017–16– comments received, and other A340–200 and A340–300 series
07, which applied to certain Airbus SAS information. The address for Docket airplanes. The MCAI states:
Model A330–200, A330–200 Freighter, Operations (phone: 800–647–5527) is In the frame of the certification of the A330
A330–300, A340–500, and A340–600 U.S. Department of Transportation, Extended Service Goal exercise, it was
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![Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations 52127
identified that Tartaric Sulfuric Anodising the Design Service Goal of these aeroplanes. Related Service Information Under 1
(TSA) or Chromic Acid Anodising (CAA) Finally, Airbus developed modification CFR Part 51
surface treatment is present in some frame (mod) 206409 and published associated SB
holes, from aeroplane MSN [manufacturer A330–53–3275 and SB A340–53–4238, as Airbus SAS has issued the following
serial number] 0400 and later MSN, applicable, as optional terminating action. service information.
following production process modification. For the reasons described above, this
On bulk cargo door frames (FR) 67 and FR [EASA] AD retains the requirements of EASA • Service Bulletin A330–53–3275,
69 right hand (RH) side, the door fitting AD 2016–0102, which is superseded, dated September 8, 2017.
attachment holes have this TSA or CAA expands the Applicability and requires • Service Bulletin A330–53–3278,
treatment, which leads to a detrimental effect redefined repetitive inspections of the holes dated August 22, 2017.
on fatigue behaviour. at the upper and lower door support fittings
This condition, if not detected and of FR 67 and FR 69 RH and the holes at door • Service Bulletin A340–53–4238,
corrected, could lead to cracks in the primary latch fitting of FR 69 RH. This [EASA] AD dated September 8, 2017.
structure, possibly resulting in in-flight loss also introduces an optional modification, • Service Bulletin A340–53–4239,
of a bulk cargo door, consequent which constitutes terminating action for the
decompression and potential damage to, and
dated September 5, 2017.
repetitive inspections as required by this
reduced control of, the aeroplane. [EASA] AD. Airbus Service Bulletins A330–53–
To initially address this potential unsafe 3278 and A340–53–4239 describe
condition, Airbus issued Alert Operators The optional modification involves procedures for rototest, HFEC/ultrasonic
Transmission (AOT) A53L012–16 to provide related investigative actions of eddy and detailed inspections for residual
instructions to inspect the fuselage bulk current rotating probe testing for cracks surface treatment and cracking of the
cargo door frames at specific locations. of the support fittings and the frame
Consequently, EASA issued AD 2016–0102 upper and lower right-hand fuselage
holes at frame (FR) 67 and FR 69. You bulk cargo door support fitting
[which corresponds to FAA AD 2017–16–07],
may examine the MCAI in the AD attachment holes at FR 67 and FR 69
requiring repetitive non-destructive test
(rototest and high-frequency eddy-current docket on the internet at http:// and the right-hand fuselage bulk cargo
(HFEC)) inspection or visual detailed (DET) www.regulations.gov by searching for door latch fitting attachment holes at FR
inspections [to detect cracking] of the and locating Docket No. FAA–2018– 69. Airbus Service Bulletins A330–53–
affected areas, and, depending on findings, 0583. 3275 and A340–53–4238 describe
accomplishment of a repair.
Comments procedures for a modification, which
Since that [EASA] AD was issued, it was
determined that only aeroplanes from MSN includes eddy current rotating probe
We gave the public the opportunity to
0400 to MSN 1779 are affected by CAA or testing for cracks of the support fittings
participate in developing this final rule.
TSA surface treatment issue in the door and the frame holes at FR 67 and FR 69,
We received no comments on the NPRM
fitting attachment holes. However, it was also and removal of TSA or CAA in the final
determined that aeroplanes MSN 0001 to
or on the determination of the cost to
holes of the bulk door frames FR 67 and
MSN 0399 are affected in the same the public.
FR 69. These documents are distinct
attachment holes due to a fatigue issue, Conclusion since they apply to different airplane
therefore, the same inspections must also be
We reviewed the relevant data and models. This service information is
accomplished on these aeroplanes. In
addition, based on inspection results and determined that air safety and the reasonably available because the
calculation, Airbus redefined inspection public interest require adopting this interested parties have access to it
thresholds and intervals, depending on final rule as proposed, except for minor through their normal course of business
aeroplane type, model and utilisation. Airbus editorial changes. We have determined or by the means identified in the
published SB A330–53–3278 and SB A340– that these minor changes: ADDRESSES section.
53–4239 providing the inspection
• Are consistent with the intent that Costs of Compliance
instructions at the specific locations with
extended inspection thresholds and intervals. was proposed in the NPRM for
Airbus also determined that the actions addressing the unsafe condition; and We estimate that this AD affects 102
should not be required for A340–500 and • Do not add any additional burden airplanes of U.S. registry. We estimate
–600 models, as for these aeroplanes, the upon the public than was already the following costs to comply with this
unsafe condition would only develop beyond proposed in the NPRM. AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections and modification .............. Up to 40 work-hours × $85 per hour $5,100 Up to $8,500 ........ Up to $867,000.
= $3,400.
We have received no definitive data detail the scope of the Agency’s because it addresses an unsafe condition
that enables us to provide cost estimates authority. that is likely to exist or develop on
for the on-condition actions specified in We are issuing this rulemaking under products identified in this rulemaking
this AD. the authority described in Subtitle VII, action.
Authority for This Rulemaking Part A, Subpart III, Section 44701: This AD is issued in accordance with
‘‘General requirements.’’ Under that authority delegated by the Executive
Title 49 of the United States Code section, Congress charges the FAA with Director, Aircraft Certification Service,
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specifies the FAA’s authority to issue promoting safe flight of civil aircraft in as authorized by FAA Order 8000.51C.
rules on aviation safety. Subtitle I, air commerce by prescribing regulations In accordance with that order, issuance
section 106, describes the authority of for practices, methods, and procedures of ADs is normally a function of the
the FAA Administrator. Subtitle VII: the Administrator finds necessary for Compliance and Airworthiness
Aviation Programs, describes in more safety in air commerce. This regulation Division, but during this transition
is within the scope of that authority period, the Executive Director has
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![52128 Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations
delegated the authority to issue ADs Authority: 49 U.S.C. 106(g), 40113, 44701. mandated programs intended to support the
applicable to transport category airplane reaching its limit of validity (LOV)
§ 39.13 [Amended] of the engineering data that support the
airplanes and associated appliances to
the Director of the System Oversight ■ 2. The FAA amends § 39.13 by established structural maintenance program.
Division. removing Airworthiness Directive (AD) We are issuing this AD to detect and correct
2017–16–07, Amendment 39–18984 (82 fatigue cracks in the bulk cargo door frames,
Regulatory Findings FR 41874, September 5, 2017), and caused by TSA/CAA surface treatment in
We determined that this AD will not adding the following new AD: certain bulk cargo door frame holes. Cracks
in the bulk cargo door frames can cause the
have federalism implications under 2018–20–19 Airbus SAS: Amendment 39– in-flight loss of a bulk cargo door, damage to
Executive Order 13132. This AD will 19453; Docket No. FAA–2018–0583; the airplane, and subsequent reduced control
not have a substantial direct effect on Product Identifier 2018–NM–019–AD. of the airplane.
the States, on the relationship between (a) Effective Date
the national government and the States, (f) Compliance
This AD is effective November 20, 2018.
or on the distribution of power and Comply with this AD within the
responsibilities among the various (b) Affected ADs compliance times specified, unless already
levels of government. This AD replaces AD 2017–16–07, done.
For the reasons discussed above, I Amendment 39–18984 (82 FR 41874, (g) Repetitive Inspections
certify that this AD: September 5, 2017) (‘‘AD 2017–16–07’’).
1. Is not a ‘‘significant regulatory Before exceeding the thresholds specified
(c) Applicability in table 1 to paragraph (g) of this AD, or
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the This AD applies to the following Airbus within the applicable time specified in
SAS airplanes, certificated in any category, paragraph (g)(1) or (g)(2) of this AD,
DOT Regulatory Policies and Procedures manufacturer serial numbers (MSNs) 0001 to whichever is later: Do a rototest, high
(44 FR 11034, February 26, 1979); 1779 inclusive; except airplanes on which frequency eddy current (HFEC), ultrasonic, or
3. Will not affect intrastate aviation in Airbus Service Bulletin A330–53–3275 or detailed inspection, as applicable, for
Alaska; and Airbus Service Bulletin A340–53–4238 has residual surface treatment and cracking of the
4. Will not have a significant been embodied.
upper and lower right-hand fuselage bulk
economic impact, positive or negative, (1) Model A330–201, –202, –203, –223, and
–243 airplanes. cargo door support fitting attachment holes at
on a substantial number of small entities FR 67 and FR 69 and the right-hand fuselage
under the criteria of the Regulatory (2) Model A330–223F and –243F airplanes.
(3) Model A330–301, –302, –303, –321, bulk cargo door latch fitting attachment holes
Flexibility Act. –322, –323, –341, –342, and –343 airplanes. at FR 69, in accordance with the
List of Subjects in 14 CFR Part 39 (4) Model A340–211, –212, and –213 Accomplishment Instructions of Airbus
airplanes. Service Bulletin A330–53–3278, dated
Air transportation, Aircraft, Aviation (5) Model A340–311, –312, and –313 August 22, 2017; or Airbus Service Bulletin
safety, Incorporation by reference, airplanes. A340–53–4239, dated September 5, 2017; as
Safety. applicable. Thereafter, depending on the
(d) Subject
areas and inspection methods as defined in
Adoption of the Amendment Air Transport Association (ATA) of table 2 to paragraph (g) of this AD, repeat the
Accordingly, under the authority America Code 53, Fuselage. inspection at intervals not exceeding those
delegated to me by the Administrator, (e) Reason specified in table 3 to paragraph (g) of this
the FAA amends 14 CFR part 39 as This AD is prompted by a determination AD.
follows: that only airplanes having certain MSNs are (1) For airplanes having MSN 0001 through
affected by tartaric sulfuric anodizing (TSA)/ 0399 inclusive: Within 200 flight cycles after
PART 39—AIRWORTHINESS chromic acid anodizing (CAA) surface the effective date of this AD.
DIRECTIVES treatment in the door fitting attachment (2) For airplanes having MSN 0400 through
holes, and that airplanes having certain 1779 inclusive: Within 800 flight cycles after
■ 1. The authority citation for part 39 MSNs were excluded from AD 2017–16–07. the effective date of this AD.
continues to read as follows: This AD is intended to complete certain BILLING CODE 4910–13–P
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![Federal Register / Vol. 83, No. 200 / Tuesday, October 16, 2018 / Rules and Regulations 52131
telephone +33 5 61 93 36 96; fax +33 5 61 this AD as of May 1, 2015 (80 FR 24789, NPRM also proposed to remove certain
93 45 80; email airworthiness.A330-A340@ May 1, 2015). airplanes from the applicability. We are
airbus.com; internet http://www.airbus.com. issuing this AD to address loss of all AC
ADDRESSES: For service information
(4) You may view this service information electrical power, which could result in
at the FAA, Transport Standards Branch, identified in this final rule, contact
2200 South 216th St., Des Moines, WA. For Boeing Commercial Airplanes, loss of control of the airplane.
information on the availability of this Attention: Contractual & Data Services Comments
material at the FAA, call 206–231–3195. (C&DS), 2600 Westminster Blvd., MC
(5) You may view this service information 110–SK57, Seal Beach, CA 90740–5600; We gave the public the opportunity to
that is incorporated by reference at the telephone 562–797–1717; internet participate in developing this AD. The
National Archives and Records https://www.myboeingfleet.com. You following presents the comments
Administration (NARA). For information on may view this service information at the received on the NPRM and the FAA’s
the availability of this material at NARA, call response to each comment.
202–741–6030, or go to: http://
FAA, Transport Standards Branch, 2200
www.archives.gov/federal-register/cfr/ibr- South 216th St., Des Moines, WA. For Support for the NPRM
locations.html. information on the availability of this
The Air Line Pilots Association,
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on International (ALPA) and American
It is also available on the internet at
September 26, 2018. Airlines indicated their support for the
http://www.regulations.gov by searching
John P. Piccola, NPRM.
for and locating Docket No. FAA–2017–
Acting Director, System Oversight Division, 0771. Request To Update Number of Affected
Aircraft Certification Service.
Airplanes
[FR Doc. 2018–22147 Filed 10–15–18; 8:45 am] Examining the AD Docket
Boeing requested that we update the
BILLING CODE 4910–13–P You may examine the AD docket on
Costs of Compliance section of the
the internet at http://
proposed AD to state that ‘‘55 airplanes
www.regulations.govby searching for
DEPARTMENT OF TRANSPORTATION of U.S. registry’’ are affected. Boeing
and locating Docket No. FAA–2017–
noted that its records show 55 N-
0771; or in person at Docket Operations
Federal Aviation Administration registered airplanes, not 47 as stated in
between 9 a.m. and 5 p.m., Monday
the proposed AD.
through Friday, except Federal holidays. We agree with the commenter’s
14 CFR Part 39
The AD docket contains this final rule, request for the reason provided. We
[Docket No. FAA–2017–0771; Product the regulatory evaluation, any have updated the Costs of Compliance
Identifier 2016–NM–212–AD; Amendment comments received, and other section of this AD accordingly.
39–19449; AD 2018–20–15] information. The address for Docket
Operations (phone: 800–647–5527) is Request To Revise Warranty
RIN 2120–AA64 U.S. Department of Transportation, Information in Costs of Compliance
Docket Operations, M–30, West Section
Airworthiness Directives; The Boeing
Building Ground Floor, Room W12–140, Boeing requested that we revise the
Company Airplanes
1200 New Jersey Avenue SE, Costs of Compliance section of the
AGENCY: Federal Aviation Washington, DC 20590. proposed AD to state that warranty
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: Joe remedies are not available for Boeing
ACTION: Final rule. Salameh, Aerospace Engineer, Systems Service Bulletin B787–81205–
and Equipment Section, FAA, Seattle SB240063–00, Issue 002, dated June 7,
SUMMARY: We are superseding ACO Branch, 2200 South 216th St., Des 2016. Boeing noted that Boeing Service
Airworthiness Directive (AD) 2015–09– Moines, WA 98198; phone and fax: 206– Bulletin B787–81205–SB240063–00,
07, which applied to all The Boeing 231–3536; email: joe.salameh@faa.gov. Issue 002, dated June 7, 2016, states
Company Model 787 airplanes. AD SUPPLEMENTARY INFORMATION: ‘‘Boeing warranty remedies are not
2015–09–07 required a repetitive available for the configuration changes
maintenance task for electrical power Discussion set forth in this service bulletin.
deactivation. This AD requires installing We issued a notice of proposed Notwithstanding, Boeing will provide
new software for the generator control rulemaking (NPRM) to amend 14 CFR the supplier software referenced in this
unit (GCU). This AD also removes part 39 to supersede AD 2015–09–07, service bulletin at no charge. This offer
certain airplanes from the applicability. Amendment 39–18153 (80 FR 24789, will expire eight years from the original
This AD was prompted by the May 1, 2015) (‘‘AD 2015–09–07’’). AD issue date of this service bulletin.’’
determination that a Model 787 airplane 2015–09–07 applied to all The Boeing We acknowledge the commenter’s
that has been powered continuously for Company Model 787 airplanes. The request and agree to clarify. The
248 days can lose all alternating current NPRM published in the Federal warranty information in the Costs of
(AC) electrical power due to the GCUs Register on August 15, 2017 (82 FR Compliance section of this AD is meant
simultaneously going into failsafe mode. 38629). The NPRM was prompted by the to be informational, and is included
We are issuing this AD to address the determination that a Model 787 airplane when the manufacturer’s service
unsafe condition on these products. that has been powered continuously for information states warranty coverage
DATES: This AD is effective November 248 days can lose all AC electrical may be available. We do not control
20, 2018. power due to the GCUs simultaneously warranty coverage and operators must
The Director of the Federal Register going into failsafe mode. This condition work with the manufacturer to
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approved the incorporation by reference is caused by a software counter internal determine if they are eligible for a
of certain publications listed in this AD to the GCUs that will overflow after 248 warranty. We have revised the warranty
as of November 20, 2018. days of continuous power. The NPRM information in the Costs of Compliance
The Director of the Federal Register proposed to require installing the new section of this AD to note that some of
approved the incorporation by reference GCU software developed to address the the software costs may be covered under
of certain other publications listed in software counter overflow anomaly. The warranty.
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Document Created: 2018-10-15 23:42:15
Document Modified: 2018-10-15 23:42:15
| 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 November 20, 2018. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3229. | |
| FR Citation | 83 FR 52126 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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