Airworthiness Directives; Airbus Airplanes

[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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (80 FR 38036, July 2, 2015) for correcting the unsafe condition; 
and
    <bullet> 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]
 BILLING CODE 4910-13-P

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