[Federal Register Volume 81, Number 186 (Monday, September 26, 2016)]
[Proposed Rules]
[Pages 65980-65983]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21703]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / 
Proposed Rules  

[[Page 65980]]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9074; Directorate Identifier 2016-NM-097-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 A318-111 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 engine fan cowl door (FCD) losses on 
airplanes equipped with CFM56 engines due to operator failure to close 
the FCD during ground operations. This proposed AD would require 
modification and re-identification of certain FCDs or replacement of 
certain FCDs. This proposed AD would also require installation of a 
placard. We are proposing this AD to prevent in-flight loss of an 
engine FCD and possible consequent damage to the airplane.

DATES: We must receive comments on this proposed AD by November 10, 
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 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. 
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-
9074; 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-2016-9074; 
Directorate Identifier 2016-NM-097-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, 2016-0069, dated April 11, 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, -211, -212, and -213 airplanes. The MCAI states:

    Fan Cowl Door (FCD) losses were reported on aeroplanes equipped 
with CFM56 engines.
    Investigations confirmed that in all cases the fan cowls were 
opened prior to the flight and were not correctly re-secured. During 
the pre-flight inspection, it was then not detected that the FCD 
were not properly latched.
    This condition, if not detected and corrected, could lead to in-
flight loss of a FCD, possibly resulting in damage to the aeroplane 
and/or injury to persons on the ground.
    Prompted by these events, new FCD front latch and keeper 
assembly were developed, having a specific key necessary to un-latch 
the FCD. This key cannot be removed unless the FCD front latch is 
safely closed. The key, after removal, must be stowed in the flight 
deck at a specific location, as instructed in the applicable 
Aircraft Maintenance Manual. Applicable Flight Crew Operating Manual 
has been amended accordingly. After modification, the FCD is 
identified with a different Part Number (P/N).
    For the reasons described above, this [EASA] AD requires 
modification and re-identification of FCD [or replacement of the 
FCD].

    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-
9074.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A320-71-1068, Revision 01, 
dated April 28, 2016. This service information describes procedures for 
modifying the left-hand and right-hand FCDs on engines 1 and 2; 
installing a placard;

[[Page 65981]]

and re-identifying both the left-hand and right-hand FCDs with the new 
part number. 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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The parts installation prohibition specified in paragraph (5) of 
the MCAI depends on the configuration of the airplane. However, 
paragraph (k) of this proposed AD prohibits installing certain parts 
for all airplanes as of the effective date of this proposed AD.

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 per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification    Up to 7 work-hours x             $4,865           $5,460       $2,184,000
 of (or replacement of) FCD, and       $85 per hour = $595.
 Installation of Placard.
----------------------------------------------------------------------------------------------------------------

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(h), 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-2016-9074; Directorate Identifier 2016-NM-
097-AD.

(a) Comments Due Date

    We must receive comments by November 10, 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.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports of engine fan cowl door (FCD) 
losses on airplanes equipped with CFM56 engines due to operator 
failure to close the FCD during ground operations. We are issuing 
this AD to prevent in-flight loss of an engine FCD and possible 
consequent damage to the airplane.

(f) Compliance

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

(g) Modification of Affected Fan Cowl Doors and Placard Installation

    Within 35 months after the effective date of this AD, accomplish 
concurrently the actions in paragraphs (g)(1), (g)(2) and (g)(3) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-71-1068, Revision 01, dated April 28, 
2016.
    (1) Modify the left-hand and right-hand FCDs on engines 1 and 2.
    (2) Install a placard on the box located at the bottom of the 
120 volt unit (120 VU) panel, or at the bottom of the coat stowage, 
as applicable to airplane configuration.
    (3) Re-identify both the left-hand and right-hand FCDs with the 
new part number, as applicable, as specified in table 1 to 
paragraphs (g), (h), (i), and (k) of this AD.

[[Page 65982]]



 Table 1 to Paragraphs (g), (h), (i), and (k) of This AD--Fan Cowl Door
                        Part Number (P/N) Change
------------------------------------------------------------------------
           Door position                 Old P/N            New P/N
------------------------------------------------------------------------
Left-hand Side--CFM56-5A..........       238-0301-501       238M0301-501
                                         238-0301-503       238M0301-503
                                         238-0301-505       238M0301-505
                                         238-0301-507       238M0301-507
                                         238-0301-511       238M0301-511
                                         238-0301-513       238M0301-513
                                         238-0301-515       238M0301-515
                                         238-0301-517       238M0301-517
                                         238-0301-519       238M0301-519
                                         238-0301-521       238M0301-521
                                         238-0301-523       238M0301-523
                                         238-0301-525       238M0301-525
                                         238-0301-527       238M0301-527
                                         238-0301-529       238-0301-533
                                         238-0301-531       238-0301-535
Right-hand Side--CFM56-5A.........       238-0302-501       238M0302-501
                                         238-0302-503       238M0302-503
                                         238-0302-505       238M0302-505
                                         238-0302-509       238M0302-509
                                         238-0302-511       238M0302-511
                                         238-0302-513       238M0302-513
                                         238-0302-515       238M0302-515
                                         238-0302-517       238M0302-517
                                         238-0302-519       238M0302-519
                                         238-0302-521       238M0302-521
                                         238-0302-523       238M0302-523
                                         238-0302-525       238M0302-525
                                         238-0302-527       238M0302-527
                                         238-0302-529       238M0302-529
                                         238-0302-531       238M0302-531
                                         238-0302-533       238M0302-533
                                         238-0302-535       238M0302-535
                                         238-0302-537       238M0302-537
                                         238-0302-539       238-0302-547
                                         238-0302-541       238-0302-549
                                         238-0302-543       238-0302-551
                                         238-0302-545       238-0302-553
Left-hand Side--CFM56-5B..........       642-3001-503       642M3001-503
                                         642-3001-505       642M3001-505
                                         642-3001-507       642-3001-511
                                         642-3001-509       642-3001-513
Right-hand Side--CFM56-5B.........       642-3002-503       642M3002-503
                                         642-3002-505       642M3002-505
                                         642-3002-507       642M3002-507
                                         642-3002-509       642M3002-509
                                         642-3002-511       642-3002-519
                                         642-3002-513       642-3002-521
                                         642-3002-515       642-3002-523
                                         642-3002-517       642-3002-525
------------------------------------------------------------------------

(h) Replacement of Affected Fan Cowl Door With New Door Design

    Replacing the FCDs, having a part number listed as ``Old P/N'' 
in table 1 to paragraphs (g), (h), (i), and (k) of this AD, with the 
FCDs having the corresponding part number listed as ``New P/N'' in 
table 1 to paragraphs (g), (h), (i), and (k) of this AD, is equal to 
compliance with paragraphs (g)(1) and (g)(3) of this AD. The 
replacement must be done in accordance with instructions approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA), or 
approved under Airbus's EASA Design Organization Approval (DOA).

(i) Compliance Information for Airplanes on Which Airbus Modification 
157517 Is Embodied

    An airplane on which Airbus modification 157517 has been 
embodied in production, is compliant with the requirements of 
paragraphs (g)(1) and (g)(3) of this AD, provided it is determined 
that no FCD, having a part number identified as ``Old P/N'' in table 
1 to paragraphs (g), (h), (i), and (k) of this AD, are installed on 
that airplane at the effective date of the AD.

(j) Compliance Information for Airplanes on Which Airbus Modification 
157519 or Modification 157521 is Embodied

    An airplane on which Airbus modification 157519 or modification 
157521 has been embodied in production is compliant with the 
requirements of paragraph (g)(2) of this AD.

(k) Parts Installation Prohibition

    As of the effective date of this AD, do not install on any 
airplane an FCD part number identified as ``Old P/N'' in table 1 to 
paragraphs (g), (h), (i), and (k) of this AD.

(l) Installation of Approved Parts

    Installation on an airplane of right-hand and left-hand FCD, 
having a part number approved after the effective date of this AD, 
is equal to compliance with the requirements of paragraphs (g)(1) 
and (g)(3) of this AD for that airplane only, provided the 
conditions specified in paragraphs (l)(1) and (l)(2) of this AD are 
met.
    (1) The part number must be approved by the Manager, 
International Branch, ANM-

[[Page 65983]]

116, Transport Airplane Directorate, FAA; or EASA, or approved under 
Airbus's EASA DOA.
    (2) The FCD installation must be accomplished in accordance with 
airplane modification instructions approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or approved under Airbus's EASA DOA.

(m) Credit for Previous Actions

    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 A320-71-1068, dated 
December 18, 2015, which is not incorporated by reference in this 
AD.

(n) 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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0069, dated April 11, 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-2016-9074.
    (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 August 31, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21703 Filed 9-23-16; 8:45 am]
 BILLING CODE 4910-13-P