Document ID: FAA-2016-8185-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-08-05T04:00Z

[Federal Register Volume 81, Number 151 (Friday, August 5, 2016)]
[Proposed Rules]
[Pages 51813-51815]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18492]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8185; Directorate Identifier 2016-NM-050-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-18-
06, for certain Airbus Model A319-131 and -132 airplanes; Model A320-
231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. 
AD 2003-18-06 currently requires installing new anti-swivel plates and 
weights on the engine fan cowl door (FCD) latches and a new cowl door 
hold-open device. Since we issued AD 2003-18-06, we have received 
reports of additional engine FCD in-flight losses, and a new FCD front 
latch and keeper assembly has been developed to address this unsafe 
condition. This proposed AD would retain the current actions and 
require modifying the engine FCDs, installing placards, and re-
identifying the FCDs with the new part numbers. This proposed AD would 
also revise the applicability to include all Model A319-131 and -132 
airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 
and -231 airplanes. We are proposing this AD to prevent in-flight loss 
of an engine FCD and possible consequent damage to the airplane and 
hazards to persons or property on the ground.

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

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, 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 account.airworth-eas@airbus.com; 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-
8185; 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-2016-8185; 
Directorate Identifier 2016-NM-050-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

    On August 29, 2003, we issued AD 2003-18-06, Amendment 39-13297 (68 
FR 53501, September 11, 2003) (``AD 2003-18-06''). AD 2003-18-06 
requires actions intended to address an unsafe condition on certain 
Airbus Model A319-131 and -132 airplanes; Model A320-231, -232, and -
233 airplanes; and Model A321-131 and -231 airplanes.
    Since we issued AD 2003-18-06, we have received reports of 
additional engine FCD in-flight losses, and a new FCD front latch and 
keeper assembly has been developed to address this unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0053, dated March 14, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 
airplanes. The MCAI states:

    Fan Cowl Door (FCD) losses during take-off were reported on 
aeroplanes equipped with IAE V2500 engines. Prompted by these 
occurences, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
DGAC France issued AD 2000-444-156(B), mandating FCD latch 
improvements. This [DGAC] AD was later superseded by AD 2001-381(B) 
[which corresponds to FAA AD 2003-18-06], requiring installation of 
additional fan cowl latch improvement by installing a hold open 
device.
    Since that [DGAC] AD was issued, further FCD in flight losses 
were experienced in service. Investigations confirmed that in all

[[Page 51814]]

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 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 recent 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 retains the 
requirements of DGAC AD 2001-381(B), which is superseded, and 
requires modification and re-identification of 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-
8185.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1069, dated December 18, 
2015. The service information describes procedures for modifying the 
engine FCDs, installing placards, and re-identifying the FCDs with the 
new part numbers. 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 558 airplanes of U.S. 
registry.
    The actions required by AD 2003-18-06, and retained in this 
proposed AD, take about 8 work-hours per product, at an average labor 
rate of $85 per work-hour. Required parts cost about $1,500 per 
product. Based on these figures, the estimated cost of the actions that 
are required by AD 2003-18-06 is $2,180 per product.
    We also estimate that it would take about 6 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $4,813 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $2,970,234, or $5,323 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 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 removing Airworthiness Directive (AD) 
2003-18-06, Amendment 39-13297 (68 FR 53501, September 11, 2003), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-8185; Directorate Identifier 2016-NM-
050-AD.

(a) Comments Due Date

    We must receive comments by September 19, 2016.

(b) Affected ADs

    This AD replaces AD 2003-18-06, Amendment 39-13297 (68 FR 53501, 
September 11, 2003) (``AD 2003-18-06'').

(c) Applicability

    This AD applies to Airbus Model A319-131 and -132 airplanes; 
Model A320-231, -232, and -233 airplanes; and Model A321-131 and -
231 airplanes; certificated in any category; all manufacturer serial 
numbers.

(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) 
in-flight losses. We are issuing this AD to prevent in-flight loss 
of an engine FCD and possible consequent damage to the airplane and 
hazards to persons or property on the ground.

(f) Compliance

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

(g) Retained Modification and/or Installation, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
2003-18-06, with no changes. Within 18 months after October 16, 2003 
(the effective date of AD 2003-18-06), do the action(s) specified in 
paragraph (g)(1) or (g)(2) of this AD, as applicable.
    (1) For Configuration 01 airplanes identified in Airbus Service 
Bulletin A320-71-1028, dated March 23, 2001: Modify the door latches 
of the fan cowl of both engines (i.e., installation of new anti-
swivel plates and weights), and install a new hold-open

[[Page 51815]]

device, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-71-1028, dated March 23, 2001.
    (2) For Configuration 02 airplanes identified in Airbus Service 
Bulletin A320-71-1028, dated March 23, 2001: Install a new hold-open 
device, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-71-1028, dated March 23, 2001.

(h) New Modifications

    Within 36 months after the effective date of this AD, do the 
actions required by paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-71-1069, dated December 18, 2015.
    (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 VU panel or at the bottom of the coat stowage, as applicable.
    (3) Re-identify both engine FCDs with the new part numbers (P/
Ns), as specified in table 1 to paragraph (h) of this AD and table 2 
to paragraph (h) of this AD, as applicable.

           Table 1 to Paragraph (h) of This AD--Left-Side Door
------------------------------------------------------------------------
                     Old part No.                         New part No.
------------------------------------------------------------------------
740-4000-501.........................................      740-4000-9501
740-4000-503.........................................      740-4000-9503
745-4000-501.........................................       745-4000-513
745-4000-503.........................................       745-4000-515
745-4000-505.........................................       745-4000-517
------------------------------------------------------------------------

          Table 2 to Paragraph (h) of This AD--Right-Side Door
------------------------------------------------------------------------
                     Old part No.                         New part No.
------------------------------------------------------------------------
740-4000-502.........................................      740-4000-9502
740-4000-504.........................................      740-4000-9504
740-4000-506.........................................      740-4000-9506
740-4000-508.........................................      740-4000-9508
745-4000-502.........................................      745-4000-9502
745-4000-504.........................................      745-4000-9504
745-4000-506.........................................      745-4000-9506
745-4000-508.........................................       745-4000-514
745-4000-510.........................................       745-4000-516
745-4000-512.........................................       745-4000-518
------------------------------------------------------------------------

(i) New Alternative Compliance

    (1) Replacing an engine FCD having a part number listed as ``Old 
Part Number'' in table 1 to paragraph (h) of this AD or table 2 to 
paragraph (h) of this AD, as applicable, with a FCD having the 
corresponding part number listed as ``New Part Number'' in table 1 
to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, 
as applicable, is an acceptable method of compliance with the 
requirements of paragraphs (h)(1) and (h)(3) of this AD for that 
engine FCD only.
    (2) An airplane on which Airbus Modification 157516 has been 
embodied in production is compliant with the requirements of 
paragraph (h)(1) and (h)(3) of this AD, provided no engine FCD, 
having a part number identified as ``Old Part Number'' in table 1 to 
paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as 
applicable, is installed on that airplane.
    (3) An airplane on which Airbus Modification 157718 has been 
embodied in production is compliant with the requirements of 
paragraph (h)(2) of this AD.

(j) New Parts Installation Limitations

    (1) For an airplane with an engine FCD installed having a part 
number identified as ``Old Part Number'' in table 1 to paragraph (h) 
of this AD or table 2 to paragraph (h) of this AD, as applicable: 
After modification of that airplane as required by paragraph (h) of 
this AD, do not install an engine FCD, having a part number 
identified as ``Old Part Number'' in table 1 to paragraph (h) of 
this AD or table 2 to paragraph (h) of this AD, as applicable.
    (2) For an airplane that does not have an engine FCD installed 
having a part number identified as ``Old Part Number'' in table 1 to 
paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as 
applicable: On or after the effective date of this AD, do not 
install an engine FCD, having a part number identified as ``Old Part 
Number'' in table 1 to paragraph (h) of this AD or table 2 to 
paragraph (h) of this AD, as applicable.

(k) New Method of Compliance

    Installation on an engine of a right-hand and left-hand engine 
FCD having a part number approved after the effective date of this 
AD is a method of compliance with the requirements of paragraphs 
(g), (h)(1), and (h)(3) of this AD for that engine only, provided 
the part number is approved, and the installation is accomplished, 
in accordance with 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).

(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, 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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: As of the effective date of 
this AD, 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 (k) 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 2016-0053, dated March 14, 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-2016-8185.
    (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 account.airworth-eas@airbus.com; 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 July 26, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-18492 Filed 8-4-16; 8:45 am]
 BILLING CODE 4910-13-P