```

[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Rules and Regulations]
[Pages 3294-3297]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01110]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8433; Directorate Identifier 2015-NM-194-AD; 
Amendment 39-18366; AD 2016-01-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A319-113 and A319-114 airplanes; and Model A320-211 and 
A320-212 airplanes. This AD requires identifying affected engines, and 
doing a torque check of the forward engine

[[Page 3295]]

bolts on affected engines. This AD would also require, for any bolt 
rotation that is found, torqueing the bolt and eventually replacing the 
forward engine mount bolts, nuts, and washers, doing a fluorescent 
penetrant inspection and dimensional check of the affected bolt holes 
for local deformation and cracks, and doing corrective actions if 
necessary. This AD was prompted by an incorrect torque unit for the 
CFM56-5A engine forward mount fasteners that was inadvertently 
introduced into a certain Airbus airplane maintenance manual. We are 
issuing this AD to prevent loose bolts, which, if combined with induced 
maintenance damage, could lead to forward engine mount failure. An 
engine mount failure can result in an engine detachment and consequent 
reduced control of the airplane, damage to the airplane, and injury to 
persons on the ground.

DATES: This AD becomes effective February 5, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 5, 
2016.
    We must receive comments on this AD by March 7, 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: 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 AD, contact Airbus, 
Airworthiness Office--EAS, 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-2015-8433.

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-
8433; or in person at the Docket Operations office 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 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:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0229, dated November 27, 2015, (referred to after this as ``the 
MCAI''), to correct an unsafe condition for all Airbus Model A319-113 
and A319-114 airplanes; and Model A320-211 and A320-212 airplanes. The 
MCAI states:

    A review of the maintenance instructions revealed that an 
incorrect torque value with wrong unit for the four forward engine 
mount pylon bolts was included in task 71-00-00-400-040-A01, 
``Installation of the power plant with Engine Positioner TWW75E'', 
of the A320 family (CFMI) [CFM International] Aircraft Maintenance 
Manual (AMM), revision dated May 2013. It was determined that this 
AMM inconsistent torque unit affected the A319/A320 airplane 
equipped with CFM56-5A engines only.
    Subsequently, AMM task 71-00-00-400-040-A01 was corrected to 
include the correct values in the August 2015 revision. During the 
period between these two AMM revisions, incorrect torque values may 
have been applied.
    This condition, if not corrected, and if combined with induced 
maintenance damage, could lead to forward engine mount failure, 
possibly resulting in engine detachment and consequent reduced 
control of the airplane, damage to the airplane and/or injury to 
persons on the ground.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A71N010-15 * * *, to provide 
instructions to check the torque values of the forward engine mount 
bolts.
    For the reasons described above, this [EASA] AD requires 
identification of CFM56-5A engines that were installed by using the 
incorrect torque data, verifying the proper torque value of the all 
four forward engine mount pylon bolts and, depending on findings, 
accomplishment of corrective action(s) [i.e., tightening the under-
torqued bolts and replacement of bolts at the next engine change. 
The replacement includes a fluorescent penetrant inspection and 
dimensional check of the pylon bolt holes of the affected forward 
engine mount platform for local deformation and cracks and 
corrective actions, i.e., replacing the forward platform].

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8433.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A71N010-15, 
dated September 30, 2015. The service information describes procedures 
for checking the current torque value for the forward engine bolts; 
torqueing the bolt; replacing the forward engine mount bolts, nuts, and 
washers; doing a fluorescent penetrant inspection and dimensional check 
of the pylon bolt holes of the affected forward engine mount platform 
for local deformation and cracks; and doing corrective actions. 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because this 
condition, if not corrected, and if combined with induced maintenance 
damage, could lead to forward engine mount failure. A failed engine 
mount can result in engine detachment and consequent reduced control of 
the airplane, damage to the airplane, and injury to persons on the

[[Page 3296]]

ground. Therefore, we determined that notice and opportunity for public 
comment before issuing this AD are impracticable and that good cause 
exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-8433; Directorate 
Identifier 2015-NM-194-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 126 airplanes of U.S. registry.
    We also estimate that it will take about 5 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 $53,550, or $425 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 1 work-hour for a cost of $85 per product. We have no 
definitive costs for the engine mounting bolts, nuts, and washers, and 
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 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):

2016-01-07 Airbus: Amendment 39-18366. Docket No. FAA-2015-8433; 
Directorate Identifier 2015-NM-194-AD.

(a) Effective Date

    This AD becomes effective February 5, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A319-113 and A319-114 airplanes, all 
manufacturer serial numbers.
    (2) Airbus Model A320-211 and A320-212 airplanes, all 
manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an incorrect torque unit for the CFM56-
5A engine forward mount fasteners that was inadvertently introduced 
into a certain Airbus airplane maintenance manual. We are issuing 
this AD to prevent loose bolts, which if combined with induced 
maintenance damage, could lead to forward engine mount failure. An 
engine mount failure can result in an engine detachment and 
consequent reduced control of the airplane, damage to the airplane, 
and injury to persons on the ground.

(f) Compliance

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

(g) Identification of Affected Engines and Torque Check

    Within 2 months after the effective date of this AD, accomplish 
the actions required by paragraphs (g)(1) and (g)(2) of this AD, as 
applicable.
    (1) Identify each CFM56-5A engine that has been installed on the 
airplane as specified in A318/A319/A320/A321 Airplane Maintenance 
Manual (AMM) Task 71-00-00-400-040-A01, ``Installation of the Power 
Plant with Engine Positioner TWW-75E,'' of an AMM having a revision 
date between May 2013 and July 2015 (inclusive). A review of 
airplane maintenance records is acceptable in lieu of this 
determination if the date of the AMM revision used for the engine 
installation can be conclusively determined from that review.
    (2) For each engine installation determined to be affected as 
required by paragraph (g)(1) of this AD, check the torque values 
applied on the forward engine mount bolts, in accordance with the 
instructions of paragraph 4.2.2 of Airbus Alert Operators 
Transmission (AOT) A71N010-15, dated September 30, 2015.

(h) On-Condition Actions

    If, during the torque check required by paragraph (g)(2) of this 
AD, any bolt rotation is detected, accomplish the actions required 
by paragraphs (h)(1) and (h)(2) of this AD.
    (1) Before further flight, torque the affected bolt, in 
accordance with the instructions of paragraph 4.2.3.1 of Airbus AOT 
A71N010-15, dated September 30, 2015.
    (2) During the next engine removal, replace the forward engine 
mount bolts, nuts, and washers; accomplish a fluorescent penetrant 
inspection and dimensional check of the pylon bolt holes of the 
affected forward engine mount platform for local deformation

[[Page 3297]]

and cracks; and do all applicable corrective actions; in accordance 
with the instructions of paragraph 4.2.3.2 of Airbus AOT A71N010-15, 
dated September 30, 2015. Do all applicable corrective actions 
before further flight.

(i) Parts Installation Limitation

    As of the effective date of this AD, installation of a CFM56-5A 
engine on an airplane is permitted, provided that the installation 
is accomplished using the torque values for forward engine mount 
bolts specified in paragraph 4.2.3.1 of Airbus AOT A71N010-15, dated 
September 30, 2015.

    Note 1 to paragraph (i) of this AD: Additional guidance for the 
re-torque can be found in Airbus A318/A319/A320/A321 AMM, Task 71-
00-00-400-040-A01, ``Installation of the Power Plant with Engine 
Positioner TWW 75E,'' dated August 2015.

(j) Special Flight Permits

    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.

(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: 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: 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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0229, dated November 27, 2015, for related information. 
You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-8433.

(m) 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 Alert Operators Transmission (AOT) A71N010-15, dated 
September 30, 2015.
    (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 December 28, 2015.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01110 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P
```