Airworthiness Directives; Airbus SAS Airplanes

[Federal Register Volume 84, Number 219 (Wednesday, November 13, 2019)]
[Rules and Regulations]
[Pages 61517-61519]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24502]



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Rules and Regulations
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Federal Register / Vol. 84, No. 219 / Wednesday, November 13, 2019 / 
Rules and Regulations

[[Page 61517]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0485; Product Identifier 2019-NM-064-AD; Amendment 
39-19757; AD 2019-20-04]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A330-243, A330-243F, A330-341, A330-342, and A330-343 
airplanes. This AD was prompted by reports of thrust reverser unit 
(TRU) beams found with evidence of thermally caused material 
degradation in the rearmost section of the TRU beam at certain latches. 
This AD requires an inspection for heat damage of each left-hand and 
right-hand TRU beam as specified in a European Union Aviation Safety 
Agency (EASA) AD, which is incorporated by reference. Depending on 
findings, this AD might also require inspections of the TRU beam 
latches, the TRU beam clevises, and the thrust reverser outer fixed 
structure rear area; corrective actions; and replacement of TRU beams. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective December 18, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 18, 
2019.

ADDRESSES: For the material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 89990 1000; email [email protected]; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. You may view this IBR material 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 in the AD docket on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2019-0485.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0485; 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: 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

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2018-0148R1, dated April 5, 2019 
(``EASA AD 2018-0148R1'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A330-243, A330-243F, A330-341, A330-
342, and A330-343 airplanes.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus SAS Model 
A330-243, A330-243F, A330-341, A330-342, and A330-343 airplanes. The 
NPRM published in the Federal Register on June 26, 2019 (84 FR 30052). 
The NPRM was prompted by reports of TRU beams found with evidence of 
thermally caused material degradation in the rearmost section of the 
TRU beam at certain latches. The NPRM proposed to require an inspection 
for heat damage of each left-hand and right-hand TRU beam. The NPRM 
also proposed to require, depending on the findings, inspections of the 
TRU beam latches, the TRU beam clevises, and the thrust reverser outer 
fixed structure rear area; corrective actions; and replacement of TRU 
beams.
    The FAA is issuing this AD to address degradation of TRU beams, 
which could lead to disconnection of the TRU from the engine, causing 
possible damage to the engine adjacent structure and controls and 
possible damage to the airplane. See the MCAI for additional background 
information.

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. Patrick 
Imperatrice expressed support for the NPRM.

Request To Allow Certain Substitutions

    American Airlines identified several errors in the service 
information referenced in EASA AD 2018-0148R1, and requested correction 
of the errors through allowing certain substitutions. The commenter 
noted that the proposed AD requires compliance with EASA AD 2018-
0148R1, which in turn references service information from Airbus, Rolls 
Royce, and Safran. The commenter stated that the applicable service 
information contains several errors when referring to part numbers, 
documents, and the order in which certain steps are to be done. The 
commenter added that Safran verified these errors. Specifically, the 
commenter requested that the proposed AD be revised to allow the 
following substitutions:
    <bullet> The installation of NAS1149 series washers in lieu of 
AN960 washers.
    <bullet> The installation of NAS6303U4 bolts in lieu of NAS6303U04 
bolts.
    <bullet> The use of NSA5050-4C nuts in lieu of NAS5050-4C nuts.
    <bullet> The reference to ``Airbus SRM 51-75'' in lieu of ``Rolls 
Royce SRM 54-02-04'' for paint restoration.
    <bullet> The reference to ``CMM 78-30-20 Figure 39 Graphic 78-30-
20-991-839-A01'' in lieu of ``CMM 78-30-20 Figure

[[Page 61518]]

38 Graphic 78-30-20-991-838-A01'' for replacement of damaged right-hand 
thrust reverser latch covers and hardware.
    <bullet> The allowance to de-energize the ground service network, 
as specified in aircraft maintenance manual (AMM) 24-42-00, after 
closing the fan cowl doors in lieu of de-energizing the ground service 
network before closing the fan cowl doors.
    The FAA acknowledges the referenced errors and agrees with the 
commenter's request. The FAA has added paragraphs (h)(3) through (8) to 
this AD to include exceptions allowing the substitutions requested by 
the commenter.

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 with the changes described previously 
and 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.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related IBR Material Under 1 CFR part 51

    EASA AD 2018-0148R1 describes procedures for a special detailed 
inspection for heat damage of each left-hand and right-hand TRU beam, 
detailed inspections of the TRU beam latches for bush migration and 
cracks or deformation, detailed inspections of the TRU beam clevises 
for cracks and deformation, ultrasonic inspections of the thrust 
reverser outer fixed structure rear area for delamination, replacement 
of TRU beams, and corrective actions. Corrective actions include 
restoring paint, repairing delaminated areas, and measuring latch pin 
hole fitting diameters near migrated bushes. This material 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 51 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.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85.............................              $0              $85           $4,335
----------------------------------------------------------------------------------------------------------------

    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 *
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170....              $0             $170
------------------------------------------------------------------------
* The table only includes the costs for on-condition inspections. The
  FAA has received no definitive data that would enable the agency to
  provide cost estimates for the on-condition corrective actions and
  replacement specified in this AD.

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. The FAA does not control warranty coverage for 
affected individuals. As a result, the FAA has included all known costs 
in our cost estimate.

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

    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) 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.

[[Page 61519]]

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):

2019-20-04 Airbus SAS: Amendment 39-19757; Docket No. FAA-2019-0485; 
Product Identifier 2019-NM-064-AD.

(a) Effective Date

    This AD is effective December 18, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A330-243, A330-243F, 
A330-341, A330-342, and A330-343 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
exhaust.

(e) Reason

    This AD was prompted by reports of thrust reverser unit (TRU) 
beams found with evidence of thermally caused material degradation 
in the rearmost section of the TRU beam at certain latches. The FAA 
is issuing this AD to address degradation of TRU beams, which could 
lead to disconnection of the TRU from the engine, causing possible 
damage to the engine adjacent structure and controls and possible 
damage to the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2018-0148R1, dated April 5, 2019 (``EASA AD 2018-0148R1'').

(h) Exceptions to EASA AD 2018-0148R1

    (1) Where EASA AD 2018-0148R1 refers to its effective date, or 
July 27, 2018 (the effective date of EASA AD 2018-0148, dated July 
13, 2018), this AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2018-0148R1 does not 
apply to this AD.
    (3) Where the service information referenced in EASA AD 2018-
0148R1 specifies the installation of AN960 washers, this AD allows 
the installation of NAS1149 series washers.
    (4) Where the service information referenced in EASA AD 2018-
0148R1 specifies the installation of NAS6303U04 bolts, this AD 
allows the installation of NAS6303U4 bolts.
    (5) Where the service information referenced in EASA AD 2018-
0148R1 specifies the use of NAS5050-4C nuts, this AD allows the use 
of NSA5050-4C nuts.
    (6) Where the service information referenced in EASA AD 2018-
0148R1 refers to ``Rolls Royce SRM 54-02-04'' for paint restoration, 
for this AD replace the phrase ``Rolls Royce SRM 54-02-04'' with 
``Airbus SRM 51-75.''
    (7) Where the service information referenced in EASA AD 2018-
0148R1 refers to ``CMM 78-30-20 Figure 38 Graphic 78-30-20-991-838-
A01'' for replacement of damaged right-hand thrust reverser latch 
covers and hardware, for this AD replace the phrase ``CMM 78-30-20 
Figure 38 Graphic 78-30-20-991-838-A01'' with ``CMM 78-30-20 Figure 
39 Graphic 78-30-20-991-839-A01.''
    (8) Where the service information referenced in EASA AD 2018-
0148R1 specifies to de-energize the ground service network, as 
specified in aircraft maintenance manual (AMM) 24-42-00, before 
closing the fan cowl doors, this AD allows de-energizing the ground 
service network after closing the fan cowl doors.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2018-
0148R1 specifies to submit certain information to the manufacturer, 
this AD does not include that requirement.

(j) 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 International Section, send it to the attention of 
the person identified in paragraph (k) 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 instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2018-0148R1 that contains RC procedures and 
tests: Except as required by paragraph (j)(2) of this AD, RC 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(k) Related Information

    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.

(l) 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) European Union Aviation Safety Agency (EASA) AD 2018-0148R1, 
dated April 5, 2019.
    (ii) [Reserved]
    (3) For information about EASA AD 2018-0148R1, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email [email protected]; internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this material 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. This 
material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2019-0485.
    (5) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on September 27, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-24502 Filed 11-12-19; 8:45 am]
BILLING CODE 4910-13-P

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