83 FR 21196 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 90 (May 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 90 (May 9, 2018)
| Page Range | 21196-21199 | |
| FR Document | 2018-09743 |
[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)] [Proposed Rules] [Pages 21196-21199] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-09743] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0395; Product Identifier 2017-NM-136-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for 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. This proposed 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 proposed AD would 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 [[Page 21197]] certain components installed on the MLG, NLG, and CLG. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 25, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 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. 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 the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0395; Product Identifier 2017-NM-136-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion 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 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 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. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. These documents are distinct since they apply to different airplane models. Service Bulletin A330-32-3281, Revision 02, dated June 16, 2017, including Appendixes 01 through 06; and Service Bulletin A340-32- 4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. 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, dated January 31, 2017, including Appendixes 01 through 07. 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 to 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 Airworthiness Limitations Section (ALS) Part 1, ``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 09, dated September 18, 2017. [[Page 21198]] 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 103 airplanes of U.S. registry. We estimate the following costs to comply with this proposed 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 would enable us to provide cost estimates for the on-condition part replacements specified in this proposed 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 proposed 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 to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): Airbus: Docket No. FAA-2018-0395; Product Identifier 2017-NM-136-AD. (a) Comments Due Date We must receive comments by June 25, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus 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 parts made from 300M high strength steel, which if uncorrected, could lead to structural failure of the landing gear, and possibly 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 [[Page 21199]] 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, dated June 16, 2017, including Appendixes 01 through 06. (2) Airbus Service Bulletin A340-32-4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. (3) Airbus Service Bulletin A340-32-5119, Revision 01, dated January 31, 2017, including Appendixes 01 through 07. (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'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 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. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 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. Issued in Des Moines, Washington, on April 30, 2018. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-09743 Filed 5-8-18; 8:45 am] BILLING CODE 4910-13-P
![21196 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
Part A, Subpart III, Section 44701: (a) Applicability (2) For operations conducted under a 14
General requirements.’’ Under that This AD applies to Model AS–365N2, AS CFR part 119 operating certificate or under
section, Congress charges the FAA with 365 N3, EC 155B, EC155B1, SA–365N1, and 14 CFR part 91, subpart K, we suggest that
promoting safe flight of civil aircraft in SA–366G1 helicopters, certificated in any you notify your principal inspector, or
category. lacking a principal inspector, the manager of
air commerce by prescribing regulations the local flight standards district office or
for practices, methods, and procedures (b) Unsafe Condition certificate holding district office before
the Administrator finds necessary for This AD defines the unsafe condition as operating any aircraft complying with this
safety in air commerce. This regulation disbonding of the aft fuselage outer skin. This AD through an AMOC.
is within the scope of that authority condition could result in loss of aft fuselage
(g) Additional Information
because it addresses an unsafe condition structural integrity and subsequent loss of
that is likely to exist or develop on control of the helicopter. The subject of this AD is addressed in
products identified in this rulemaking European Aviation Safety Agency (EASA) AD
(c) Comments Due Date No. 2017–0165, dated September 5, 2017.
action.
We must receive comments by July 9, 2018. You may view the EASA AD on the internet
Regulatory Findings at http://www.regulations.gov in the AD
(d) Compliance
Docket.
We determined that this proposed AD You are responsible for performing each
would not have federalism implications action required by this AD within the (h) Subject
under Executive Order 13132. This specified compliance time unless it has Joint Aircraft Service Component (JASC)
proposed AD would not have a already been accomplished prior to that time. Code: 5302, Rotorcraft tail boom.
substantial direct effect on the States, on (e) Required Actions Issued in Fort Worth, Texas, on April 26,
the relationship between the national 2018.
(1) Within 110 hours time-in-service (TIS),
Government and the States, or on the tap inspect the aft fuselage outer skin for Lance T. Gant,
distribution of power and disbonding between frames X4630 and Director, Compliance & Airworthiness
responsibilities among the various X6630 in the areas depicted in Figure 1 of Division,Aircraft Certification Service.
levels of government. Airbus Helicopters Alert Service Bulletin
[FR Doc. 2018–09742 Filed 5–8–18; 8:45 am]
For the reasons discussed, I certify (ASB) No. AS365–05.00.77, ASB No. SA366–
this proposed regulation: 05.48, or ASB No. EC155–05A033, all BILLING CODE 4910–13–P
1. Is not a ‘‘significant regulatory Revision 0 and dated July 21, 2017 (ASB
action’’ under Executive Order 12866; AS365–05.00.77, ASB SA366–05.48, or ASB
2. Is not a ‘‘significant rule’’ under the EC155–05A033), as applicable for your DEPARTMENT OF TRANSPORTATION
DOT Regulatory Policies and Procedures model helicopter. Examples of acceptable
and unacceptable disbonding areas are Federal Aviation Administration
(44 FR 11034, February 26, 1979);
depicted in Figure 2 of ASB AS365–05.00.77,
3. Will not affect intrastate aviation in ASB SA366–05.48, and ASB EC155–05A033,
Alaska to the extent that it justifies 14 CFR Part 39
as applicable for your model helicopter.
making a regulatory distinction; and (i) If there is no disbonding, repeat the tap [Docket No. FAA–2018–0395; Product
4. Will not have a significant inspection at intervals not to exceed 660 Identifier 2017–NM–136–AD]
economic impact, positive or negative, hours TIS.
on a substantial number of small entities (ii) If there is disbonding within one RIN 2120–AA64
under the criteria of the Regulatory square-shaped area measuring 3.94 in. x 3.94
in. (10 cm x 10 cm) that does not cross two Airworthiness Directives; Airbus
Flexibility Act.
We prepared an economic evaluation skin panels, repeat the tap inspection at Airplanes
of the estimated costs to comply with intervals not to exceed 110 hours TIS.
(iii) If there is disbonding that exceeds one AGENCY: Federal Aviation
this proposed AD and placed it in the square-shaped area measuring 3.94 in. x 3.94 Administration (FAA), DOT.
AD docket. in. (10 cm x 10 cm) or crosses two skin ACTION: Notice of proposed rulemaking
List of Subjects in 14 CFR Part 39 panels, before further flight, repair or replace (NPRM).
the panel. Thereafter, tap inspect the panel
Air transportation, Aircraft, Aviation at intervals not to exceed 660 hours TIS. SUMMARY: We propose to adopt a new
safety, Incorporation by reference, (2) Within 220 hours TIS, and thereafter at airworthiness directive (AD) for all
Safety. intervals not to exceed 110 hours TIS, clean
Airbus Model A330–200 Freighter series
the aft fuselage outer skin and using a light,
The Proposed Amendment visually inspect for distortion, wrinkling, and airplanes, Model A330–200 series
corrosion between frames X4630 and X6630 airplanes, Model A330–300 series
Accordingly, under the authority
as depicted in Figure 1 of ASB AS365– airplanes, Model A340–200 series
delegated to me by the Administrator,
05.00.77, ASB SA366–05.48, or ASB EC155– airplanes, Model A340–300 series
the FAA proposes to amend 14 CFR part
05A033, as applicable for your model airplanes, Model A340–500 series
39 as follows: helicopter. If there is any distortion, airplanes, and Model A340–600 series
wrinkling, or corrosion, before further flight, airplanes. This proposed AD was
PART 39—AIRWORTHINESS tap inspect the area for disbonding by
DIRECTIVES prompted by a report of deficient fatigue
following the inspection instructions in
paragraph (e)(1) of this AD. performance of high strength steel used
■ 1. The authority citation for part 39 in forgings. Components made from the
continues to read as follows: (f) Alternative Methods of Compliance affected high strength steel are installed
(AMOCs) on the main landing gear (MLG), nose
Authority: 49 U.S.C. 106(g), 40113, 44701.
amozie on DSK3GDR082PROD with PROPOSALS
(1) The Manager, Safety Management landing gear (NLG), and center landing
§ 39.13 [Amended] Section, Rotorcraft Standards Branch, FAA, gear (CLG). This proposed AD would
■ 2. The FAA amends § 39.13 by adding may approve AMOCs for this AD. Send your require identifying the part number and
proposal to: Matt Fuller, Senior Aviation
the following new airworthiness serial number of certain components
Safety Engineer, Safety Management Section,
directive (AD): Rotorcraft Standards Branch, FAA, 10101 installed on the MLG, NLG, and CLG;
Airbus Helicopters: Docket No. FAA–2018– Hillwood Pkwy., Fort Worth, TX 76177; replacing affected parts; identifying the
0384; Product Identifier 2017–SW–061– telephone (817) 222–5110; email 9-ASW- airplane’s weight variant; and
AD. FTW-AMOC-Requests@faa.gov. determining the applicable life limit for
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![Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules 21197
certain components installed on the NM–136–AD’’ at the beginning of your part numbers and serial numbers of the main
MLG, NLG, and CLG. We are proposing comments. We specifically invite fitting, bogie beam and sliding piston of the
this AD to address the unsafe condition comments on the overall regulatory, MLG, NLG, and CLG, and the airplane’s
on these products. economic, environmental, and energy weight variant], and implementation of the
reduced life limits for the affected parts and
DATES: We must receive comments on aspects of this NPRM. We will consider replacement of any parts that are close to, or
this proposed AD by June 25, 2018. all comments received by the closing have exceeded the applicable reduced life
ADDRESSES: You may send comments,
date and may amend this NPRM based limit.
using the procedures found in 14 CFR on those comments.
We will post all comments we You may examine the MCAI in the
11.43 and 11.45, by any of the following AD docket on the internet at http://
receive, without change, to http://
methods: www.regulations.gov by searching for
www.regulations.gov, including any
• Federal eRulemaking Portal: Go to and locating Docket No. FAA–2018–
personal information you provide. We
http://www.regulations.gov. Follow the 0395.
will also post a report summarizing each
instructions for submitting comments.
• Fax: 202–493–2251. substantive verbal contact we receive Related Service Information Under 1
• Mail: U.S. Department of about this NPRM. CFR Part 51
Transportation, Docket Operations, Discussion Airbus has issued the following
M–30, West Building Ground Floor, The European Aviation Safety Agency service information. These documents
Room W12–140, 1200 New Jersey (EASA), which is the Technical Agent are distinct since they apply to different
Avenue SE, Washington, DC 20590. for the Member States of the European airplane models.
• Hand Delivery: Deliver to Mail Union, has issued EASA AD 2017–0185, • Service Bulletin A330–32–3281,
address above between 9 a.m. and 5 dated September 22, 2017 (referred to Revision 02, dated June 16, 2017,
p.m., Monday through Friday, except after this as the Mandatory Continuing including Appendixes 01 through 06;
Federal holidays. Airworthiness Information, or ‘‘the and Service Bulletin A340–32–4310,
For service information identified in Revision 02, dated June 16, 2017,
MCAI’’), to correct an unsafe condition
this NPRM, contact Airbus SAS, including Appendixes 01 through 06.
for all Airbus Model A330–200
Airworthiness Office—EAL, 1 Rond This service information includes
Freighter series airplanes, Model A330–
Point Maurice Bellonte, 31707 Blagnac procedures for inspections to identify
200 series airplanes, Model A330–300
Cedex, France; telephone +33 5 61 93 36 the part numbers and serial numbers of
series airplanes, Model A340–200 series
96; fax +33 5 61 93 45 80; email the main fittings, bogie beams, and
airplanes, Model A340–300 series
airworthiness.A330–A340@airbus.com; sliding pistons of the MLG; and
airplanes, Model A340–500 series
internet http://www.airbus.com. You procedures for determining the
airplanes, and Model A340–600 series
may view this service information at the airplane’s weight variant. This service
airplanes. The MCAI states:
FAA, Transport Standards Branch, 2200 information also describes the reduced
South 216th St., Des Moines, WA. For In 2006, Messier-Dowty identified a
deficiency in the fatigue performance of life limits for affected parts. These
information on the availability of this documents are distinct since they apply
300M high strength steel used in forgings.
material at the FAA, call 206–231–3195. The root cause for this fatigue deficiency was to different airplane models.
Examining the AD Docket the processing during preparation of the • Service Bulletin A340–32–5119,
material. After investigation, it was Revision 01, dated January 31, 2017,
You may examine the AD docket on determined that the following material including Appendixes 01 through 07.
the internet at http:// sources (S) were affected by this fatigue This service information includes
www.regulations.gov by searching for deficiency: Electralloy (S1), RSM (S2A, S2B
procedures for inspections to identify
and locating Docket No. FAA–2018– or S2C), Latrobe (S3) and Aubert et Duval
(S4). the part numbers and serial numbers of
0395; or in person at the Docket the main fittings and bogie beams of the
Consequently, reduced lives were
Management Facility between 9 a.m. MLG, NLG, and CLG; and procedures
calculated for certain landing gear main
and 5 p.m., Monday through Friday, fittings, bogie beams and sliding pistons, for determining the airplane’s weight
except Federal holidays. The AD docket determined to be affected by the 300M variant. This service information also
contains this NPRM, the regulatory material properties quality issue. These describes the reduced life limits for
evaluation, any comments received, and components are installed on Main, Nose and affected parts.
other information. The street address for Centre Landing Gears (MLG, NLG, CLG) of
A330 and A340 aeroplanes.
In addition, Airbus has issued the
the Docket Operations office (telephone following service information, which
800–647–5527) is in the ADDRESSES This condition, if not corrected, could lead
to structural failure of a landing gear, describes life limits for affected parts.
section. Comments will be available in possibly resulting in loss of control of the These documents are distinct since they
the AD docket shortly after receipt. aeroplane during take-off or landing. apply to different airplane models and
FOR FURTHER INFORMATION CONTACT: To initially address this potential unsafe to different life limited parts.
Vladimir Ulyanov, Aerospace Engineer, condition, Airbus published reduced life • A330 Airworthiness Limitations
International Section, Transport limits for the affected parts from material Section (ALS) Part 1, ‘‘Safe Life
Standards Branch, FAA, 2200 South sources S1, S2 and S3 in the applicable
Airworthiness Limitation Section (ALS) Part Airworthiness Limitation Items (SL–
216th St., Des Moines, WA 98198–6547; 1. Later, it was determined that ALS Part 1 ALI),’’ Revision 09, dated September 18,
telephone and fax 206–231–3229. was an inappropriate place for recording the 2017.
SUPPLEMENTARY INFORMATION: reduced lives and Airbus published Service • A330 ALS Part 1, ‘‘Safe Life
amozie on DSK3GDR082PROD with PROPOSALS
Bulletin (SB) A330–32–3281, SB A340–32– Airworthiness Limitation Items (SL–
Comments Invited 4310, and SB A340–32–5119, as applicable, ALI),’’ Variation 9.2, dated November
We invite you to send any written to provide identification and replacement 28, 2017.
relevant data, views, or arguments about instructions for affected parts made of all • A340 Airworthiness Limitations
material sources S1, S2, S3 and S4. This
this proposal. Send your comments to action was also accomplished to simplify Section (ALS) Part 1, ‘‘Safe Life
an address listed under the ADDRESSES Airbus ALS Part 1. Airworthiness Limitation Items (SL–
section. Include ‘‘Docket No. FAA– For the reasons described above, this ALI),’’ Revision 09, dated September 18,
2018–0395; Product Identifier 2017– [EASA] AD requires [identification of the 2017.
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![21198 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules
• A340 ALS Part 1, ‘‘Safe Life FAA’s Determination and Requirements AD because we evaluated all pertinent
Airworthiness Limitation Items (SL– of This Proposed AD information and determined an unsafe
ALI),’’ Variation 9.2, dated November This product has been approved by condition exists and is likely to exist or
28, 2017. the aviation authority of another develop on other products of these same
This service information is reasonably country, and is approved for operation type designs.
available because the interested parties in the United States. Pursuant to our Costs of Compliance
have access to it through their normal bilateral agreement with the State of
Design Authority, we have been notified We estimate that this proposed AD
course of business or by the means
of the unsafe condition described in the affects 103 airplanes of U.S. registry.
identified in the ADDRESSES section.
MCAI and service information We estimate the following costs to
referenced above. We are proposing this comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection ........................................................ 4 work-hours × $85 per hour = $340 ............. $0 $340 $35,020
We have received no definitive data substantial direct effect on the States, on (b) Affected ADs
that would enable us to provide cost the relationship between the national None.
estimates for the on-condition part Government and the States, or on the
(c) Applicability
replacements specified in this proposed distribution of power and
AD. responsibilities among the various This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(7)
levels of government.
Authority for This Rulemaking of this AD; certificated in any category; all
For the reasons discussed above, I manufacturer serial numbers.
Title 49 of the United States Code certify this proposed regulation: (1) Model A330–201, –202, –203, –223, and
specifies the FAA’s authority to issue 1. Is not a ‘‘significant regulatory –243 airplanes.
rules on aviation safety. Subtitle I, action’’ under Executive Order 12866; (2) Model A330–223F and –243F airplanes.
section 106, describes the authority of 2. Is not a ‘‘significant rule’’ under the (3) Model A330–301, –302, –303, –321,
the FAA Administrator. ‘‘Subtitle VII: –322, –323, –341, –342, and –343 airplanes.
DOT Regulatory Policies and Procedures
Aviation Programs,’’ describes in more (4) Model A340–211, –212, and –213
(44 FR 11034, February 26, 1979); airplanes.
detail the scope of the Agency’s 3. Will not affect intrastate aviation in (5) Model A340–311, –312, and –313
authority. Alaska; and airplanes.
We are issuing this rulemaking under 4. Will not have a significant (6) Model A340–541 airplanes.
the authority described in ‘‘Subtitle VII, economic impact, positive or negative, (7) Model A340–642 airplanes.
Part A, Subpart III, Section 44701: on a substantial number of small entities
General requirements.’’ Under that (d) Subject
under the criteria of the Regulatory Air Transport Association (ATA) of
section, Congress charges the FAA with Flexibility Act.
promoting safe flight of civil aircraft in America Code 32, Landing Gear.
air commerce by prescribing regulations List of Subjects in 14 CFR Part 39 (e) Reason
for practices, methods, and procedures Air transportation, Aircraft, Aviation This AD was prompted by a report of
the Administrator finds necessary for safety, Incorporation by reference, deficient fatigue performance of 300M high
safety in air commerce. This regulation Safety. strength steel used in forgings. Components
is within the scope of that authority made of 300M high strength steel are
because it addresses an unsafe condition The Proposed Amendment installed on the main landing gear (MLG),
that is likely to exist or develop on nose landing gear (NLG), and center landing
Accordingly, under the authority gear (CLG). We are issuing this AD to detect
products identified in this rulemaking delegated to me by the Administrator, and correct parts made from 300M high
action. the FAA proposes to amend 14 CFR part strength steel, which if uncorrected, could
This proposed AD is issued in 39 as follows: lead to structural failure of the landing gear,
accordance with authority delegated by and possibly loss of control of the airplane
the Executive Director, Aircraft PART 39—AIRWORTHINESS during take-off or landing.
Certification Service, as authorized by DIRECTIVES (f) Compliance
FAA Order 8000.51C. In accordance
1. The authority citation for part 39 Comply with this AD within the
with that order, issuance of ADs is ■
compliance times specified, unless already
normally a function of the Compliance continues to read as follows: done.
and Airworthiness Division, but during Authority: 49 U.S.C. 106(g), 40113, 44701.
this transition period, the Executive (g) Definitions
Director has delegated the authority to § 39.13 [Amended] (1) For the purpose of this AD, an affected
issue ADs applicable to transport ■ 2. The FAA amends § 39.13 by adding part is any main fitting, bogie beam, or
amozie on DSK3GDR082PROD with PROPOSALS
category airplanes to the Director of the sliding piston of the MLG, NLG, or CLG
the following new airworthiness
installed on the airplane, having a part
System Oversight Division. directive (AD): number and serial number combination
Regulatory Findings Airbus: Docket No. FAA–2018–0395; Product specified in the applicable service
Identifier 2017–NM–136–AD. information identified in paragraphs (h)(1),
We determined that this proposed AD (h)(2), and (h)(3) of this AD.
would not have federalism implications (a) Comments Due Date (2) For the purpose of this AD, a
under Executive Order 13132. This We must receive comments by June 25, serviceable part is any main fitting, bogie
proposed AD would not have a 2018. beam, or sliding piston of the MLG, NLG, or
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![Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules 21199
CLG that has not exceeded the applicable life (1) Alternative Methods of Compliance Issued in Des Moines, Washington, on
limit specified in paragraph (g)(2)(i), (g)(2)(ii), (AMOCs): The Manager, International April 30, 2018.
or (g)(2)(iii) of this AD, since first installation Section, Transport Standards Branch, FAA, Dionne Palermo,
on an airplane. has the authority to approve AMOCs for this Acting Director, System Oversight Division,
(i) The life limit specified in the applicable AD, if requested using the procedures found Aircraft Certification Service.
service information identified in paragraphs in 14 CFR 39.19. In accordance with 14 CFR
(h)(1), (h)(2), and (h)(3) of this AD. [FR Doc. 2018–09743 Filed 5–8–18; 8:45 am]
39.19, send your request to your principal
(ii) The life limit specified in Airbus A330 inspector or local Flight Standards District BILLING CODE 4910–13–P
Airworthiness Limitations Section (ALS) Part Office, as appropriate. If sending information
1, ‘‘Safe Life Airworthiness Limitation Items
directly to the International Section, send it
(SL–ALI),’’ Revision 09, dated September 18, DEPARTMENT OF TRANSPORTATION
to the attention of the person identified in
2017, and A330 ALS Part 1, ‘‘Safe Life
Airworthiness Limitation Items (SL–ALI),’’ paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC-
Federal Aviation Administration
Variation 9.2, dated November 28, 2017.
(iii) The life limit specified in Airbus A340 REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate 14 CFR Part 39
Airworthiness Limitations Section (ALS) Part
1, ‘‘Safe Life Airworthiness Limitation Items principal inspector, or lacking a principal [Docket No. FAA–2018–0326; Product
(SL–ALI),’’ Revision 09, dated September 18, inspector, the manager of the local flight Identifier 2018–CE–006–AD]
2017, and A340 ALS Part 1, ‘‘Safe Life standards district office/certificate holding
Airworthiness Limitation Items (SL–ALI),’’ district office. RIN 2120–AA64
Variation 9.2, dated November 28, 2017. (2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective Airworthiness Directives; SOCATA
(h) Identification of Part Number, Serial Airplanes
Number, Weight Variant, and Reduced Life actions from a manufacturer, the action must
Limit be accomplished using a method approved AGENCY: Federal Aviation
by the Manager, International Section, Administration (FAA), Department of
Within 3 months after the effective date of Transport Standards Branch, FAA; or the
this AD: Identify the part number and serial Transportation (DOT).
European Aviation Safety Agency (EASA); or
number of each main fitting, bogie beam, and ACTION: Notice of proposed rulemaking
Airbus’s EASA Design Organization
sliding piston of the MLG, NLG, and CLG (NPRM).
installed on the airplane; identify the Approval (DOA). If approved by the DOA,
airplane’s weight variant; and determine the the approval must include the DOA-
authorized signature. SUMMARY: We propose to supersede
applicable reduced life limit; in accordance Airworthiness Directive (AD) 98–16–03
with the Accomplishment Instructions of the (3) Required for Compliance (RC): If any
applicable service information identified in service information contains procedures or for SOCATA Models TB 9 and TB 10
paragraph (h)(1), (h)(2), or (h)(3) of this AD. tests that are identified as RC, those airplanes. This proposed AD results
A review of airplane maintenance records is procedures and tests must be done to comply from mandatory continuing
acceptable for identification of the installed with this AD; any procedures or tests that are airworthiness information (MCAI)
main fittings, bogie beams, and sliding not identified as RC are recommended. Those originated by an aviation authority of
pistons of the MLG, NLG, and CLG, provided procedures and tests that are not identified another country to identify and correct
the part number and serial number of each as RC may be deviated from using accepted an unsafe condition on an aviation
component can be conclusively identified by methods in accordance with the operator’s product. The MCAI describes the unsafe
that review. maintenance or inspection program without
(1) Airbus Service Bulletin A330–32–3281,
condition as fatigue cracking of the wing
obtaining approval of an AMOC, provided front attachments on the wing and
Revision 02, dated June 16, 2017, including the procedures and tests identified as RC can
Appendixes 01 through 06. fuselage sides. We are issuing this
be done and the airplane can be put back in proposed AD to require actions to
(2) Airbus Service Bulletin A340–32–4310,
an airworthy condition. Any substitutions or
Revision 02, dated June 16, 2017, including address the unsafe condition on these
changes to procedures or tests identified as
Appendixes 01 through 06. products.
(3) Airbus Service Bulletin A340–32–5119, RC require approval of an AMOC.
Revision 01, dated January 31, 2017, DATES: We must receive comments on
(l) Related Information
including Appendixes 01 through 07. this proposed AD by June 25, 2018.
(1) Refer to Mandatory Continuing
ADDRESSES: You may send comments by
(i) Replacement of Affected Parts Airworthiness Information (MCAI) EASA AD
2017–0185, dated September 22, 2017, for
any of the following methods:
Prior to exceeding the applicable life limit, • Federal eRulemaking Portal: Go to
as specified in the applicable service related information. This MCAI may be
information identified in paragraph (h)(1), found in the AD docket on the internet at http://www.regulations.gov. Follow the
(h)(2), or (h)(3) of this AD, or within 3 http://www.regulations.gov by searching for instructions for submitting comments.
months after the effective date of this AD, and locating Docket No. FAA–2018–0395. • Fax: (202) 493–2251.
whichever occurs later: Replace each affected (2) For more information about this AD, • Mail: U.S. Department of
part (as defined in paragraph (g)(1) of this contact Vladimir Ulyanov, Aerospace Transportation, Docket Operations, M–
AD) with a serviceable part (as defined in Engineer, International Section, Transport 30, West Building Ground Floor, Room
paragraph (g)(2) of this AD). Standards Branch, FAA, 2200 South 216th W12–140, 1200 New Jersey Avenue SE,
(j) Parts Installation Specification St., Des Moines, WA 98198–6547; telephone Washington, DC 20590.
As of the effective date of this AD, any
and fax 206–231–3229. • Hand Delivery: U.S. Department of
(3) For service information identified in Transportation, Docket Operations, M–
affected part (as defined in paragraph (g)(1)
this AD, contact Airbus SAS, Airworthiness 30, West Building Ground Floor, Room
of this AD) may be used as a replacement
Office—EAL, 1 Rond Point Maurice Bellonte,
part, provided the affected part is also a W12–140, 1200 New Jersey Avenue SE,
31707 Blagnac Cedex, France; telephone +33
amozie on DSK3GDR082PROD with PROPOSALS
serviceable part (as defined in paragraph Washington, DC 20590, between 9 a.m.
(g)(2) of this AD), and following installation, 5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com; and 5 p.m., Monday through Friday,
the affected part is replaced prior to except Federal holidays.
exceeding the applicable life limit as internet http://www.airbus.com. You may
view this service information at the FAA, For service information identified in
specified in paragraph (g)(2) of this AD.
Transport Standards Branch, 2200 South this proposed AD, contact SOCATA,
(k) Other FAA AD Provisions 216th St., Des Moines, WA. For information Direction des services, 65921 Tarbes
The following provisions also apply to this on the availability of this material at the Cedex 9, France; phone: +33 (0) 5 62 41
AD: FAA, call 206–231–3195. 73 00; fax: +33 (0) 5 62 41 76 54; email:
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Document Created: 2018-05-09 03:17:35
Document Modified: 2018-05-09 03:17:35
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 25, 2018. | |
| 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. | |
| FR Citation | 83 FR 21196 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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