80 FR 68434 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 214 (November 5, 2015)

Page Range		68434-68437
FR Document		2015-27925
We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by a cracked upper cardan in the main landing gear (MLG). This AD requires revising the maintenance or inspection program, as applicable, to reduce the life limits for the MLG upper cardan for certain installations. 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.
Federal Register, Volume 80 Issue 214 (Thursday, November 5, 2015)
[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68434-68437]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-27925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0244; Directorate Identifier 2014-NM-127-AD; 
Amendment 39-18313; AD 2015-22-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318, A319, and A320 series airplanes. This AD was 
prompted by a cracked upper cardan in the main landing gear (MLG). This 
AD requires revising the maintenance or inspection program, as 
applicable, to reduce the life limits for the MLG upper cardan for 
certain installations. 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.

DATES: This AD becomes effective December 10, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 10, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0244; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0244.

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: 

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 A318, 
A319, and A320 series airplanes. The NPRM published in the Federal 
Register on March 5, 2015 (80 FR 11964).
    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 
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/#!documentDetail;D=FAA-2015-0244-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 11964, March 5, 2015) and the FAA's response to each comment.

Request To Extend the Compliance Time

    Delta Airlines (DAL) requested that paragraph (g) of the proposed 
AD (80 FR

[[Page 68435]]

11964, March 5, 2015) be revised so the initial compliance time for 
replacing the MLG upper cardan is extended and corresponds to that of 
European Aviation Safety Agency (EASA) AD 2014-0141, dated June 4, 
2014. EASA AD 2014-0141 specifies an initial compliance time of 
``within 3 months'' after the effective date of that EASA AD and the 
proposed AD specified an initial compliance time of prior to the 
applicable life limit specified in paragraphs (g)(1) through (g)(5), or 
within 30 days after the effective date of the AD, whichever occurs 
later.
    We agree with the commenter's request. In consideration of the 
average utilization rate of affected U.S. operators, the practical 
aspects of an orderly modification of the U.S. fleet during regular 
maintenance periods, and the availability of required modification 
parts, we have determined that a 3 month initial compliance time is 
appropriate for replacing the MLG upper cardan. We have changed 
paragraph (g) of this AD accordingly.

Request To Reference Next Higher Part Number Assembly

    Lufthansa Technik requested that the part number for the next 
higher assembly of MLG cardan part number (P/N) 201163620 be referenced 
in the NPRM (80 FR 11964, March 5, 2015). The commenter stated that the 
NPRM and corresponding EASA AD 2014-0141, dated June 4, 2014, reference 
P/N 201163620, but that part number is not identified in the aircraft 
illustrated parts catalog (AIPC). The commenter is concerned that if 
operators only look in the AIPC to see if P/N 201163620 is identified, 
and it is not there, they may falsely think that their airplanes would 
not be affected by the NPRM.
    We do not agree with the commenter's request. Although MLG cardan 
P/N 201163620 is not included in the AIPC, it is identified in Airbus 
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation 
Items, which is part of the approved type design for these airplanes. 
Therefore, we have not changed this AD in this regard.

Clarification of Parts Installation Limitation

    In paragraph (j) of the proposed AD (NPRM (80 FR 11964, March 5, 
2015), we referred to applicable life limits in paragraphs (g)(1) 
through (g)(5) of the proposed AD. For airplanes other than those 
identified paragraphs (g)(1) through (g)(5) of the proposed AD, the 
life limit is in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation, Revision 02, dated May 13, 2011, as specified 
in paragraph (h)(5) of this AD. In addition, if a part is transferred 
between airplanes, operators must adjust the life limit using the 
method specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation, Revision 02, dated May 13, 2011, as specified 
in paragraph (h)(3) of this AD. We have clarified paragraph (j) of this 
AD by also referring to paragraphs (h)(3) and (h)(5) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 11964, March 5, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 11964, March 5, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this 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 and life limits for 
airworthiness limitations items. 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 of this AD.

Costs of Compliance

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

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:

[[Page 68436]]

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):

2015-22-08 Airbus: Amendment 39-18313. Docket No. FAA-2015-0244; 
Directorate Identifier 2014-NM-127-AD.

(a) Effective Date

    This AD becomes effective December 10, 2015.

(b) Affected ADs

    For airplanes with configurations specified in paragraphs (g)(1) 
through (g)(5) of this AD: 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 main 
landing gear (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 paragraphs (g)(1) 
through (g)(5) of this AD, or within 3 months 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.

    Note 1 to paragraphs (h)(3) and (h)(5) of this AD: Airbus A318/
A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, 
Revision 02, dated May 13, 2011, is already required by paragraph 
(n) of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 
2015).

    (4) A 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. A 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.

(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, paragraph (h)(3) of 
this AD, and paragraph (h)(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, paragraph 
(h)(3) of this AD, and paragraph (h)(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

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA 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/#!documentDetail;D=FAA-2015-
0244.

(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 A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items,

[[Page 68437]]

Revision 02, dated May 13, 2011. The revision level of this document 
is identified on only the title page and in the Record of Revisions. 
The revision date is not identified on the title page of this 
document.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (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 Renton, Washington, on October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27925 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68435

11964, March 5, 2015) be revised so the paragraph (h)(5) of this AD. In addition, detail the scope of the Agency’s
initial compliance time for replacing the if a part is transferred between authority.
MLG upper cardan is extended and airplanes, operators must adjust the life We are issuing this rulemaking under
corresponds to that of European limit using the method specified in the authority described in ‘‘Subtitle VII,
Aviation Safety Agency (EASA) AD Airbus A318/A319/A320/A321 ALS Part A, Subpart III, Section 44701:
2014–0141, dated June 4, 2014. EASA Part 1—Safe Life Airworthiness General requirements.’’ Under that
AD 2014–0141 specifies an initial Limitation, Revision 02, dated May 13, section, Congress charges the FAA with
compliance time of ‘‘within 3 months’’ 2011, as specified in paragraph (h)(3) of promoting safe flight of civil aircraft in
after the effective date of that EASA AD this AD. We have clarified paragraph (j) air commerce by prescribing regulations
and the proposed AD specified an initial of this AD by also referring to for practices, methods, and procedures
compliance time of prior to the paragraphs (h)(3) and (h)(5) of this AD. the Administrator finds necessary for
applicable life limit specified in safety in air commerce. This regulation
paragraphs (g)(1) through (g)(5), or Conclusion
is within the scope of that authority
within 30 days after the effective date of We reviewed the relevant data, because it addresses an unsafe condition
the AD, whichever occurs later. considered the comments received, and that is likely to exist or develop on
We agree with the commenter’s determined that air safety and the products identified in this rulemaking
request. In consideration of the average public interest require adopting this AD action.
utilization rate of affected U.S. with the changes described previously
operators, the practical aspects of an Regulatory Findings
and minor editorial changes. We have
orderly modification of the U.S. fleet determined that these minor changes: We determined that this AD will not
during regular maintenance periods, • Are consistent with the intent that have federalism implications under
and the availability of required was proposed in the NPRM (80 FR Executive Order 13132. This AD will
modification parts, we have determined 11964, March 5, 2015) for correcting the not have a substantial direct effect on
that a 3 month initial compliance time unsafe condition; and the States, on the relationship between
is appropriate for replacing the MLG • Do not add any additional burden the national government and the States,
upper cardan. We have changed or on the distribution of power and
upon the public than was already
paragraph (g) of this AD accordingly. responsibilities among the various
proposed in the NPRM (80 FR 11964,
Request To Reference Next Higher Part March 5, 2015). levels of government.
Number Assembly We also determined that these For the reasons discussed above, I
changes will not increase the economic certify that this AD:
Lufthansa Technik requested that the 1. Is not a ‘‘significant regulatory
part number for the next higher burden on any operator or increase the
action’’ under Executive Order 12866;
assembly of MLG cardan part number scope of this AD.
2. Is not a ‘‘significant rule’’ under the
(P/N) 201163620 be referenced in the Related Service Information Under 1 DOT Regulatory Policies and Procedures
NPRM (80 FR 11964, March 5, 2015). CFR Part 51 (44 FR 11034, February 26, 1979);
The commenter stated that the NPRM 3. Will not affect intrastate aviation in
and corresponding EASA AD 2014– Airbus has issued A318/A319/A320/
Alaska; and
0141, dated June 4, 2014, reference P/N A321 ALS Part 1—Safe Life 4. Will not have a significant
201163620, but that part number is not Airworthiness Limitation Items, economic impact, positive or negative,
identified in the aircraft illustrated parts Revision 02, dated May 13, 2011. This on a substantial number of small entities
catalog (AIPC). The commenter is document provides revised instructions under the criteria of the Regulatory
concerned that if operators only look in and life limits for airworthiness Flexibility Act.
the AIPC to see if P/N 201163620 is limitations items. This service
identified, and it is not there, they may information is reasonably available Examining the AD Docket
falsely think that their airplanes would because the interested parties have You may examine the AD docket on
not be affected by the NPRM. access to it through their normal course the Internet at http://
We do not agree with the commenter’s of business or by the means identified www.regulations.gov/
request. Although MLG cardan P/N in the ADDRESSES section of this AD. #!docketDetail;D=FAA-2015-0244; or in
201163620 is not included in the AIPC, Costs of Compliance person at the Docket Management
it is identified in Airbus A318/A319/ Facility between 9 a.m. and 5 p.m.,
A320/A321 ALS Part 1—Safe Life We estimate that this AD affects 851 Monday through Friday, except Federal
Airworthiness Limitation Items, which airplanes of U.S. registry. holidays. The AD docket contains this
is part of the approved type design for We also estimate that it will take AD, the regulatory evaluation, any
these airplanes. Therefore, we have not about 1 work-hour per product to comments received, and other
changed this AD in this regard. comply with the basic requirements of information. The street address for the
this AD. The average labor rate is $85 Docket Operations office (telephone
Clarification of Parts Installation per work-hour. Required parts will cost
Limitation 800–647–5527) is in the ADDRESSES
about $0 per product. Based on these section.
In paragraph (j) of the proposed AD figures, we estimate the cost of this AD
(NPRM (80 FR 11964, March 5, 2015), on U.S. operators to be $72,335, or $85 List of Subjects in 14 CFR Part 39
we referred to applicable life limits in per product. Air transportation, Aircraft, Aviation
paragraphs (g)(1) through (g)(5) of the safety, Incorporation by reference,
Authority for This Rulemaking
jstallworth on DSK7TPTVN1PROD with RULES

proposed AD. For airplanes other than Safety.
those identified paragraphs (g)(1) Title 49 of the United States Code
through (g)(5) of the proposed AD, the specifies the FAA’s authority to issue Adoption of the Amendment
life limit is in Airbus A318/A319/A320/ rules on aviation safety. Subtitle I, Accordingly, under the authority
A321 ALS Part 1—Safe Life section 106, describes the authority of delegated to me by the Administrator,
Airworthiness Limitation, Revision 02, the FAA Administrator. ‘‘Subtitle VII: the FAA amends 14 CFR part 39 as
dated May 13, 2011, as specified in Aviation Programs,’’ describes in more follows:

VerDate Sep<11>2014 14:34 Nov 04, 2015 Jkt 238001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\05NOR1.SGM 05NOR1
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68437

Revision 02, dated May 13, 2011. The consequent loss of control of the inspections, at various locations in
revision level of this document is identified airplane. certain stringers of the lower lobe cargo
on only the title page and in the Record of compartments. The NPRM proposed to
Revisions. The revision date is not identified DATES: This AD is effective December
10, 2015. require drilling a hole and installing and
on the title page of this document.
(ii) Reserved. The Director of the Federal Register bonding plugs in certain stringers of the
(3) For service information identified in approved the incorporation by reference lower lobe cargo compartments. We are
this AD, contact Airbus, Airworthiness of a certain publication listed in this AD issuing this AD to detect and correct
Office—EIAS, 1 Rond Point Maurice as of December 10, 2015. missing or misaligned plugs which, in
Bellonte, 31707 Blagnac Cedex, France; ADDRESSES: For service information the event of a fire, could cause an
telephone +33 5 61 93 36 96; fax +33 5 61 identified in this AD, contact Boeing increased rate of loss of Halon in the
93 44 51; email account.airworth-eas@ lower cargo compartments, and result in
airbus.com; Internet http://www.airbus.com.
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707, the inability to extinguish a fire and
(4) You may view this service information consequent loss of control of the
at the FAA, Transport Airplane Directorate, MC 2H–65, Seattle, WA 98124–2207;
1601 Lind Avenue SW., Renton, WA. For telephone 206–544–5000, extension 1; airplane.
information on the availability of this fax 206–766–5680; Internet https:// Comments
material at the FAA, call 425–227–1221. www.myboeingfleet.com. You may view
(5) You may view this service information this referenced service information at We gave the public the opportunity to
that is incorporated by reference at the the FAA, Transport Airplane participate in developing this AD. The
National Archives and Records Directorate, 1601 Lind Avenue SW., following presents the comments
Administration (NARA). For information on Renton, WA. For information on the received on the NPRM (79 FR 56682,
the availability of this material at NARA, call September 23, 2014) and the FAA’s
202–741–6030, or go to: http://
availability of this material at the FAA,
call 425–227–1221. It is also available response to each comment.
www.archives.gov/federal-register/cfr/ibr-
locations.html. on the Internet at http:// Supportive Comment
www.regulations.gov by searching for
Issued in Renton, Washington, on October United Airlines stated that it concurs
and locating Docket No. FAA–2014–
22, 2015. with the NPRM (79 FR 56682,
0649.
Jeffrey E. Duven, September 23, 2014), and agrees that the
Manager, Transport Airplane Directorate, Examining the AD Docket detection and correction of the missing
Aircraft Certification Service. You may examine the AD docket on or misaligned plugs will maintain a
[FR Doc. 2015–27925 Filed 11–4–15; 8:45 am] the Internet at http:// higher level of safety.
BILLING CODE 4910–13–P www.regulations.gov by searching for Request To Delay Issuance of the NPRM
and locating Docket No. FAA–2014– (79 FR 56682, September 23, 2014)
0649; or in person at the Docket
DEPARTMENT OF TRANSPORTATION All Nippon Airways (ANA) asked that
Management Facility between 9 a.m.
we delay issuance of the NPRM (79 FR
and 5 p.m., Monday through Friday,
Federal Aviation Administration 56682, September 23, 2014) until Boeing
except Federal holidays. The AD docket
Alert Service Bulletin B787–81205–
contains this AD, the regulatory
14 CFR Part 39 SB530024–00, Issue 001, dated May 15,
evaluation, any comments received, and
2014 (referred to as the appropriate
[Docket No. FAA–2014–0649; Directorate other information. The address for the
source of service information for
Identifier 2014–NM–132–AD; Amendment Docket Office (phone: 800–647–5527) is
accomplishing the specified actions),
39–18314; AD 2015–22–09] Docket Management Facility, U.S.
can be revised. ANA noted that the
Department of Transportation, Docket
service information specifies using a
RIN 2120–AA64 Operations, M–30, West Building
stringer plug removal/installation tool,
Ground Floor, Room W12–140, 1200
Airworthiness Directives; The Boeing having tool number (T/N)
New Jersey Avenue SE., Washington,
Company Airplanes MIT140Z4372–3; however, this tool
DC 20590.
does not work well for doing the
AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT: actions. ANA provided the following
Administration (FAA), DOT. Francis Smith, Aerospace Engineer, reasons to substantiate its request:
ACTION: Final rule.
Cabin Safety and Environmental • For the instructions specified in
Systems Branch, ANM–150S, FAA, Task 1 of this service information, the
SUMMARY: We are adopting a new Seattle Aircraft Certification Office, connecting tube on the tool (T/N
airworthiness directive (AD) for certain 1601 Lind Avenue SW., Renton, WA 140Z4372–8/–15) interferes with the
The Boeing Company Model 787–8 98057–3356; phone: 425–917–6596; fax: fasteners at the section 41/43 joint;
airplanes. This AD was prompted by 425–917–6590; email: francis.smith@ therefore, the tool cannot be inserted
reports of missing plugs found prior to faa.gov. into the stringers. The connecting tube
airplane delivery, during manufacturing SUPPLEMENTARY INFORMATION: needs to be shortened in length and
inspections, at various locations in trimmed to taper.
certain stringers of the lower lobe cargo Discussion • For the instructions specified in
compartments. This AD requires drilling We issued a notice of proposed Task 3 of the service information, the
a hole and installing and bonding plugs rulemaking (NPRM) to amend 14 CFR tool (T/N 140Z4372–3) cannot be
in certain stringers of the lower lobe part 39 by adding an AD that would inserted at stringers 30R through 35R,
jstallworth on DSK7TPTVN1PROD with RULES

cargo compartments. We are issuing this apply to certain The Boeing Company adjacent to the cargo door, because it
AD to detect and correct missing or Model 787–8 airplanes. The NPRM won’t bend at the location adjacent to
misaligned plugs which, in the event of published in the Federal Register on the stringer end and frame.
a fire, could cause an increased rate of September 23, 2014 (79 FR 56682). The • For the instructions specified in
loss of Halon in the lower cargo NPRM was prompted by reports of Task 3 of the service information, the
compartments, and result in the missing plugs found prior to airplane tool (T/N 140Z4372–3) is inserted into
inability to extinguish a fire and delivery, during manufacturing the stringer from station (STA) 1593 to

VerDate Sep<11>2014 14:34 Nov 04, 2015 Jkt 238001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\05NOR1.SGM 05NOR1
Document Created: 2015-12-14 15:03:55
Document Modified: 2015-12-14 15:03:55
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		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective December 10, 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 68434
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 68434 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 214 (November 5, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
