[Federal Register Volume 82, Number 170 (Tuesday, September 5, 2017)]
[Rules and Regulations]
[Pages 41874-41877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16568]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9517; Product Identifier 2016-NM-100-AD; Amendment 
39-18984; AD 2017-16-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200, A330-200 Freighter, A330-300, A340-500, and 
A340-600 series airplanes; and A340-313 airplanes. This AD was prompted 
by the discovery of Tartaric Sulfuric Anodizing (TSA)/Chromic Acid 
Anodizing (CAA) surface treatment in certain bulk cargo door frame 
holes of certain airplanes. This AD requires inspection of the fuselage 
bulk cargo door frames at specific locations, and corrective action if 
necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective October 10, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 10, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email [email protected]; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9517.

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-
9517; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 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 all Airbus Model A330-200, 
A330-200 Freighter, A330-300, A340-500, and A340-600 series airplanes; 
and A340-313 airplanes. The NPRM published in the Federal Register on 
December 28, 2016 (81 FR 95538) (``the NPRM''). The NPRM was prompted 
by the discovery of TSA/CAA surface treatment in certain bulk cargo 
door frame holes of certain airplanes. The NPRM proposed to require 
inspection of the fuselage bulk cargo door frames at specific 
locations, and corrective action if necessary. 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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0102, dated June 1, 2016; corrected June 
7, 2016 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''); to correct an unsafe 
condition for all Airbus Model A330-200, A330-200 Freighter, A330-300, 
A340-500, and A340-600 series airplanes; and A340-313 airplanes. The 
MCAI states:

    In the frame of the certification of the A330 Extended Service 
Goal exercise, it has been identified that Tartaric Sulfuric 
Anodising (TSA)/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 
Side, the door fitting attachment holes have this TSA/CAA

[[Page 41875]]

treatment, which leads to a detrimental effect on fatigue behaviour. 
This condition, if not detected and corrected, could lead to 
critical cracks in the primary structure, possibly resulting in in-
flight loss of a bulk cargo door, consequent decompression and 
potential damage to the aeroplane that could reduce the control of 
the aeroplane.
    To 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.
    For the reasons described above, this [EASA] AD requires 
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.
    This [EASA] AD is considered an interim measure, and further 
[EASA] AD action may follow.

    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-
9517.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to that comment.

Request To Remove the Reporting Requirement

    Lufthansa agrees that reporting inspection results, as proposed in 
paragraph (k) of the proposed AD, is beneficial to the original 
equipment manufacturer (OEM). However, Lufthansa disagrees that 
reporting should be a hard requirement for operators. Lufthansa does 
not consider that reporting or non-reporting is an airworthiness 
concern for the affected aircraft. Lufthansa does not agree with the 
potential of having to ground an aircraft just because the reporting 
may be provided later than 30 days after inspection. According to 
Lufthansa, some layover may, in fact, take more than 30 days to 
complete; in such cases, the aircraft may not yet be released back into 
service, and the reporting as proposed could become overdue. Lufthansa 
considers that because of these circumstances, reporting should be a 
strong recommendation, but not a requirement.
    We find that reporting of inspection results for the affected 
aircraft is necessary. Reporting allows the manufacturer to collect 
airworthiness information from operators in order to fully understand 
the scope of the unsafe condition and to develop a final solution as a 
terminating action. Reporting is not intended to ground aircraft and is 
only required after the inspections required by paragraphs (g) and (h) 
of this AD have been completed. We have made no change to this AD in 
this regard.

Conclusion

    We reviewed the relevant data, considered the comment received, 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 Alert Operators Transmission (AOT) A53L012-16, 
Revision 00, dated May 30, 2016, including the following appendices.
     Appendix 1. Technical Disposition TD_K48_S3_01755_2016, 
Issue B, dated May 12, 2016.
     Appendix 2. Technical Disposition TD_K48_S3_01754_2016, 
Issue B, dated May 12, 2016.
     Appendix 3. Technical Disposition TD_K48_S3_01772_2016, 
Issue A, dated May 12, 2016.
     Appendix 4. Technical Disposition TD_K48_S3_01773_2016, 
Issue A, dated May 12, 2016.
     Appendix 5. Appendix 4: AOT reporting sheet, undated. 
(Appendix 5 is incorrectly identified as ``Appendix 4'' on all pages.
     Appendix 6. Advance Copy of Chapter 53-40-18, 
ALL_A330_NTM_534018, dated May 18, 2016, of the Airbus A330 Non-
Destructive Testing (NDT) Manual. (``Advance copy'' indicates that the 
identified material will be incorporated into the NDT manual during the 
next manual revision. The ``advanced copy'' is intended to provide 
operators with access to the identified material quickly instead of 
making them wait several months until the next manual revision is 
released.)
    The service information describes procedures for inspections of the 
fuselage bulk cargo frames at the door support and latch fittings 
location; repair instructions; and reporting instructions. 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 96 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  2 work-hours x $85               $0  $170 per inspection  $16,320 per
                                    per hour = $170                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Reporting........................  1 work-hour x $85                $0  $85................  $8,160.
                                    per hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be
required based on the results of the required inspection. We have no 
way of
determining the number of aircraft that might need this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Optional door frame replacement...............  200 work-hours x $85 per hour =          $68,000         $85,000
                                                 $17,000.
----------------------------------------------------------------------------------------------------------------


[[Page 41876]]

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-16-07 Airbus: Amendment 39-18984; FAA-2016-9517; Product 
Identifier 2016-NM-100-AD.

(a) Effective Date

    This AD is effective October 10, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Airbus airplanes, certificated 
in any category, manufacturer serial numbers (MSNs) 0400 and higher.
    (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Airbus Model A330-223F and -243F airplanes.
    (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
    (4) Airbus Model A340-313 airplanes.
    (5) Airbus Model A340-541 airplanes.
    (6) Airbus Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by the discovery of Tartaric Sulfuric 
Anodizing (TSA)/Chromic Acid Anodizing (CAA) surface treatment in 
certain bulk cargo door frame holes of airplanes with MSNs 0400 and 
higher. 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) Initial Inspection

    At the applicable compliance time specified in table 1 to 
paragraph (g) of this AD, do the actions specified in paragraph 
(g)(1) or (g)(2) of this AD, in accordance with the instructions of 
Airbus Alert Operators Transmission (AOT) A53L012-16, Revision 00, 
dated May 30, 2016.
    (1) Accomplish a rototest inspection to detect cracking of the 
holes for the bulk cargo door support fittings at fuselage frame 
(FR) 67 and FR 69, and a high-frequency eddy-current (HFEC) 
inspection of the holes for the door latch fitting at FR 69.
    (2) Accomplish a detailed visual inspection to detect cracking 
in the bulk cargo door support fittings at FR 67 and FR 69 and the 
holes for the door latch fitting at FR 69.

         Table 1 to Paragraph (g) of This AD--Initial Inspection
------------------------------------------------------------------------
     Total flight cycles
  accumulated since airplane
     first flight, on the                   Compliance time
  effective date of this AD
------------------------------------------------------------------------
12,500 total flight cycles or  Within 200 flight cycles or 2 months,
 more.                          whichever occurs first, after the
                                effective date of this AD.
Fewer than 12,500 total        Within 200 flight cycles or 2 months,
 flight cycles.                 whichever occurs first, after exceeding
                                12,500 flight cycles.
------------------------------------------------------------------------


[[Page 41877]]

(h) Repetitive Inspections

    At intervals not to exceed the values specified in table 2 to 
paragraph (h) of this AD, as applicable, depending on the previously 
selected inspection method, repeat the inspection(s) specified in 
either paragraph (g)(1) or (g)(2) of this AD.

       Table 2 to Paragraph (h) of this AD--Repetitive Inspections
------------------------------------------------------------------------
           Inspection method                   Inspection interval
------------------------------------------------------------------------
Detailed visual inspection.............  150 flight cycles.
Rototest and HFEC inspections..........  2,900 flight cycles.
------------------------------------------------------------------------

(i) Repair

    If, during any inspection required by paragraph (g) or (h) of 
this AD, any crack is detected, 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's EASA Design Organization Approval (DOA).

(j) Non-Terminating Action for Repairs

    Accomplishment of a repair on an airplane, as required by 
paragraph (i) of this AD, does not constitute terminating action for 
the inspections required by 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's EASA DOA.

(k) Reporting

    After the initial inspection specified in paragraph (g) of this 
AD, and after each repetitive inspection specified in paragraph (h) 
of this AD, at the applicable times specified in paragraph (k)(1) 
and (k)(2) of this AD: Report inspection findings, both positive and 
negative, to Airbus in accordance with the instructions of Airbus 
AOT A53L012-16, Revision 00, dated May 30, 2016.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the 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: [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0102, dated June 1, 2016; corrected June 7, 
2016, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9517.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Section, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
telephone 425-227-1138; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus A330 Alert Operators Transmission (AOT) A53L012-16, 
Revision 00, dated May 30, 2016, including Appendices 1 through 6. 
Except as described in paragraph (n)(2)(i)(E), none of these 
appendices are identified as ``appendices'' to Airbus A330 AOT 
A53L012-16.
    (A) Appendix 1. Airbus Technical Disposition 
TD_K48_S3_01755_2016, Issue B, dated May 12, 2016.
    (B) Appendix 2. Airbus Technical Disposition 
TD_K48_S3_01754_2016, Issue B, dated May 12, 2016.
    (C) Appendix 3. Airbus Technical Disposition 
TD_K48_S3_01772_2016, Issue A, dated May 12, 2016.
    (D) Appendix 4. Airbus Technical Disposition 
TD_K48_S3_01773_2016, Issue A, dated May 12, 2016.
    (E) Appendix 5. Appendix 4: AOT reporting sheet, undated. 
(Appendix 5 is incorrectly identified as ``Appendix 4'' on all 
pages.)
    (F) Appendix 6. Advance Copy of Chapter 53-40-18, 
ALL_A330_NTM_534018, dated May 18, 2016, of the Airbus A330 Non-
Destructive Testing (NDT) Manual.
    (``Advance copy'' indicates that the identified material will be 
incorporated into the NDT manual during the next manual revision. 
The ``advanced copy'' is intended to provide operators with access 
to the identified material quickly instead of making them wait 
several months until the next manual revision is released.)
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 28, 2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-16568 Filed 9-1-17; 8:45 am]
 BILLING CODE 4910-13-P