[Federal Register Volume 83, Number 130 (Friday, July 6, 2018)]
[Proposed Rules]
[Pages 31499-31504]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-14407]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0583; Product Identifier 2018-NM-019-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-16-
07, which applies to certain Airbus Model A330-200, A330-200 Freighter, 
A330-300, A340-500, and A340-600 series airplanes; and Model A340-313 
airplanes. AD 2017-16-07 requires inspection of the fuselage bulk cargo 
door frames at specific locations, and corrective action if necessary. 
Since we issued AD 2017-16-07, it was determined 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 proposed 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. This proposed 
AD would require new inspections of certain attachment holes for 
residual surface treatment and cracking, and corrective action if 
necessary; and would provide an optional terminating action for the 
inspections. The proposed AD would also revise the applicability to add 
certain airplanes and remove others. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 20, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAL, 2 Rond-Point Emile Dewoitine, 31700 
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, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

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 the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

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.

[[Page 31500]]


SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0583; 
Product Identifier 2018-NM-019-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a limit of 
validity (LOV) of the engineering data that support the structural 
maintenance program under 14 CFR 26.21. This proposed AD is the result 
of an assessment of the previously established programs by the design 
approval holder (DAH) during the process of establishing the LOV for 
the affected airplanes. The actions specified in this proposed AD are 
necessary to complete certain programs to ensure the continued 
airworthiness of aging airplane structure and to support an airplane 
reaching its LOV.
    We issued AD 2017-16-07, Amendment 39-18984 (82 FR 41874, September 
5, 2017) (``AD 2017-16-07''), for all Airbus Model A330-200, A330-200 
Freighter, A330-300, A340-500, and A340-600 series airplanes; and Model 
A340-313 airplanes. AD 2017-16-07 requires inspection of the fuselage 
bulk cargo door frames at specific locations, and corrective action if 
necessary. AD 2017-16-07 resulted from the discovery of TSA/CAA surface 
treatment in certain bulk cargo door frame holes of airplanes with MSNs 
0400 and higher. We issued AD 2017-16-07 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.

Actions Since AD 2017-16-07 Was Issued

    Since we issued AD 2017-16-07, it was determined that only 
airplanes having manufacturer serial numbers (MSNs) 0400 through 1779 
are affected by TSA/CAA surface treatment in the door fitting 
attachment holes due to fatigue. However, it was also determined that 
airplanes having 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 airplanes. In addition, 
based on inspection results and calculations, Airbus also redefined the 
inspection thresholds and intervals. Airbus determined that these 
actions should not be required for Model A340-500 and -600 airplanes 
because the unsafe condition would only develop beyond the design 
service goal of these airplanes. Additionally, Airbus developed an 
optional terminating modification.
    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 Model A330-200, A330-200 
Freighter, and A330-300 series airplanes, and 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 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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A330-53-3275, dated August 22, 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

[[Page 31501]]

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.

FAA's Determination and Requirements of This Proposed AD

    Although this proposed AD does not explicitly restate the actions 
that are part of the requirements of AD 2017-16-07, this proposed AD 
would retain those required actions. Those actions are referenced in 
the service information identified above.
    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 102 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                  Labor cost       Parts cost     Cost per product    Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections and modification...  Up to 40 work-             $5,100  Up to $8,500.....  Up to $867,000.
                                  hours x $85 per
                                  hour = $3,400.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus: Docket No. FAA-2018-0583; Product Identifier 2018-NM-019-AD.

(a) Comments Due Date

    We must receive comments by August 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 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) 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 A340-211, -212, and -213 airplanes.
    (5) Airbus 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

[[Page 31502]]

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 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.
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(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'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'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 Airbus Service 
Bulletin A330-53-3275, dated August 22, 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's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.

[[Page 31504]]

(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 All Operators Telex (AOT) 
A53L012-16, dated May 30, 2016, or Revision 1, 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: [email protected]. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or 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) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 2 Rond-Point Emile Dewoitine, 
31700 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 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.

    Issued in Des Moines, Washington, on June 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-14407 Filed 7-5-18; 8:45 am]
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