80 FR 11964 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 43 (March 5, 2015)

Page Range		11964-11966
FR Document		2015-02923
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This proposed AD was prompted by a cracked upper cardan in the main landing gear (MLG). This proposed AD would require revising the maintenance or inspection program, as applicable, to reduce the life limits for the MLG upper cardan for certain installations. We are proposing this AD to prevent failure of the upper cardan in the MLG, which could result in MLG collapse and subsequent damage to the airplane and injury to occupants.
Federal Register, Volume 80 Issue 43 (Thursday, March 5, 2015)
[Federal Register Volume 80, Number 43 (Thursday, March 5, 2015)]
[Proposed Rules]
[Pages 11964-11966]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-02923]



[[Page 11964]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0244; Directorate Identifier 2014-NM-127-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 A318, A319, and A320 series airplanes. This proposed AD 
was prompted by a cracked upper cardan in the main landing gear (MLG). 
This proposed AD would require revising the maintenance or inspection 
program, as applicable, to reduce the life limits for the MLG upper 
cardan for certain installations. We are proposing this AD to prevent 
failure of the upper cardan in the MLG, which could result in MLG 
collapse and subsequent damage to the airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by April 20, 2015.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. Because this service information is incorporated by 
reference in AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 
2015), it is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0692.

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-2015-
0244; 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 proposed AD, 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0244; 
Directorate Identifier 2014-NM-127-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD 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 proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0141, dated June 4, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
Airbus Model A318, A319, and A320 series airplanes. The MCAI states:

    During an A320-200 77T main landing gear (MLG) fatigue test by 
Messier Bugatti-Dowty (MBD), an upper cardan was found with a crack, 
emanating from the grease hole/main lug intersection. The affected 
upper cardan, Part Number (P/N) 201163620, is listed in the 
applicable Airworthiness Limitations Section (ALS) Part 1 with a 
demonstrated fatigue life of 60,000 landings.
    This condition, if not corrected, could lead to MLG upper cardan 
failure, possibly resulting in MLG collapse and subsequent damage to 
the aeroplane and injury to occupants.
    Prompted by these findings and further to analysis, it has been 
decided to reduce the life limit for certain installations of the P/
N 201163620 MLG upper cardan.
    For the reasons described above, this AD requires implementation 
of the new life limits, as applicable, and replacement of any 
affected MLG upper cardan units that have already exceeded the 
reduced limit.
    The reduced life limits for the affected MLG upper cardan are 
expected to be incorporated in a next revision of the Airbus A318/
A319/A320/A321 ALS Part 1.

    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-2015-
0244.

Related AD

    AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
applicable to all Airbus Model A318, A319, A320, and A321 series 
airplanes, requires revising the maintenance or inspection program, as 
applicable, to incorporate certain Airworthiness Limitation Items. 
Paragraph (n)(1) of AD 2014-23-15 requires incorporating Part 1--Safe 
Life Airworthiness Limitation Items, of the Airbus A318/A319/A320/A321 
ALS, Revision 02, dated May 13, 2011. AD 2014-23-15 corresponds to EASA 
AD 2013-0147, dated July 16, 2013. This proposed AD would not supersede 
AD 2014-23-15, but would require a reduced life limit for MLG upper 
cardans having part number (P/N) 201163620 and installed in certain 
airplane configurations. Accomplishing the requirement specified in 
paragraph (g) of this proposed AD terminates the life limit required by 
paragraph (n)(1) of AD 2014-23-15 for P/N 201163620, which is installed 
in certain airplane configurations identified in this proposed AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. This 
document provides revised instructions

[[Page 11965]]

and life limits for airworthiness limitations items. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. This service information is 
incorporated by reference in AD 2014-23-15, Amendment 39-18031 (80 FR 
3871, January 26, 2015). It is reasonably available; see ADDRESSES for 
ways to access this service information.

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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    EASA AD 2014-0141, dated June 4, 2014, requires replacement of each 
MLG upper cardan having P/N 201163620 with a serviceable part within 3 
months after the effective date of that EASA AD, or prior to exceeding 
new life limits, whichever occurs later. Instead of requiring the part 
replacement, this proposed AD would require only a revision to the 
maintenance or inspection program, as applicable, to incorporate the 
new reduced life limits. The affected airplanes operated in the U.S. 
fleet are below the reduced life limit thresholds and will not reach 
those thresholds within 3 months after the effective date of this 
proposed AD. Therefore this proposed AD would require revising the 
maintenance or inspection program, as applicable, within 30 days after 
the effective date of this proposed AD. Requiring a revision to the 
maintenance or inspection program, as applicable, rather than requiring 
individual repetitive actions (such as repetitively replacing a part 
prior to a life limit), requires operators to record AD compliance only 
at the time the revision is made. Repetitive actions specified in the 
airworthiness limitations must be complied with in accordance with 
section 91.403(c) of the Federal Aviation Regulations (14 CRF 
91.403(c)).

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $72,335, or $85 per product.

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.

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-2015-0244; Directorate Identifier 2014-NM-
127-AD.

(a) Comments Due Date

    We must receive comments by April 20, 2015.

(b) Affected ADs

    Paragraph (g) of this AD terminates the life limit specified in 
paragraph (n)(1) of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, 
January 26, 2015), for airplanes having a main landing gear (MLG) 
upper cardan part number (P/N) 201163620.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a cracked upper cardan in the MLG. We 
are issuing this AD to prevent failure of the upper cardan in the 
MLG, which could result in MLG collapse and subsequent damage to the 
airplane and injury to occupants.

(f) Compliance

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

(g) Revision to Maintenance or Inspection Program

    For airplanes having a MLG upper cardan part number (P/N) 
201163620: Within 30 days after the effective date of this AD revise 
the maintenance or inspection program, as applicable, to incorporate 
the applicable life limits for the MLG upper cardan P/N 201163620 
specified in paragraphs (g)(1) through (g)(5) of this AD and the 
life limit clarifications specified in paragraph (h) of this AD. The 
initial compliance time for replacing the MLG upper cardan is prior 
to the applicable life limit specified in

[[Page 11966]]

paragraphs (g)(1) through (g)(5) of this AD, or within 30 days after 
the effective date of this AD, whichever occurs later. Accomplishing 
this revision terminates the life limit required by paragraph (n)(1) 
of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), 
for the MLG upper cardan P/N 201163620 for that airplane only.
    (1) For Airbus Model A319 series airplanes, pre-Airbus 
Modification 26644, excluding corporate jets post-Airbus 
Modification 28238, 28162, and 28342: The life limit is 50,590 total 
flight cycles.
    (2) For Airbus Model A319 series airplanes, post-Airbus 
Modification 26644, excluding corporate jets post-Airbus 
Modification 28238, 28162, and 28342: The life limit is 56,480 total 
flight cycles.
    (3) For Airbus Model A320 series airplanes pre-Airbus 
Modification 26644 having weight variant (WV) WV011, WV012, WV016, 
or WV018: The life limit is 50,590 total flight cycles.
    (4) For Airbus Model A320 series airplanes post-Airbus 
Modification 26644, having WV011, WV012, WV016, or WV018: The life 
limit is 56,480 total flight cycles.
    (5) For Airbus Model A320 series airplanes post-Airbus 
Modification 26644, having WV015 or WV017: The life limit is 42,140 
total flight cycles.

(h) Additional Life Limit Clarifications

    (1) The life limits specified in paragraphs (g)(1) through 
(g)(5) of this AD are total flight cycles accumulated by the MLG 
since first installation on an airplane.
    (2) The life limits specified in paragraphs (g)(1) through 
(g)(5) of this AD are applicable only for the airplane model, 
configuration and WV specified in those paragraphs.
    (3) If a part is transferred between airplanes having a 
different life limit for the MLG unit, adjust the life limit using 
the method specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe 
Life Airworthiness Limitation Items, Revision 02, dated May 13, 
2011, which is incorporated by reference in AD 2014-23-15, Amendment 
39-18031 (80 FR 3871, January 26, 2015).
    (4) An MLG unit on which Airbus Modification 26644 is installed 
is also known as ``enhanced'' landing gear and is identified as P/N 
201582xxx Leg and Dressing Series. An MLG unit that does not have 
Airbus Modification 26644 installed is identified as P/N 201375xxx 
Leg and Dressing Series. (The xxx designation is a placeholder for 
numbers).
    (5) For airplanes with configurations not specified in 
paragraphs (g)(1) through (g)(5) of this AD, the life limit for the 
MLG unit is specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe 
Life Airworthiness Limitation Items, Revision 02, dated May 13, 
2011, which is incorporated by reference in AD 2014-23-15, Amendment 
39-18031 (80 FR 3871, January 26, 2015).

(i) No Alternative Actions and Intervals

    After the maintenance or inspection program, as applicable, has 
been revised as required by paragraph (g) of this AD, no alternative 
actions (e.g., inspections) or intervals may be used unless the 
actions or intervals are approved as an alternative method of 
compliance (AMOC) in accordance with the procedures specified in 
paragraph (k)(1) of this AD.

(j) Parts Installation Limitation

    As of the effective date of this AD, a MLG upper cardan having 
P/N 201163620 may be installed on an airplane, provided the part 
life has not exceeded the applicable life limit specified in 
paragraphs (g)(1) through (g)(5) of this AD, and is replaced with a 
serviceable part prior to exceeding the applicable life limit 
specified in paragraphs (g)(1) through (g)(5) 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 Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. 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. The 
AMOC approval letter must specifically reference this AD.
    (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 
Branch, ANM-116, Transport Airplane Directorate, 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2014-
0141, dated June 4, 2014, 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-2015-0244.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on February 3, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02923 Filed 3-5-15; 4:15 pm]
 BILLING CODE 4910-13-P
Document Created: 2015-12-18 12:09:29
Document Modified: 2015-12-18 12:09:29
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 April 20, 2015.
Contact		Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation		80 FR 11964
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 11964 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 43 (March 5, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
