Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 83, Number 200 (Tuesday, October 16, 2018)]
[Rules and Regulations]
[Pages 52126-52131]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22147]


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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; 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.

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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 [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. 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> 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.
    <bullet> Service Bulletin A330-53-3275, dated September 8, 2017.
    <bullet> Service Bulletin A330-53-3278, dated August 22, 2017.
    <bullet> Service Bulletin A340-53-4238, dated September 8, 2017.
    <bullet> 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.
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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 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: [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 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 
[email protected]; 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]
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