Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 84, Number 167 (Wednesday, August 28, 2019)]
[Rules and Regulations]
[Pages 45061-45065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-18516]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0257; Product Identifier 2018-NM-175-AD; Amendment 
39-19714; AD 2019-16-11]
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: The FAA is superseding Airworthiness Directive (AD) 2018-20-
06, which applied to certain Airbus SAS Model A300 F4-600R series 
airplanes. AD 2018-20-06 required repetitive high frequency eddy 
current (HFEC) inspections of the aft lower deck cargo door (LDCD) 
frame forks; a one-time check of the LDCD clearances; a one-time 
detailed visual inspection of hooks, eccentric bushes, and x-stops; and 
corrective actions if necessary. This AD retains the actions of AD 
2018-20-06 and requires new compliance times, depending on frame fork 
configuration. This AD was prompted by a report of two adjacent frame 
forks that were found cracked on the aft LDCD of two airplanes during 
scheduled maintenance, and a determination that certain compliance 
times need to be revised. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective October 2, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 26, 
2017 (81 FR 93801, December 22, 2016), and November 5, 2018 (83 FR 
49265, October 1, 2018).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email [email protected]; 
internet http://www.airbus.com. You may view this referenced service 
information at the FAA, Transport 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-2019-0257.

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-2019-
0257; 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 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-20-06, Amendment 39-19440 (83 FR 
49265, October 1, 2018) (``AD 2018-20-06''). AD 2018-20-06 applied to 
certain Airbus SAS Model A300 F4-600R series airplanes. The NPRM 
published in the Federal Register on May 7, 2019 (84 FR 19881). The 
NPRM was prompted by a report of two adjacent frame forks that were 
found cracked on the aft LDCD of two airplanes during scheduled 
maintenance, and a determination that certain compliance times need to 
be revised. The NPRM proposed to continue to require the actions of AD 
2018-20-06 and also to require new compliance times, depending on frame 
fork configuration. The FAA is issuing this AD to address cracked or 
ruptured aft LDCD frames, which could allow loads to be transferred to 
the remaining structural elements. This condition could lead to the 
rupture of one or more vertical aft LDCD frames, which could result in 
reduced structural integrity of the aft LDCD.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0266, dated December 11, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus SAS Model A300 F4-600R 
series airplanes. The MCAI states:

    During scheduled maintenance at frames (FR) 61 and FR61A on the 
aft lower deck cargo door (LDCD) of two [Airbus SAS] A300-600F4 
aeroplanes, two adjacent frame forks were found cracked. Subsequent 
analysis determined that, in case of cracked or ruptured aft cargo 
door frame(s), loads will be transferred to the remaining structural 
elements. However, these secondary load paths will be able to 
sustain the loads for a limited number of flight cycles (FC) only.
    This condition, if not detected and corrected, could lead to the 
rupture of one or more vertical aft cargo door frame(s), resulting 
in reduced structural integrity of the aft cargo door.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A52W011-15 to provide inspection instructions, 
and, consequently, EASA issued AD 2015-0152 to require repetitive 
inspections of the aft LDCD frame forks and, depending on findings, 
the accomplishment of applicable corrective action(s). Subsequently, 
Airbus published the modification SB [service bulletin] to provide 
frame fork reinforcement instructions, and the inspection SB to 
provide instructions to inspect the cargo door for cracks, as well 
as for frame fork replacement, including provisions for extended 
inspection intervals. EASA revised the AD accordingly.
    Since EASA AD 2015-0152R1 [which corresponds to FAA AD 2018-20-
06] was issued, further investigations results allowed Airbus to 
define new thresholds and inspection intervals according to the 
frame fork configuration. Consequently, the inspection SB was 
revised to include these new thresholds and intervals.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0152R1, which is superseded, and 
introduces new thresholds and intervals, depending on frame fork 
configuration.

    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-2019-
0257.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the NPRM and the FAA's response to each comment.

[[Page 45062]]

Support for the NPRM

    FedEx stated agreement that this AD is required to maintain the 
continued airworthiness and safety of its fleet.

Request To Clarify Reason for Referencing Alert Operators Transmission

    Airbus requested clarification as to why the proposed AD referenced 
Airbus Alert Operators Transmission A52W011-15, even though the MCAI no 
longer references Airbus Alert Operators Transmission A52W011-15, 
Revision 00, dated July 23, 2015 (``Airbus All Operators Transmission 
A52W011-15''), as it had in previous versions of the EASA ADs. Airbus 
pointed out that the MCAI no longer references Airbus Alert Operators 
Transmission A52W011-15, and now only references Airbus Service 
Bulletin A300-52-6086, Revision 01, dated May 2, 2018 (``Airbus Service 
Bulletin A300-52-6086''). Further, Airbus noted that the proposed AD 
retained the reference to Airbus Alert Operators Transmission A52W011-
15.
    The FAA acknowledges that the MCAI does not reference Airbus Alert 
Operators Transmission A52W011-15, and that the proposed AD retained 
this reference. We determined that, for the purposes of this AD, the 
inclusion of Airbus Alert Operators Transmission A52W011-15 is 
necessary to meet the requirements of this AD. The FAA carries over 
previous requirements for several reasons, including: To provide credit 
to operators who have already complied with the service information, to 
reduce the need for alternative method of compliance (AMOC) requests, 
and to prevent situations where operators could potentially be put out 
of compliance. For these reasons, the FAA has determined that this AD 
should include reference to Airbus Alert Operators Transmission 
A52W011-15. No changes have been made to this AD in this regard.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule as proposed, except for minor 
editorial changes. The FAA has 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

    This AD requires Airbus Service Bulletin A300-52-6085, Revision 01, 
dated May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 
01, dated May 29, 2018; which the Director of the Federal Register 
approved for incorporation by reference as of November 5, 2018 (83 FR 
49265, October 1, 2018).
    This AD also requires Airbus Alert Operators Transmission A52W011-
15, Revision 00, including Appendices 1, 2, 3, and 4, dated July 23, 
2015, which the Director of the Federal Register approved for 
incorporation by reference as of January 26, 2017 (81 FR 93801, 
December 22, 2016).
    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

    The FAA estimates that this AD affects 58 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-20-06...  17 work-hours x $85 per               $0          $1,445         $83,810
                                         hour = $1,445.
----------------------------------------------------------------------------------------------------------------

    The new requirements of this AD add no additional economic burden.
    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need these on-condition actions:

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
               Labor cost                             Parts cost                       Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 65 work-hours x $85 per hour = Up  Up to $10,000......................  Up to $15,525.
 to $5,525.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    The FAA 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

[[Page 45063]]

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) Will not affect intrastate aviation in Alaska, and
    (3) 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) 
2018-20-06, Amendment 39-19440 (83 FR 49265, October 1, 2018), and 
adding the following new AD:

2019-16-11 Airbus SAS: Amendment 39-19714; Docket No. FAA-2019-0257; 
Product Identifier 2018-NM-175-AD.

(a) Effective Date

    This AD is effective October 2, 2019.

(b) Affected ADs

    This AD replaces 2018-20-06, Amendment 39-19440 (83 FR 49265, 
October 1, 2018) (``AD 2018-20-06'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 F4-605R and F4-622R 
airplanes, certificated in any category, on which Airbus 
modification 12046 has been embodied in production. Modification 
12046 has been embodied in production on manufacturer serial numbers 
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report of two adjacent frame forks 
that were found cracked on the aft lower deck cargo door (LDCD) of 
two airplanes during scheduled maintenance, and a determination that 
certain compliance times need to be revised. The FAA is issuing this 
AD to address cracked or ruptured aft LDCD frames, which could allow 
loads to be transferred to the remaining structural elements. This 
condition could lead to the rupture of one or more vertical aft LDCD 
frames, which could result in reduced structural integrity of the 
aft LDCD.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) New Affected Part Definition

    For the purposes of this AD, an affected part is a frame fork 
having a part number identified in figure 1 to paragraph (g) of this 
AD.
[GRAPHIC] [TIFF OMITTED] TR28AU19.000

(h) Retained Inspection Requirements and On-Condition Actions, With 
Revised Compliance Language

    This paragraph restates the requirements of paragraph (g) of AD 
2018-20-06, with revised compliance language. At the applicable time 
specified in paragraph (i) of this AD, or before exceeding the 
threshold defined in figure 2 to paragraph (h) of this AD, whichever 
occurs later: Do the actions specified in paragraphs (h)(1) through 
(3) of this AD. Repeat the high frequency eddy current (HFEC) 
inspection specified in paragraph (h)(3) of this AD at all LDCD 
frame fork stations having affected parts thereafter at intervals 
not to exceed the applicable times specified in figure 2 to 
paragraph (h) of this AD.
    (1) A one-time check of the aft LDCD clearances ``U'' and ``V'' 
between the latching hooks and the eccentric bush at frame (FR) 60 
through FR64A, in accordance with the instructions of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; 
or the Accomplishment Instructions of Airbus Service Bulletin A300-
52-6086, Revision 01, dated May 29, 2018. If any value outside 
tolerance is found, adjust the latching hook before further flight, 
in accordance with the instructions of Airbus Alert Operators 
Transmission A52W011-15, Revision 00, dated July 23, 2015; or the 
Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, 
Revision 01, dated May 29, 2018.
    (2) A one-time detailed inspection to detect signs of wear of 
the hooks, eccentric bushes, and x-stops, in accordance with the 
instructions of Airbus Alert Operators Transmission A52W011-15, 
Revision 00, dated July 23, 2015. If any wear is found, do all 
applicable corrective actions before further flight, in accordance 
with the instructions of Airbus Alert Operators Transmission 
A52W011-15, Revision 00, dated July 23, 2015.
    (3) An HFEC inspection to detect cracking at all frame fork 
stations of the aft LDCD, in accordance with the instructions of 
Airbus Alert Operators Transmission A52W011-15, Revision 00, dated 
July 23, 2015; or the Accomplishment Instructions of Airbus Service 
Bulletin A300-52-6086, Revision 01, dated May 29, 2018. If any crack 
is found, before further flight, replace the cracked frame fork, in 
accordance with the instructions of Airbus Alert Operators 
Transmission A52W011-15, Revision 00, dated July 23, 2015; repair 
the cracked frame fork, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, 
dated May 29, 2018; or modify (reinforce) the cracked frame fork, 
including doing all applicable related investigative and corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 
2018; except as required by paragraph (j) of this AD.

[[Page 45064]]

[GRAPHIC] [TIFF OMITTED] TR28AU19.001

(i) Retained Compliance Times, With No Changes

    At the later of the times specified in paragraphs (i)(1) and (2) 
of this AD, do the actions required by paragraph (h) of this AD.
    (1) Before the accumulation of 4,500 total flight cycles.
    (2) At the applicable time specified by paragraph (i)(2)(i) or 
(ii) of this AD.
    (i) For airplanes that have accumulated 8,000 or more total 
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016) (``AD 
2016-25-03'')): Within 100 flight cycles after January 26, 2017.
    (ii) For airplanes that have accumulated fewer than 8,000 total 
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 400 flight cycles after January 26, 2017.

(j) Service Information Exception

    Where Airbus Service Bulletin A300-52-6085, Revision 01, dated 
May 2, 2018, specifies to contact Airbus for appropriate action: 
Before further flight, accomplish corrective actions in accordance 
with the procedures specified in paragraph (n)(2) of this AD.

(k) No Terminating Action

    Accomplishment of corrective actions on an airplane as required 
by paragraph (h)(1) or (2) of this AD; or repair, modification, or 
replacement of a frame fork as required by paragraph (h)(3) of this 
AD, on the aft LDCD of an airplane; does not constitute terminating 
action for the repetitive HFEC

[[Page 45065]]

inspections required by paragraph (h)(3) of this AD for that 
airplane.

(l) No Reporting

    Although the Accomplishment Instructions of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; 
and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 
2018; specify to submit certain information to the manufacturer, 
this AD does not include that requirement.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (h)(1) and (3) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
    (2) This paragraph provides credit for actions required by 
paragraph (h)(3) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A300-52-
6085, Revision 00, dated December 22, 2016.

(n) 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 International Section, send it to the attention of 
the person identified in paragraph (o)(2) of this AD. Information 
may be emailed to [email protected].
    (i) 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.
    (ii) AMOCs approved previously for AD 2018-20-06 are approved as 
AMOCs for the corresponding provisions of this AD.
    (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 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0266, dated December 11, 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-2019-0257.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (6) of this AD.

(p) 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.
    (3) The following service information was approved for IBR on 
November 5, 2018 (83 FR 49265, October 1, 2018).
    (i) Airbus Service Bulletin A300-52-6085, Revision 01, dated May 
2, 2018.
    (ii) Airbus Service Bulletin A300-52-6086, Revision 01, dated 
May 29, 2018.
    (4) The following service information was approved for IBR on 
January 26, 2017 (81 FR 93801, December 22, 2016).
    (i) Airbus Alert Operators Transmission A52W011-15, Revision 00, 
dated July 23, 2015, including the following appendices:
    (A) Appendix 1--Flowchart, undated.
    (B) Appendix 2--Reporting Sheet, undated. (None of the pages of 
Appendix 2 are numbered.)
    (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/
L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is 
identified with an appendix number only on page 1 of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 
2015.)
    (D) Appendix 4--P/N identification for frame forks and bushings, 
undated.
    (ii) [Reserved]
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; internet 
http://www.airbus.com.
    (6) 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.
    (7) 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 August 15, 2019.
Suzanne Masterson,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-18516 Filed 8-27-19; 8:45 am]
 BILLING CODE 4910-13-P

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