
[Federal Register Volume 84, Number 39 (Wednesday, February 27, 2019)]
[Rules and Regulations]
[Pages 6317-6321]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03256]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0904; Product Identifier 2018-NM-108-AD; Amendment 
39-19575; AD 2019-03-23]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes, 
and Model A340-200, -300, -500, and -600 series airplanes. This AD was 
prompted by a report that certain sensor struts, in the case of down 
drive element disconnection, would be unable to provide failure 
detection information for flap movements. This AD requires repetitive 
inspections of certain drive station elements and sensor struts; an 
inspection of certain other drive station elements if necessary; and 
corrective actions if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective April 3, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 3, 
2019.

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; phone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0904.

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-
0904; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday

[[Page 6318]]

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; phone and fax: 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus SAS Model A330-
200, -200 Freighter, and -300 series airplanes, and Model A340-200, -
300, -500, and -600 series airplanes. The NPRM published in the Federal 
Register on November 5, 2018 (83 FR 55303). The NPRM was prompted by a 
report that certain sensor struts, in the case of down drive element 
disconnection, would be unable to provide failure detection 
information. The NPRM proposed to require repetitive inspections of 
certain drive station elements and sensor struts; an inspection of 
certain other drive station elements if necessary; and corrective 
actions if necessary.
    We are issuing this AD to address abnormal flap movement due to 
mechanical drive station element disconnection at flap track station 4 
or station 5 which could lead to undetected down drive shaft 
disconnection. Such a condition could result in complete flap 
disconnection in the case of additional failure on the remaining flap 
drive station, and could ultimately result in loss of 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 
2018-0151, dated July 16, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus SAS Model A330-200 Freighter series, 
Model A330-200 series, Model A330-300 series, Model A340-200 series, 
Model A340-300 series, Model A340-500 series, and Model A340-600 series 
airplanes. The MCAI states:

    Design features of the track station 4 sensor struts, 
respectively installed on the right hand (RH) and left hand (LH) 
wings of an aeroplane, ensure detection of any abnormal flap 
movement in case of a mechanical DSE [drive station element] 
disconnection at the level of the flap track station 4 or flap track 
station 5. Evidence was collected revealing that the track station 4 
sensor strut, in case of a down drive element disconnection, would 
be unable to provide failure detection information.
    This condition, if not detected and corrected, in the case of an 
additional failure on the remaining flap drive station, could lead 
to a complete flap disconnection, possibly resulting in loss of 
control of the aeroplane.
    To address this potential unsafe condition, Airbus published the 
applicable SB [Airbus Service Bulletin A330-27-3226, dated April 5, 
2018; Airbus Service Bulletin A340-27-4206, dated April 3, 2018; or 
Airbus Service Bulletin A340-27-5071, dated April 3, 2018; as 
applicable] to provide inspection instructions of the track station 
4 and track station 5 DSE and sensor struts of the LH and RH wings.
    For the reasons described above, this [EASA] AD requires 
repetitive [detailed] inspections of the LH and RH track station 4 
[DSE, repetitive general visual inspections of the LH and RH track 
station 4 sensor struts,] and [for certain airplanes, a one-time 
detailed inspection of the LH or RH, as applicable] track station 5 
DSE * * * and, depending on findings, accomplishment of applicable 
corrective action(s).

    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-
0904.

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:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-27-3226, dated April 5, 2018.
     Airbus Service Bulletin A340-27-4206, dated April 3, 2018.
     Airbus Service Bulletin A340-27-5071, dated April 3, 2018.
    This service information describes procedures for repetitive 
detailed inspections of the LH and RH track station 4 drive station 
elements; repetitive general visual inspections of the LH and RH track 
station 4 sensor struts; a detailed inspection of the track station 5 
drive station elements if any discrepancy is found during a general 
visual inspection; and corrective actions (i.e., replacement of 
affected parts). These documents are distinct since they apply to 
different 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 105 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
              Labor cost                   Parts cost        Cost per product         Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 7 work-hours x $85 per hour =                 $0   Up to $595..............  Up to $62,475.
 $595.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    We estimate that it would take about 1 work-hour per product to 
comply with the reporting requirement in this AD. The average labor 
rate is $85 per hour. Based on these figures, we estimate the cost of 
reporting the inspection results on U.S. operators to be $8,925, or $85 
per product.
    We have received no definitive data that would enable us to provide 
cost

[[Page 6319]]

estimates for the on-condition actions 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. We do not control warranty coverage for affected 
individuals. As a result, we have included all known costs in our cost 
estimate.

Paperwork Reduction Act

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes 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) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

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

2019-03-23 Airbus SAS: Amendment 39-19575; Docket No. FAA-2018-0904; 
Product Identifier 2018-NM-108-AD.

(a) Effective Date

    This AD is effective April 3, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (c)(7) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Model A330-223F and -243F airplanes.
    (2) Model A330-201, -202, -203, -223, and -243 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.
    (6) Model A340-541 airplanes.
    (7) Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by a report that the right-hand (RH) and 
left-hand (LH) track station 4 sensor struts, in the case of down 
drive element disconnection, would be unable to provide failure 
detection information for flap movements. We are issuing this AD to 
address abnormal flap movement due to mechanical drive station 
element disconnection at flap track station 4 or station 5 which 
could lead to undetected down drive shaft disconnection. Such a 
condition could result in complete flap disconnection in the case of 
additional failure on the remaining flap drive station, and could 
ultimately result in loss of control of the airplane.

(f) Compliance

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

(g) Definitions

    For the purpose of this AD, the drive station elements are 
defined as the down drive, down drive shaft, geared rotary actuator 
(gearbox), geared rotary actuator (output lever and fork end), and 
drive strut.

(h) Detailed and General Visual Inspections

    (1) At the applicable times specified in paragraphs (h)(1)(i) 
and (h)(1)(ii) of this AD, and thereafter not to exceed the 
applicable intervals specified in table 1 to paragraph (h)(1) of 
this AD, do a detailed inspection of the LH and RH track station 4 
drive station elements for corrosion or ruptured, loose, or missing 
components (including any attached bolts and nuts that are loose, 
broken, or missing) and a general visual inspection of the LH and RH 
track station 4 sensor struts for corrosion or ruptured, loose, or 
missing components (including any attached bolts that are loose, 
broken, or missing), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-27-3226, dated April 5, 
2018; Airbus Service Bulletin A340-27-4206, dated April 3, 2018; or 
Airbus Service Bulletin A340-27-5071, dated April 3, 2018; as 
applicable.

[[Page 6320]]

[GRAPHIC] [TIFF OMITTED] TR27FE19.000

    (i) For airplanes that, as of the effective date of this AD, 
have accumulated less than 1,000 flight cycles since first flight: 
Before exceeding 24 months since first flight or within 18 months 
after the effective date of this AD, whichever occurs later, but 
without exceeding 2,300 flight cycles since first flight.
    (ii) For airplanes that, as of the effective date of this AD, 
have accumulated 1,000 or more flight cycles since first flight: 
Within 1,000 flight cycles or 12 months, whichever occurs first 
after the effective date of this AD.
    (2) If, during any general visual inspection required by 
paragraph (h)(1) of this AD, any corrosion is detected or any 
ruptured, loose, or missing components (including any attached bolts 
that are loose, broken, or missing) are detected, before further 
flight, accomplish a detailed inspection of the applicable LH or RH 
track station 5 drive station elements for corrosion or ruptured, 
loose, or missing components (including any attached bolts and nuts 
that are loose, broken, or missing) in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3226, 
dated April 5, 2018; Airbus Service Bulletin A340-27-4206, dated 
April 3, 2018; or Airbus Service Bulletin A340-27-5071, dated April 
3, 2018; as applicable.

(i) Corrective Actions

    (1) If, during any detailed inspection required by paragraph 
(h)(1) of this AD, any corrosion is detected or any ruptured, loose, 
or missing components (including any attached bolts and nuts that 
are loose, broken, or missing) are detected, before further flight, 
replace each affected part with a serviceable part in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-27-3226, dated April 5, 2018; Airbus Service Bulletin A340-27-
4206, dated April 3, 2018; or Airbus Service Bulletin A340-27-5071, 
dated April 3, 2018; as applicable, or 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.
    (2) If, during any general visual inspection required by 
paragraph (h)(1) of this AD, any corrosion is detected or any 
ruptured, loose, or missing components (including any attached bolts 
that are loose, broken, or missing) are detected, before further 
flight, replace each affected part with a serviceable part in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3226, dated April 5, 2018; Airbus Service Bulletin 
A340-27-4206, dated April 3, 2018; or Airbus Service Bulletin A340-
27-5071, dated April 3, 2018; as applicable, or using a method 
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.
    (3) If, during any detailed inspection required by paragraph 
(h)(2) of this AD, any corrosion is detected or any ruptured, loose, 
or missing components (including any attached bolts and nuts that 
are loose, broken, or missing) are detected, before further flight, 
replace each affected part with a serviceable part in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-27-3226, dated April 5, 2018; Airbus Service Bulletin A340-27-
4206, dated April 3, 2018; or Airbus Service Bulletin A340-27-5071, 
dated April 3, 2018; as applicable, or using a method 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) Reporting

    At the applicable time specified in paragraph (j)(1) or (j)(2) 
of this AD: Report the results (positive or negative) of each 
inspection required by paragraphs (h)(1) and (h)(2) of this AD to 
Airbus Service Bulletin Reporting Online Application on Airbus World 
(https://w3.airbus.com/), or submit the results to Airbus in 
accordance with the instructions of Airbus Service Bulletin A330-27-
3226, dated April 5, 2018; Airbus Service Bulletin A340-27-4206, 
dated April 3, 2018; or Airbus Service Bulletin A340-27-5071, dated 
April 3, 2018.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(k) 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 (l)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or using a method 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
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.
    (4) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 1 
hour per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW, Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

[[Page 6321]]

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0151, dated July 16, 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-2018-0904.
    (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; 
phone and fax: 206-231-3229.

(m) 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 A330-27-3226, dated April 5, 2018.
    (ii) Airbus Service Bulletin A340-27-4206, dated April 3, 2018.
    (iii) Airbus Service Bulletin A340-27-5071, dated April 3, 2018.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: 
+33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
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 February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-03256 Filed 2-26-19; 8:45 am]
 BILLING CODE 4910-13-P


