[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)]
[Rules and Regulations]
[Pages 4169-4172]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00952]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1991; Directorate Identifier 2014-NM-251-AD;
Amendment 39-18381; AD 2016-02-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, and -
115 airplanes; Model A320-214
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airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes.
This AD was prompted by reports of cracked cadmium-plated lock nuts
that attach the hinge to the fan cowl door. This AD requires inspecting
to determine the serial number of each engine fan cowl door, inspecting
for cracking of the hinge lock nuts of any affected door, and replacing
the lock nuts if necessary. We are issuing this AD to detect and
correct cracking of the hinge lock nuts, which could result in
separation of the hinge from the fan cowl door, in-flight loss of the
door, and consequent damage to the airplane.
DATES: This AD becomes effective March 1, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 1,
2016.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1991; 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 final rule, contact the
following:
For Airbus service information 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.
For Goodrich service information contact Goodrich Aerostructures,
850 Lagoon Drive, Chula Vista, California, 91910-2098; telephone: 619-
691-2719; email: [email protected]; Internet: http://www.goodrich.com/TechPubs.
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-
1991.
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 A318-111
and -112 airplanes; Model A319-111, -112, and -115 airplanes; Model
A320-214 airplanes; and Model A321-111, -112, -211, -212, and -213
airplanes. The NPRM published in the Federal Register on July 2, 2015
(80 FR 38036).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0276, dated December 19, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318-111 and -112 airplanes; Model A319-111, -112, and -115 airplanes;
Model A320-214 airplanes; and Model A321-111, 112, -211, -212, and -213
airplanes. The MCAI states:
In-service findings have been reported of cracked cadmium plated
lock nuts. This cracking occurs shortly after installation.
Investigation results attribute the cause to an improper
manufacturing procedure of the nuts. It was determined that the
affected batch of lock nuts was used on the fan cowl to attach
hinges to the cowl doors on CFM56-5B engines only.
This condition, if not corrected, could lead to separation of
the hinge from the fan cowl door, possibly resulting in in-flight
loss of a fan cowl door, with consequent damage to the aeroplane
and/or injury to persons on the ground.
For the reasons describes above, this [EASA] AD required
identification of the affected fan cowl doors, a one-time inspection
of the fan cowl door hinge nuts and, depending on findings,
replacement of the affected nuts.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1991-0003.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 38036, July 2,
2015) or on the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed, except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 38036, July 2, 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 38036, July 2, 2015).
Related Service Information under 1 CFR part 51
Airbus has issued Service Bulletin A320-71-1062, dated July 28,
2014. Goodrich Aerostructures has issued Service Bulletin RA32071-151,
dated June 11, 2014. The service information describes procedures for
inspection and replacement of the hinge nuts of the fan cowl door. This
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 437 airplanes of U.S. registry.
We also estimate that it takes about 2 work-hours 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 $74,290, or $170 per product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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
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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-2015-1991; 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:
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):
2016-02-02 Airbus: Amendment 39-18381. Docket No. FAA-2015-1991;
Directorate Identifier 2014-NM-251-AD.
(a) Effective Date
This AD becomes effective March 1, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this
AD, all manufacturer serial numbers.
(1) Airbus Model A318-111 and -112 airplanes.
(2) Airbus Model A319-111, -112, and -115 airplanes.
(3) Airbus Model A320-214 airplanes.
(4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of cracked cadmium-plated lock
nuts that attach the hinge to the fan cowl door. We are issuing this
AD to detect and correct cracking of the hinge lock nuts, which
could result in separation of the hinge from the fan cowl door, the
in-flight loss of the door, and consequent damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspect to Determine Serial Number
Within 24 months after the effective date of this AD: Inspect to
determine if any fan cowl door has a serial number 10029001 through
11092003 inclusive, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28,
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated
June 11, 2014. A review of airplane maintenance records is
acceptable in lieu of the inspection required by this paragraph,
provided those records can be relied upon for that purpose and the
serial number can be positively identified by that review.
(h) Inspection and Replacement
For any fan cowl door having any serial number identified in
paragraph (g) of this AD: Within 24 months after the effective date
of this AD, do a detailed inspection for cracking of the hinge lock
nuts of the door, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-71-1062, dated July 28, 2014; or
Goodrich Aerostructures Service Bulletin RA32071-151, dated June 11,
2014. If any crack is found, before further flight, replace each
cracked hinge lock nut, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28,
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated
June 11, 2014.
(i) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(j) 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.
(k) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2014-0276, dated December 19, 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-
1991-0003.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-71-1062, dated July 28, 2014.
(ii) Goodrich Aerostructures Service Bulletin RA32071-151, dated
June 11, 2014.
(3) For Airbus 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) For Goodrich service information identified in this AD,
contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista,
California, 91910-2098; telephone: 619-691-2719; email:
[email protected]; Internet: http://www.goodrich.com/TechPubs.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the
[[Page 4172]]
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 January 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-00952 Filed 1-25-16; 8:45 am]
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