Document ID: FAA-2014-1047-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-04-05T04:00Z

[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Rules and Regulations]
[Pages 19467-19470]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07028]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1047; Directorate Identifier 2014-NM-157-AD; 
Amendment 39-18449; AD 2016-07-04]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was 
prompted by a report that, during the assembly process, several gaps 
between the two parts of the girt bar fittings for the aft passenger 
doors were found to exceed tolerances. This AD requires an inspection 
of the gap between the two parts of the girt bar fittings on left-hand 
(LH) and right-hand (RH) aft passenger doors, and corrective actions if 
necessary. We are issuing this AD to detect and correct incorrect gaps 
between the girt bar fittings. Detachment of a girt bar could lead to 
the separation of the slide or slide-raft from the fuselage, making the 
emergency exit inoperative, which could impede an emergency evacuation.

DATES: This AD becomes effective May 10, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 10, 
2016.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1047.

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-2014-
1047; 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 Office (telephone 
800-647-5527) is Docket Management Facility,

[[Page 19468]]

U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

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 certain Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on January 23, 2015 (80 FR 3533) (``the NPRM''). The 
NPRM was prompted by a report that, during the assembly process, 
several gaps between the two parts of the girt bar fittings for the aft 
passenger doors were found to exceed tolerances. The NPRM proposed to 
require an inspection of the gap between the two parts of the girt bar 
fittings on LH and RH aft passenger doors, and corrective actions if 
necessary. We are issuing this AD to detect and correct incorrect gaps 
between the girt bar fittings. Detachment of a girt bar could lead to 
the separation of the slide or slide-raft from the fuselage, making the 
emergency exit inoperative, which could impede an emergency evacuation.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. The following 
presents the comments received on the NPRM and the FAA's response to 
each comment.

Request To Reference Later Revision of Service Information

    United Airlines (UAL) proposed to update the reference to the 
service information to Airbus Service Bulletin A320-53-1289, Revision 
01, dated August 29, 2014. UAL also suggested that the service 
information update would also update the effectivity for the applicable 
inspection.
    We agree to reference the latest service information, Airbus 
Service Bulletin A320-53-1289, Revision 01, dated August 29, 2014, 
which updates the effectivity, and have revised paragraph (g) of this 
AD accordingly. We have also added a new paragraph (i) to this AD to 
provide credit for actions done using Airbus Service Bulletin A320-53-
1289, dated May 28, 2014, and have redesignated subsequent paragraphs 
accordingly.

Request To Clarify the Tolerances for the Gap Size

    UAL requested clarification on the inspection task's initial gap 
requirement tolerance and the required gap tolerance for trimmed 
latches. UAL stated that it seems the initial inspection in Task 
531289-832-601/602-001 of Airbus Service Bulletin A320-53-1289, 
Revision 01, dated August 29, 2014, specifies that a gap equal to or 
less than 4 millimeters (mm) (0.158 inch) is acceptable without the 
need for further action, but other tasks for post-trimming and post-
latch-replacement inspections specify replacement if the gap is less 
than 1 mm (0.0394 inch). UAL noted that those inspection tasks 
reference a figure in Airbus Service Bulletin A320-53-1289, Revision 
01, dated August 29, 2014, which specifies the gap should be between 1 
mm (0.0394 inch) and 4 mm (0.158 inch). UAL also stated that the 
trimming action in Task 531289-831-601-001 of Airbus Service Bulletin 
A320-53-1289, Revision 01, dated August 29, 2014, specifies trimming 
the latch again if the gap is still greater than 4 mm (0.158 inch), 
which seems to conflict with a figure that gives one trim dimension 
without any tolerance. UAL further stated that it should be clearer 
that the latch should be trimmed as many times as required with a 
maximum trim dimension of 0.5 mm (0.0197 inch) until the required gap 
tolerance is achieved.
    We agree to provide clarification. Figure A-SBCAA of Airbus Service 
Bulletin A320-53-1289, Revision 01, dated August 29, 2014, specifies 
0.5 mm (0.0197 inch) as the limit of the edge margin, which must not be 
exceeded while trimming the latch part during the gap adjustment. We 
find that Airbus Service Bulletin A320-53-1289, Revision 01, dated 
August 29, 2014, is clear on the initial gap tolerance, which specifies 
corrective actions if the gap is initially greater than 4 mm (0.158 
inch). The corrective actions include trimming and determining the gap 
after trimming. If the gap is less than 1 mm (0.0394 inch) or greater 
than 4 mm (0.158 inch) after trimming, Airbus Service Bulletin A320-53-
1289, Revision 01, dated August 29, 2014, specifies additional 
corrective actions. No change has been made to this final rule in this 
regard.

Request To Address Issue of Obsolete Part Numbers

    UAL stated that the NPRM and the referenced service information 
(Airbus Service Bulletins A320-53-1289, dated May 28, 2014, and 
Revision 01, dated August 29, 2014) do not identify part number 
D531125020000 as obsolete, which is identified in the illustrated parts 
catalog (IPC) as an acceptable part. UAL pointed out that the 
referenced service information introduces new part numbers D5348027920-
200/400 as part of a corrective action, but does not specify the new 
part numbers as a part of an action to require new or revised latch or 
girt bar assembly parts. UAL asserts that, without a revised IPC or 
specific steps in the service information, there is a risk that the old 
part number could be used in the future, and lead to an incorrect gap 
after accomplishing the inspection required by this AD.
    We agree to clarify the issue. This AD refers to Airbus Service 
Bulletin A320-53-1289, Revision 01, dated August 29, 2014, as the 
appropriate source of service information for accomplishing the actions 
required by this AD. We have determined the information specified in 
Airbus Service Bulletin A320-53-1289, Revision 01, dated August 29, 
2014, is adequate. In addition, the requirements of an AD take 
precedence over any specifications in an IPC, which is not an FAA-
approved document. We recommend that operators work with the 
manufacturer to ensure there are no discrepancies in the IPC. It is the 
responsibility of operators to apply necessary controls to maintain the 
airplane in accordance with the required configuration of an AD. No 
change has been made to this final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1289, Revision 01, dated 
August 29, 2014. The service information describes procedures for a 
detailed inspection of the gap in the girt bar fittings of the aft 
passenger doors, LH and RH sides, and corrective actions.

[[Page 19469]]

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 838 airplanes of U.S. registry.
    We also estimate that it will take about 3 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $213,690, or $255 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $435, for a cost of 
$775 per product. We have no way of determining the number of aircraft 
that might need these actions.

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 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.

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):

2016-07-04 Airbus: Amendment 39-18449. Docket No. FAA-2014-1047; 
Directorate Identifier 2014-NM-157-AD.

(a) Effective Date

    This AD becomes effective May 10, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(4) of this AD, 
except those on which Airbus Modification 154966 has been embodied 
during production.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report that, during the assembly 
process, several gaps between the two parts of the girt bar fittings 
for the aft passenger doors were found to exceed tolerances. We are 
issuing this AD to detect and correct incorrect gaps between the 
girt bar fittings. Detachment of a girt bar could lead to the 
separation of the slide or slide-raft from the fuselage, making the 
emergency exit inoperative, which could impede an emergency 
evacuation.

(f) Compliance

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

(g) Inspection and Corrective Action

    Except as provided by paragraph (h) of this AD, within 36 months 
after the effective date of this AD, do a detailed inspection of the 
gap in the girt bar fittings of the aft passenger doors, left-hand 
(LH) and right-hand (RH) sides, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1289, Revision 01, dated August 29, 
2014. Do all applicable corrective actions before further flight.

(h) Exception

    For any airplane that has been modified to a configuration where 
one or both LH and RH aft passenger doors are permanently 
inoperative or deactivated: If any aft passenger door is 
reactivated, after reactivation but before further flight, do the 
detailed inspection of the reactivated aft passenger door(s) and all 
applicable corrective actions, as required by paragraph (g) of this 
AD.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1289, dated May 28, 2014, which is not incorporated by 
reference in this AD.

(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: 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) Required for Compliance (RC): 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

[[Page 19470]]

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.
    (3) 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

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2014-
0178, dated July 25, 2014, 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-2014-1047.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

(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 A320-53-1289, Revision 01, dated 
August 29, 2014.
    (ii) Reserved.
    (3) 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.
    (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.
    (5) You may view this service information that is incorporated 
by reference at the 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 March 20, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07028 Filed 4-4-16; 8:45 am]
BILLING CODE 4910-13-P