83 FR 49269 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 190 (October 1, 2018)

We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus SAS Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report of deficient fatigue performance of high strength steel used in forgings. Components made from the affected high strength steel are installed on the main landing gear (MLG), nose landing gear (NLG), and center landing gear (CLG). This AD requires identifying the part number and serial number of certain components installed on the MLG, NLG, and CLG; replacing affected parts; identifying the airplane's weight variant; and determining the applicable life limit for certain components installed on the MLG, NLG, and CLG. We are issuing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 190 (Monday, October 1, 2018)]
[Rules and Regulations]
[Pages 49269-49272]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-20932]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0395; Product Identifier 2017-NM-136-AD; Amendment 
39-19430; AD 2018-19-29]
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 adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes; 
and Airbus SAS Model A340-200, -300, -500, and -600 series airplanes. 
This AD was prompted by a report of deficient fatigue performance of 
high strength steel used in forgings. Components made from the affected 
high strength steel are installed on the main landing gear (MLG), nose 
landing gear (NLG), and center landing gear (CLG). This AD requires 
identifying the part number and serial number of certain components 
installed on the MLG, NLG, and CLG; replacing affected parts; 
identifying the airplane's weight variant; and determining the 
applicable life limit for certain components installed on the MLG, NLG, 
and CLG. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 5, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 5, 
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; telephone +33 5 61 93 36 
96; fax +33 5 61 93 45 80; email [email protected]; 
internet http://www.airbus.com. You may view this service information 
at the FAA, Transport Standards Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0395.

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-
0395; 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 in the ADDRESSES section.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198-6547; telephone 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 Model A330-200 
Freighter series airplanes, Model A330-200 series airplanes, Model 
A330-300 series airplanes, Model A340-200 series airplanes, Model A340-
300 series airplanes, Model A340-500 series airplanes, and Model A340-
600 series airplanes. The NPRM published in the Federal Register on May 
9, 2018 (83 FR 21196). The NPRM was prompted by a report of deficient 
fatigue performance of high strength steel used in forgings. Components 
made from the affected high strength steel are installed on the MLG, 
NLG, and CLG. The NPRM proposed to require identifying the part number 
and serial number of certain components installed on the MLG, NLG, and 
CLG; replacing affected parts; identifying the airplane's weight 
variant; and determining the applicable life limit for certain 
components installed on the MLG, NLG, and CLG.
    We are issuing this AD to address certain parts made from 300M high 
strength steel, which if uncorrected, could lead to structural failure 
of the landing gear, and possible loss of control of the airplane 
during take-off or landing.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0185, dated September 22, 2017 (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 airplanes, Model A330-200 series airplanes, Model A330-300 
series airplanes, Model A340-200 series airplanes, Model A340-300 
series airplanes, Model A340-500 series

[[Page 49270]]

airplanes, and Model A340-600 series airplanes. The MCAI states:

    In 2006, Messier-Dowty identified a deficiency in the fatigue 
performance of 300M high strength steel used in forgings. The root 
cause for this fatigue deficiency was the processing during 
preparation of the material. After investigation, it was determined 
that the following material sources (S) were affected by this 
fatigue deficiency: Electralloy (S1), RSM (S2A, S2B or S2C), Latrobe 
(S3) and Aubert et Duval (S4).
    Consequently, reduced lives were calculated for certain landing 
gear main fittings, bogie beams and sliding pistons, determined to 
be affected by the 300M material properties quality issue. These 
components are installed on Main, Nose and Centre Landing Gears 
(MLG, NLG, CLG) of A330 and A340 aeroplanes.
    This condition, if not corrected, could lead to structural 
failure of a landing gear, possibly resulting in loss of control of 
the aeroplane during take-off or landing.
    To initially address this potential unsafe condition, Airbus 
published reduced life limits for the affected parts from material 
sources S1, S2 and S3 in the applicable Airworthiness Limitation 
Section (ALS) Part 1. Later, it was determined that ALS Part 1 was 
an inappropriate place for recording the reduced lives and Airbus 
published Service Bulletin (SB) A330-32-3281, SB A340-32-4310, and 
SB A340-32-5119, as applicable, to provide identification and 
replacement instructions for affected parts made of all material 
sources S1, S2, S3 and S4. This action was also accomplished to 
simplify Airbus ALS Part 1.
    For the reasons described above, this [EASA] AD requires 
[identification of the part numbers and serial numbers of the main 
fitting, bogie beam and sliding piston of the MLG, NLG, and CLG, and 
the airplane's weight variant], and implementation of the reduced 
life limits for the affected parts and replacement of any parts that 
are close to, or have exceeded the applicable reduced life limit.

    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-
0395.

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 SAS has issued the following service information.
     Service Bulletin A330-32-3281, Revision 02, including 
Appendixes 01 through 06, dated June 16, 2017; and Service Bulletin 
A340-32-4310, Revision 02, including Appendixes 01 through 06, dated 
June 16, 2017. This service information includes procedures for 
inspections to identify the part numbers and serial numbers of the main 
fittings, bogie beams, and sliding pistons of the MLG; and procedures 
for determining the airplane's weight variant. This service information 
also describes the reduced life limits for affected parts. These 
documents are distinct since they apply to different airplane models.
     Service Bulletin A340-32-5119, Revision 01, including 
Appendixes 01 through 07, dated January 31, 2017. This service 
information includes procedures for inspections to identify the part 
numbers and serial numbers of the main fittings and bogie beams of the 
MLG, NLG, and CLG; and procedures for determining the airplane's weight 
variant. This service information also describes the reduced life 
limits for affected parts.
    In addition, Airbus has issued the following service information, 
which describes life limits for affected parts. These documents are 
distinct since they apply to different airplane models and different 
life limited parts.
     A330 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 09, 
dated September 18, 2017.
     A330 ALS Part 1, ``Safe Life Airworthiness Limitation 
Items (SL-ALI),'' Variation 9.2, dated November 28, 2017.
     A340 ALS Part 1, ``Safe Life Airworthiness Limitation 
Items (SL-ALI),'' Revision 09, dated September 18, 2017.
     A340 ALS Part 1, ``Safe Life Airworthiness Limitation 
Items (SL-ALI),'' Variation 9.2, dated November 28, 2017.
    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 103 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  4 work-hours x $85 per                $0            $340         $35,020
                                         hour = $340.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition part replacements 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 49271]]

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):

2018-19-29 Airbus SAS: Amendment 39-19430; Docket No. FAA-2018-0395; 
Product Identifier 2017-NM-136-AD.

(a) Effective Date

    This AD is effective November 5, 2018.

(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 A330-201, -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.
    (6) Model A340-541 airplanes.
    (7) Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a report of deficient fatigue 
performance of 300M high strength steel used in forgings. Components 
made of 300M high strength steel are installed on the main landing 
gear (MLG), nose landing gear (NLG), and center landing gear (CLG). 
We are issuing this AD to detect and correct certain parts made from 
300M high strength steel, which if uncorrected, could lead to 
structural failure of the landing gear, and possible loss of control 
of the airplane during take-off or landing.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD, an affected part is any main 
fitting, bogie beam, or sliding piston of the MLG, NLG, or CLG 
installed on the airplane, having a part number and serial number 
combination specified in the applicable service information 
identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
    (2) For the purpose of this AD, a serviceable part is any main 
fitting, bogie beam, or sliding piston of the MLG, NLG, or CLG that 
has not exceeded the applicable life limit specified in paragraph 
(g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD, since first 
installation on an airplane.
    (i) The life limit specified in the applicable service 
information identified in paragraphs (h)(1), (h)(2), and (h)(3) of 
this AD.
    (ii) The life limit specified in Airbus A330 Airworthiness 
Limitations Section (ALS) Part 1, ``Safe Life Airworthiness 
Limitation Items (SL-ALI),'' Revision 09, dated September 18, 2017; 
and A330 ALS Part 1, ``Safe Life Airworthiness Limitation Items (SL-
ALI),'' Variation 9.2, dated November 28, 2017.
    (iii) The life limit specified in Airbus A340 Airworthiness 
Limitations Section (ALS) Part 1, ``Safe Life Airworthiness 
Limitation Items (SL-ALI),'' Revision 09, dated September 18, 2017; 
and A340 ALS Part 1, ``Safe Life Airworthiness Limitation Items (SL-
ALI),'' Variation 9.2, dated November 28, 2017.

(h) Identification of Part Number, Serial Number, Weight Variant, and 
Reduced Life Limit

    Within 3 months after the effective date of this AD: Identify 
the part number and serial number of each main fitting, bogie beam, 
and sliding piston of the MLG, NLG, and CLG installed on the 
airplane; identify the airplane's weight variant; and determine the 
applicable reduced life limit; in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane 
maintenance records is acceptable for identification of the 
installed main fittings, bogie beams, and sliding pistons of the 
MLG, NLG, and CLG, provided the part number and serial number of 
each component can be conclusively identified by that review.
    (1) Airbus Service Bulletin A330-32-3281, Revision 02, including 
Appendixes 01 through 06, dated June 16, 2017.
    (2) Airbus Service Bulletin A340-32-4310, Revision 02, including 
Appendixes 01 through 06, dated June 16, 2017.
    (3) Airbus Service Bulletin A340-32-5119, Revision 01, including 
Appendixes 01 through 07, dated January 31, 2017.

(i) Replacement of Affected Parts

    Prior to exceeding the applicable life limit, as specified in 
the applicable service information identified in paragraph (h)(1), 
(h)(2), or (h)(3) of this AD, or within 3 months after the effective 
date of this AD, whichever occurs later: Replace each affected part 
(as defined in paragraph (g)(1) of this AD) with a serviceable part 
(as defined in paragraph (g)(2) of this AD).

(j) Parts Installation Specification

    As of the effective date of this AD, any affected part (as 
defined in paragraph (g)(1) of this AD) may be used as a replacement 
part, provided the affected part is also a serviceable part (as 
defined in paragraph (g)(2) of this AD), and following installation, 
the affected part is replaced prior to exceeding the applicable life 
limit as specified in paragraph (g)(2) 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: [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 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or

[[Page 49272]]

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.

 (l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0185, dated September 22, 2017, 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-2018-0395.
    (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-
6547; telephone 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 A330 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 09, 
dated September 18, 2017.
    (ii) Airbus A330 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Variation 
9.2, dated November 28, 2017.
    (iii) Airbus A340 Airworthiness Limitations Section (ALS) Part 
1, ``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 
09, dated September 18, 2017.
    (iv) Airbus A340 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Variation 
9.2, dated November 28, 2017.
    (v) Airbus Service Bulletin A330-32-3281, Revision 02, including 
Appendixes 01 through 06, dated June 16, 2017.
    (vi) Airbus Service Bulletin A340-32-4310, Revision 02, 
including Appendixes 01 through 06, dated June 16, 2017.
    (vii) Airbus Service Bulletin A340-32-5119, Revision 01, 
including Appendixes 01 through 07, dated January 31, 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; 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 14, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-20932 Filed 9-28-18; 8:45 am]
 BILLING CODE 4910-13-P