[Federal Register Volume 80, Number 146 (Thursday, July 30, 2015)]
[Proposed Rules]
[Pages 45462-45465]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18533]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2963; Directorate Identifier 2015-NM-016-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 A319-131, -132, and -133 airplanes; Model A320-232 and -
233 airplanes; and Model A321-131, -231, and -232 airplanes. This 
proposed AD was prompted by reports of forward engine mount attachment 
pins that were manufactured from discrepant raw material. This proposed 
AD would require identification and replacement of affected forward 
engine mount attachment pins. We are proposing this AD to prevent 
failure of a forward engine mount attachment pin, possible loss of an 
engine in-flight, and consequent reduced controllability of the 
airplane.

DATES: We must receive comments on this proposed AD by September 14, 
2015.

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: 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 Airbus service information identified in this proposed 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. For Goodrich Aerostructures service information 
identified in this proposed AD, contact UTC Aerospace Systems, ATTN: 
Christopher Newth--V2500 A1/A5 Project Engineer, Aftermarket--
Aerostructures; 850 Lagoon Drive, Chula Vista, CA; telephone 619-498-
7505; email [email protected]. 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-2015-
2963; 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-2015-2963; 
Directorate Identifier 2015-NM-016-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 45463]]

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 2015-0004, dated January 13, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A319-131, -132, and -133 airplanes; Model A320-232 and -233 airplanes; 
and Model A321-131, -231, and -232 airplanes. The MCAI states:

    A number of forward engine mount pins, Part Number (P/N) 740-
2022-501, intended for IAE V2500 series engines, have been reported 
as non-compliant with the current certification requirements, due to 
a quality issue during manufacturing of the raw material. It was 
also determined that a batch of 88 affected pins are installed on 
in-service aeroplanes fitted with forward engine mount P/N 745-2010-
503 and the serial numbers (s/n) of the affected pins and the 
[manufacturer serial number] MSN of the related aeroplanes have been 
identified.
    This condition, if not corrected, could lead to forward engine 
mount pin failure, possibly resulting in in-flight loss of an engine 
and consequent reduced control of the aeroplane.
    For the reasons described above, this [EASA] AD requires 
identification of the affected forward engine mount pins and removal 
from service [replacement] of those pins.

    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-2015-
2963.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1064, dated November 5, 
2014; and Goodrich Aerostructures has issued Service Bulletin V2500-
NAC-71-0323, dated September 18, 2014. The service information 
describes procedures for an inspection to determine the serial number 
of the attachment pins for the forward engine mount crossbeam to main 
beam for each engine, and replacement of affected pins. 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 of this NPRM.

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.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified Airbus service information, procedures and tests identified 
as RC must be done to comply with the proposed AD. However, procedures 
and 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 alternative method 
of compliance (AMOC), provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 922 airplanes of U.S. 
registry.
    We also estimate that it would take about 2 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 $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $156,740, or $170 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 4 work-hours and require parts costing $1,724, for a cost of 
$2,064 per attachment pin replacement. We have no way of determining 
the number of aircraft that might need this action.

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,

[[Page 45464]]

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-2015-2963; Directorate Identifier 2015-NM-
016-AD.

(a) Comments Due Date

    We must receive comments by September 14, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers.
    (1) Model A319-131, -132, and -133 airplanes.
    (2) Model A320-232 and -233 airplanes.
    (3) Model A321-131, -231, and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of forward engine mount 
attachment pins that were manufactured from discrepant raw material. 
We are issuing this AD to prevent failure of a forward engine mount 
attachment pin, possible loss of an engine in-flight, and consequent 
reduced controllability of the airplane.

(f) Compliance

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

(g) Identification of Part Numbers for Forward Engine Mount and 
Attachment Pins

    Except as provided by paragraph (i) of this AD, at the earliest 
of the times specified in paragraphs (g)(1) through (g)(4) of this 
AD: For each engine, identify the part number of the forward engine 
mount, and the part number and serial number of the attachment pin 
for that forward engine mount, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-71-1064, dated November 
5, 2014; and Goodrich Aerostructures Service Bulletin V2500-NAC-71-
0323, dated September 18, 2014. A review of airplane maintenance 
records is acceptable in lieu of this identification if the part 
number of the forward engine mount, and the part number and serial 
number of the attachment pin for that forward engine mount can be 
conclusively determined from that review. If any part number of the 
forward engine mount, or part number or serial number of the 
attachment pins for the forward engine mount, cannot be identified: 
At the earliest of the times specified in paragraphs (g)(1) through 
(g)(4) of this AD, contact 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), for identification information.
    (1) Within 24 months after the effective date of this AD.
    (2) At the next engine removal after the effective date of this 
AD.
    (3) Within 7,500 flight hours after the effective date of this 
AD.
    (4) Within 5,000 flight cycles after the effective date of this 
AD.

(h) Corrective Actions

    If, during any identification required by paragraph (g) of this 
AD, a forward engine mount having part number (P/N) 745-2010-503 is 
found, and the attachment pin has P/N 740-2022-501 with any serial 
number that is included in figure 1 to paragraphs (h) and (j) of 
this AD: At the earliest of the times specified in paragraphs (g)(1) 
through (g)(4) of this AD, replace the affected attachment pin with 
a serviceable part having a part number other than P/N 740-2022-501, 
and having a serial number that is not identified in figure 1 to 
paragraphs (h) and (j) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-71-1064, 
dated November 5, 2014; and Goodrich Aerostructures Service Bulletin 
V2500-NAC-71-0323, dated September 18, 2014.

 Figure 1 to Paragraphs (h) and (j) of This AD--Part Numbers and Serial
      Numbers of Affected Forward Engine Mounts and Attachment Pins
------------------------------------------------------------------------
                               Serial Nos.
-------------------------------------------------------------------------
                                     Forward Engine Mount (P/N 745-2010-
 Attachment Pin (P/N 740-2022-501)                   503)
------------------------------------------------------------------------
                  1396SC                            13665001
                  1391SC                            13655001
                  1412SC                            13689001
                  1402SC                            13669001
                  1409SC                            13683001
                  1416SC                            13697001
                  1418SC                            13701001
                  1417SC                            13699001
                  1414SC                            13693001
                  1415SC                            13695001
                  1420SC                            13705001
                  1421SC                            13707001
                  1422SC                            13709001
                  1436SC                            13737001
                  1438SC                            13741001
                  1452SC                            13769001
                  1456SC                            13777001
                  1397SC                            13667001
                  1432SC                            13729001
                  1405SC                            13675001
                  1411SC                            13687001
                  1389SC                            13651001
                  1392SC                            13657001
                  1382SC                            13637001
                  1384SC                            13641001
                  1407SC                            13679001
                  1408SC                            13681001
                  1395SC                            13663001
                  1406SC                            13677001
                  1383SC                            13639001
                  1404SC                            13673001
                  1393SC                            13659001
                  1413SC                            13691001
                  1386SC                            13645001
                  1388SC                            13649001
                  1390SC                            13653001
                  1410SC                            13685001
                  1423SC                            13711001
                  1424SC                            13713001
                  1403SC                            13671001
                  1419SC                            13703001
                  1385SC                            13643001
                  1387SC                            13647001
                  1431SC                            13727001
                  1433SC                            13731001
                  1425SC                            13715001
                  1428SC                            13721001
                  1429SC                            13723001
                  1430SC                            13725001
                  1427SC                            13719001
                  1434SC                            13733001
                  1442SC                            13749001
                  1394SC                            13661001
                  1441SC                            13747001
                  1426SC                            13717001
                  1437SC                            13739001
                  1439SC                            13743001
                  1443SC                            13751001
                  1448SC                            13761001
                  1435SC                            13735001
                  1440SC                            13745001
                  1454SC                            13773001
                  1455SC                            13775001
                  1451SC                            13767001
                  1453SC                            13771001
                  1444SC                            13753001
                  1450SC                            13765001
                  1461SC                            13787001
                  1469SC                            13817001
                  1480SC                            13839001
                  1481SC                            13841001
                  1446SC                            13757001
                  1449SC                            13763001

[[Page 45465]]

 
                  1467SC                            13813001
                  1445SC                            13755001
                  1462SC                            13789001
                  1464SC                            13793001
                  1466SC                            13811001
                  1470SC                            13819001
                  1459SC                            13783001
                  1463SC                            13791001
                  1475SC                            13829001
                  1458SC                            13781001
                  1477SC                            13833001
                  1474SC                            13827001
                  1478SC                            13835001
                  1479SC                            13837001
                  1472SC                            13823001
------------------------------------------------------------------------

(i) Exception to Paragraph (g) of This AD

    For airplanes with manufacturer serial numbers identified in 
figure 2 to paragraph (i) of this AD: If it can be conclusively 
determined that an engine has not been replaced after March 1, 2011 
(the date of manufacture of the first airplane with affected engine 
mounts), the airplane is not affected by the requirements of 
paragraphs (g) and (h) of this AD.

   Figure 2 to Paragraph (i) of This AD--Airplane Manufacturer Serial
                                 Numbers
------------------------------------------------------------------------
                    Airplane manufacturer serial Nos.
-------------------------------------------------------------------------
                                           4593
                                           4602
                                           4620
                                           4637
                                           4638
                                           4642
                                           4643
                                           4644
                                           4660
                                           4677
                                           4690
                                           4696
                                           4700
                                           4701
                                           4703
                                           4706
                                           4707
                                           4710
                                           4716
                                           4719
                                           4725
                                           4726
                                           4731
                                           4736
                                           4737
                                           4741
                                           4746
                                           4751
                                           4752
                                           4753
                                           4754
                                           4755
                                           4757
                                           4761
                                           4762
                                           4772
                                           4773
                                           4774
                                           4775
                                           4779
                                           4782
                                           4783
                                           4784
                                           4786
                                           4788
                                           4790
                                           4791
                                           4798
                                           4804
                                           4813
------------------------------------------------------------------------

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane any engine mount attachment pin having P/N 740-2022-501 
with a serial number identified in figure 1 to paragraphs (h) and 
(j) of this AD.

(k) 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.
    (3) 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 obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Special Flight Permits Prohibited

    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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0004, dated January 13, 
2015, 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-2015-2963.
    (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. For Goodrich Aerostructures service 
information identified in this AD, contact UTC Aerospace Systems, 
ATTN: Christopher Newth--V2500 A1/A5 Project Engineer, Aftermarket--
Aerostructures; 850 Lagoon Drive, Chula Vista, CA; telephone 619-
498-7505; email [email protected]. 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 17, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-18533 Filed 7-29-15; 8:45 am]
BILLING CODE 4910-13-P