81 FR 51142 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 149 (August 3, 2016)

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD was prompted by reports of cracks on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). This proposed AD would require repetitive inspections for cracking and corrosion of the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and corrective actions if necessary. We are proposing this AD to detect and correct such cracking and corrosion, which could lead to T/R malfunction and, in a case of rejected takeoff at V1 on a wet runway, a consequent runway excursion, possibly resulting in damage to the airplane and injury to occupants.

[Federal Register Volume 81, Number 149 (Wednesday, August 3, 2016)]
[Proposed Rules]
[Pages 51142-51144]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-18262]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8182; Directorate Identifier 2016-NM-069-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and 
Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD 
was prompted by reports of cracks on the 3 o'clock and 9 o'clock pivot 
fittings of a CFM56 engine's thrust reverser (T/R). This proposed AD 
would require repetitive inspections for cracking and corrosion of the 
3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and 
corrective actions if necessary. We are proposing this AD to detect and 
correct such cracking and corrosion, which could lead to T/R 
malfunction and, in a case of rejected takeoff at V1 on a wet runway, a 
consequent runway excursion, possibly resulting in damage to the 
airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by September 19, 
2016.

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 Airbus service information identified in this NPRM, 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 Aerostructures service information identified in this 
NPRM, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, 
CA 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.

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-2016-
8182; 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-2016-8182; 
Directorate Identifier 2016-NM-069-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 2016-0076, dated April 18, 2016 (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, -113, -114, and -115 
airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-
111, -112, v211, -212, and -213 airplanes. The MCAI states:

    Several operators reported finding cracks, during an unscheduled 
inspection, on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 
engine's thrust reverser (T/R). Investigation results revealed that 
these cracks were caused by a combination of stress and fatigue 
effects. Further analysis determined that only aeroplanes fitted 
with

[[Page 51143]]

CFM56-5A or CFM56-5B series engines could be affected by this issue.
    This condition, if not detected and corrected, could lead to T/R 
malfunction and, in a case of rejected take off at V1 on a wet 
runway, a consequent runway excursion, possibly resulting in damage 
to the aeroplane and injury to occupants.
    For the reasons described above, EASA issued AD 2016-0068, 
requiring repetitive inspections [for cracks and corrosion] of the 
T/R pivot fittings at the 3 o'clock and 9 o'clock positions and, 
depending on findings, accomplishment of applicable corrective 
action(s).
    Since that [EASA] AD was issued, it was determined that the list 
of part numbers (P/N) of affected T/R pivot fitting, as identified 
in that [EASA] AD, was incomplete.
    For the reason stated above, this [EASA] AD retains the 
requirements of EASA AD 2016-0068, which is superseded, but expands 
the list of affected fitting P/Ns.

Corrective actions include repair of cracking and corrosion.
    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-2016-
8182.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-70-1003, Revision 01, dated 
December 18, 2015. This service information describes procedures for 
doing inspections for cracking and corrosion of the 3 o'clock and 9 
o'clock pivot fittings of a CFM56 engine's T/R.
    Goodrich Aerostructures has issued Service Bulletin RA32078-137, 
Rev. 3, dated March 14, 2016. This service information describes 
procedures for doing inspections for cracking and corrosion of the 3 
o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and 
repair of corrosion.
    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 400 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  4 work-hours x $85 per               $0   $340 per            $136,000 per
                                  hour = $340 per                           inspection cycle.   inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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.

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-2016-8182; Directorate Identifier 2016-NM-
069-AD.

(a) Comments Due Date

    We must receive comments by September 19, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(4) of this AD, 
all manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Airbus Model A320-211, -212, and -214 airplanes.
    (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.

[[Page 51144]]

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
exhaust.

(e) Reason

    This AD was prompted by reports of cracks on the 3 o'clock and 9 
o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). We 
are issuing this AD to detect and correct such cracking and 
corrosion, which could lead to T/R malfunction and, in a case of 
rejected takeoff at V1 on a wet runway, a consequent runway 
excursion, possibly resulting in damage to the airplane and injury 
to occupants.

(f) Compliance

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

(g) Inspections and Corrective Actions

    At the applicable compliance time specified in paragraph (h) of 
this AD: Do a high frequency eddy current (HFEC) inspection for 
cracking and corrosion of each T/R pivot fitting specified in 
paragraphs (g)(1) and (g)(2) of this AD, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, 
dated December 18, 2015; and Goodrich Aerostructures Service 
Bulletin RA32078-137, Rev. 3, dated March 14, 2016; as applicable; 
except as required by paragraph (i) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
the T/R pivot fittings thereafter at intervals not to exceed 60 
months or 12,000 flight cycles, whichever occurs first.
    (1) The 3 o'clock position T/R pivot fittings having part 
numbers (P/N) that are provided in paragraphs (g)(1)(i) through 
(g)(1)(iv) of this AD.
    (i) P/N 321-200-850-6.
    (ii) P/N 321-200-851-6.
    (iii) P/N 321-200-852-6.
    (iv) P/N 321-200-853-6.
    (2) The 9 o'clock position T/R pivot fittings having P/Ns that 
are provided in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
    (i) P/N 321-200-800-6.
    (ii) P/N 321-200-801-6.
    (iii) P/N 321-200-802-6.
    (iv) P/N 321-200-803-6.

(h) Compliance Times

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, do the initial inspection specified in paragraph 
(g) of this AD. If maintenance records cannot conclusively determine 
the T/R flight cycles accumulated since first installation, or the 
time since new, do the initial inspection required by paragraph (g) 
of this AD at the compliance time specified in paragraph (h)(2) of 
this AD.
    (1) Before exceeding 10 years or 24,000 total flight cycles 
accumulated by the T/R, whichever occurs first since first 
installation on an airplane.
    (2) Within 36 months or 7,200 flight cycles, whichever occurs 
first after the effective date of this AD.

(i) Exceptions to Service Information Specification

    (1) If any crack is found during any inspection required by this 
AD: Before further flight, repair 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).
    (2) If any corrosion is found during any inspection required by 
this AD and Goodrich Aerostructures Service Bulletin RA32078-137, 
Rev. 3, dated March 14, 2016, specifies obtaining a damage 
disposition from Goodrich Aerostructures: Before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA; or 
Airbus's EASA DOA.

(j) Parts Installation Limitation

    As of the effective date of this AD, no person may install on 
any airplane a T/R pivot fitting having a part number specified in 
paragraph (g)(1) or (g)(2) of this AD, unless it is determined, 
prior to installation, that the T/R pivot fitting has accumulated 
less than 10 years and fewer than 24,000 total flight cycles since 
its first installation on an airplane, or less than 60 months and 
fewer than 12,000 flight cycles after having passed an inspection in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-70-1003, Revision 01, dated December 18, 2015; and 
Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated 
March 14, 2016.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-70-
1003, dated May 7, 2014.
    (2) This paragraph provides credit for actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(2)(i), or (k)(2)(ii), or (k)(2)(iii) of this AD.
    (i) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; and 
Goodrich Aerostructures Service Bulletin RA32078-137, dated April 
29, 2014.
    (ii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; 
and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 1, 
dated January 26, 2015.
    (iii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; 
and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 2, 
dated December 2, 2015.

(l) 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) of this AD: 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0076, dated April 18, 2016, 
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-2016-8182.
    (2) 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.
    (3) For Goodrich Aerostructures service information identified 
in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone 619-691-2719; email 
[email protected]; Internet http://www.goodrich.com/TechPubs.
    (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.

    Issued in Renton, Washington, on July 25, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18262 Filed 8-2-16; 8:45 am]
BILLING CODE 4910-13-P