81_FR_3307 81 FR 3294 - Airworthiness Directives; Airbus Airplanes

81 FR 3294 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 13 (January 21, 2016)

Page Range3294-3297
FR Document2016-01110

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 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.

Federal Register, Volume 81 Issue 13 (Thursday, January 21, 2016) 
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Rules and Regulations]
[Pages 3294-3297]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-01110]


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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.

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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 [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. 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: [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 
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 [email protected]; 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

3294 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations In an interim rule published in the view of the foregoing, it can be Comments on the interim rule were Federal Register on August 19, 2015, concluded that the majority of required to be received on or before and effective on August 20, 2015, (80 FR Washington apricots producers and October 19, 2015. No comments were 50189, Doc. No. AMS–FV–15–0033, handlers may be classified as small received. Therefore, for reasons given in FV15–922–1 IR), § 922.235 was entities. the interim rule, we are adopting the amended by decreasing the assessment This rule continues in effect the interim rule as a final rule, without rate for the 2015–2016 and subsequent action that decreased the assessment change. fiscal periods from $1.50 to $0.75 per rate collected from handlers for the To view the interim rule, go to: http:// ton. The decrease in the per ton 2015–2016 and subsequent fiscal www.regulations.gov/ assessment rate allows the Committee to periods from $1.50 to $0.75 per ton of #!documentDetail;D=AMS-FV-15-0033- reduce its financial reserve while still apricots handled. The Committee also 0001. providing adequate funding to meet unanimously recommended 2015–2016 This action also affirms information program expenses. fiscal period expenditures of $7,610. contained in the interim rule concerning With a 2015 Washington apricot crop Executive Orders 12866, 12988, 13175, Final Regulatory Flexibility Analysis estimate of 5,800 fresh market tons, the and 13563; the Paperwork Reduction Pursuant to requirements set forth in Committee anticipates assessment Act (44 U.S.C. Chapter 35); and the E- the Regulatory Flexibility Act (RFA) (5 income of approximately $4,350. Gov Act (44 U.S.C. 101). U.S.C. 601–612), the Agricultural Income derived from handler After consideration of all relevant Marketing Service (AMS) has assessments, along with funds from the material presented, it is found that considered the economic impact of this Committee’s monetary reserve, will be finalizing the interim rule, without rule on small entities. Accordingly, adequate to cover budgeted expenses for change, as published in the Federal AMS has prepared this final regulatory the 2015–2016 fiscal period. This action Register (80 FR 50189, August 19, 2015) flexibility analysis. will allow the Committee to reduce its will tend to effectuate the declared The purpose of the RFA is to fit policy of the Act. financial reserve while still providing regulatory actions to the scale of adequate funding to meet program List of Subjects in 7 CFR Part 922 businesses subject to such actions in expenses. order that small businesses will not be Apricots, Marketing agreements, unduly or disproportionately burdened. This rule continues in effect the action that decreased the assessment Reporting and recordkeeping Marketing orders issued pursuant to the requirements. Act, and the rules issued thereunder, are obligation imposed on handlers. Assessments are applied uniformly on Accordingly, the interim rule unique in that they are brought about amending 7 CFR part 922, which was through group action of essentially all handlers. However, decreasing the assessment rate reduces the burden on published at 80 FR 50189 on August 19, small entities acting on their own 2015, is adopted as a final rule without behalf. handlers, and may reduce the burden on producers. change. There are approximately 100 apricot producers in the production area and In addition, the Committee’s meeting Dated: January 15, 2016. approximately 17 handlers subject to was widely publicized throughout the Erin Morris, regulation under the marketing order. Washington apricot industry, and all Associate Administrator, Agricultural Small agricultural producers are defined interested persons were invited to Marketing Service. by the Small Business Administration as attend the meeting and participate in [FR Doc. 2016–01137 Filed 1–20–16; 8:45 am] those having annual receipts of less than Committee deliberations on all issues. BILLING CODE 3410–02–P $750,000, and small agricultural service Like all Committee meetings, the May firms are defined as those having annual 12, 2015, meeting was a public meeting, receipts of less than $7,000,000 (13 CFR and all entities, both large and small, DEPARTMENT OF TRANSPORTATION 121.201). were able to express views on this issue. The National Agricultural Statistics In accordance with the Paperwork Federal Aviation Administration Service reported that, in 2014, the Reduction Act of 1995 (44 U.S.C. Washington apricot total utilization of Chapter 35), the order’s information 14 CFR Part 39 8,500 tons (including both fresh and collection requirements have been previously approved by the Office of [Docket No. FAA–2015–8433; Directorate processed markets) sold for an average Identifier 2015–NM–194–AD; Amendment of $1,080 per ton. Consequently, the Management and Budget (OMB) and 39–18366; AD 2016–01–07] total farm-gate value in 2014 was assigned OMB No. 0581–0189. No approximately $9,180,000. Based on the changes in those requirements as a RIN 2120–AA64 number of producers in the production result of this action are necessary. area (100), the 2014 average revenue Should any changes become necessary, Airworthiness Directives; Airbus from the sale of apricots is estimated at they would be submitted to OMB for Airplanes approximately $91,800 per producer. In approval. AGENCY: Federal Aviation addition, based on information from the This action imposes no additional Administration (FAA), Department of USDA’s Market News Service, 2014 reporting or recordkeeping requirements Transportation (DOT). f.o.b. prices for WA No. 1 apricots on either small or large Washington ACTION: Final rule; request for ranged from $20.00 to $26.00 per 24- apricot handlers. As with all Federal comments. pound loose-pack container, and from marketing order programs, reports and jstallworth on DSK7TPTVN1PROD with RULES $22.00 to $30.00 for 2-layer tray-pack forms are periodically reviewed to SUMMARY: We are adopting a new containers. Using average price and reduce information requirements and airworthiness directive (AD) for all shipment information provided by the duplication by industry and public Airbus Model A319–113 and A319–114 Committee, it is determined that each of sector agencies. airplanes; and Model A320–211 and the Washington apricot handlers USDA has not identified any relevant A320–212 airplanes. This AD requires currently ship less than $7,000,000 Federal rules that duplicate, overlap, or identifying affected engines, and doing worth of apricots on an annual basis. In conflict with this rule. a torque check of the forward engine VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\21JAR1.SGM 21JAR1

Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3295 bolts on affected engines. This AD Examining the AD Docket engine mount pylon bolts and, depending on would also require, for any bolt rotation findings, accomplishment of corrective You may examine the AD docket on action(s) [i.e., tightening the under-torqued that is found, torqueing the bolt and the Internet at http:// bolts and replacement of bolts at the next eventually replacing the forward engine www.regulations.gov by searching for engine change. The replacement includes a mount bolts, nuts, and washers, doing a and locating Docket No. FAA–2015– fluorescent penetrant inspection and fluorescent penetrant inspection and 8433; or in person at the Docket dimensional check of the pylon bolt holes of dimensional check of the affected bolt Operations office between 9 a.m. and 5 the affected forward engine mount platform holes for local deformation and cracks, p.m., Monday through Friday, except for local deformation and cracks and and doing corrective actions if corrective actions, i.e., replacing the forward Federal holidays. The AD docket platform]. necessary. This AD was prompted by an contains this AD, the regulatory incorrect torque unit for the CFM56–5A evaluation, any comments received, and You may examine the MCAI on the engine forward mount fasteners that was other information. The street address for Internet at http://www.regulations.gov inadvertently introduced into a certain the Docket Operations office (telephone by searching for and locating Docket No. Airbus airplane maintenance manual. 800–647–5527) is in the ADDRESSES FAA–2015–8433. We are issuing this AD to prevent loose section. Comments will be available in Related Service Information Under 1 bolts, which, if combined with induced the AD docket shortly after receipt. CFR Part 51 maintenance damage, could lead to FOR FURTHER INFORMATION CONTACT: forward engine mount failure. An Airbus has issued Alert Operators Sanjay Ralhan, Aerospace Engineer, Transmission (AOT) A71N010–15, engine mount failure can result in an International Branch, ANM–116, engine detachment and consequent dated September 30, 2015. The service Transport Airplane Directorate, FAA, information describes procedures for reduced control of the airplane, damage 1601 Lind Avenue SW., Renton, WA to the airplane, and injury to persons on checking the current torque value for 98057–3356; telephone 425–227–1405; the forward engine bolts; torqueing the the ground. fax 425–227–1149. DATES: This AD becomes effective bolt; replacing the forward engine SUPPLEMENTARY INFORMATION: mount bolts, nuts, and washers; doing a February 5, 2016. The Director of the Federal Register Discussion fluorescent penetrant inspection and approved the incorporation by reference dimensional check of the pylon bolt The European Aviation Safety Agency holes of the affected forward engine of a certain publication listed in this AD (EASA), which is the Technical Agent mount platform for local deformation as of February 5, 2016. for the Member States of the European and cracks; and doing corrective We must receive comments on this Union, has issued EASA AD 2015–0229, actions. This service information is AD by March 7, 2016. dated November 27, 2015, (referred to reasonably available because the ADDRESSES: You may send comments, after this as ‘‘the MCAI’’), to correct an interested parties have access to it using the procedures found in 14 CFR unsafe condition for all Airbus Model through their normal course of business 11.43 and 11.45, by any of the following A319–113 and A319–114 airplanes; and or by the means identified in the methods: Model A320–211 and A320–212 ADDRESSES section. • Federal eRulemaking Portal: Go to airplanes. The MCAI states: http://www.regulations.gov. Follow the FAA’s Determination and Requirements A review of the maintenance instructions instructions for submitting comments. of This AD revealed that an incorrect torque value with • Fax: 202–493–2251. wrong unit for the four forward engine mount This product has been approved by • Mail: U.S. Department of pylon bolts was included in task 71–00–00– the aviation authority of another Transportation, Docket Operations, M– 400–040–A01, ‘‘Installation of the power country, and is approved for operation 30, West Building Ground Floor, Room plant with Engine Positioner TWW75E’’, of in the United States. Pursuant to our W12–140, 1200 New Jersey Avenue SE., the A320 family (CFMI) [CFM International] bilateral agreement with the State of Washington, DC 20590. Aircraft Maintenance Manual (AMM), revision dated May 2013. It was determined Design Authority, we have been notified • Hand Delivery: U.S. Department of of the unsafe condition described in the that this AMM inconsistent torque unit Transportation, Docket Operations, M– affected the A319/A320 airplane equipped MCAI and service information 30, West Building Ground Floor, Room with CFM56–5A engines only. referenced above. We are issuing this W12–140, 1200 New Jersey Avenue SE., Subsequently, AMM task 71–00–00–400– AD because we evaluated all pertinent Washington, DC, between 9 a.m. and 5 040–A01 was corrected to include the correct information and determined the unsafe p.m., Monday through Friday, except values in the August 2015 revision. During condition exists and is likely to exist or Federal holidays. the period between these two AMM develop on other products of these same For service information identified in revisions, incorrect torque values may have type designs. this AD, contact Airbus, Airworthiness been applied. This condition, if not corrected, and if FAA’s Determination of the Effective Office—EAS, 1 Rond Point Maurice combined with induced maintenance Date Bellonte, 31707 Blagnac Cedex, France; damage, could lead to forward engine mount telephone +33 5 61 93 36 96; fax +33 5 failure, possibly resulting in engine An unsafe condition exists that 61 93 44 51; email account.airworth- detachment and consequent reduced control requires the immediate adoption of this eas@airbus.com; Internet http:// of the airplane, damage to the airplane and/ AD. The FAA has found that the risk to www.airbus.com. You may view this or injury to persons on the ground. the flying public justifies waiving notice referenced service information at the To address this potential unsafe condition, and comment prior to adoption of this FAA, Transport Airplane Directorate, Airbus issued Alert Operators Transmission rule because this condition, if not jstallworth on DSK7TPTVN1PROD with RULES 1601 Lind Avenue SW., Renton, WA. (AOT) A71N010–15 * * *, to provide corrected, and if combined with instructions to check the torque values of the For information on the availability of induced maintenance damage, could forward engine mount bolts. this material at the FAA, call 425–227– For the reasons described above, this lead to forward engine mount failure. A 1221. It is also available on the Internet [EASA] AD requires identification of failed engine mount can result in engine at http://www.regulations.gov by CFM56–5A engines that were installed by detachment and consequent reduced searching for and locating Docket No. using the incorrect torque data, verifying the control of the airplane, damage to the FAA–2015–8433. proper torque value of the all four forward airplane, and injury to persons on the VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\21JAR1.SGM 21JAR1

3296 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations ground. Therefore, we determined that air commerce by prescribing regulations (c) Applicability notice and opportunity for public for practices, methods, and procedures This AD applies to the airplanes identified comment before issuing this AD are the Administrator finds necessary for in paragraphs (c)(1) and (c)(2) of this AD, impracticable and that good cause exists safety in air commerce. This regulation certificated in any category. for making this amendment effective in is within the scope of that authority (1) Airbus Model A319–113 and A319–114 fewer than 30 days. because it addresses an unsafe condition airplanes, all manufacturer serial numbers. that is likely to exist or develop on (2) Airbus Model A320–211 and A320–212 Comments Invited airplanes, all manufacturer serial numbers. products identified in this rulemaking This AD is a final rule that involves action. (d) Subject requirements affecting flight safety, and Air Transport Association (ATA) of we did not precede it by notice and Regulatory Findings America Code 71, Power Plant. opportunity for public comment. We We determined that this AD will not (e) Reason invite you to send any written relevant have federalism implications under data, views, or arguments about this AD. This AD was prompted by an incorrect Executive Order 13132. This AD will torque unit for the CFM56–5A engine Send your comments to an address not have a substantial direct effect on forward mount fasteners that was listed under the ADDRESSES section. the States, on the relationship between inadvertently introduced into a certain Include ‘‘Docket No. FAA–2015–8433; the national government and the States, Airbus airplane maintenance manual. We are Directorate Identifier 2015–NM–194– or on the distribution of power and issuing this AD to prevent loose bolts, which AD’’ at the beginning of your comments. responsibilities among the various if combined with induced maintenance We specifically invite comments on the levels of government. damage, could lead to forward engine mount overall regulatory, economic, failure. An engine mount failure can result in environmental, and energy aspects of For the reasons discussed above, I an engine detachment and consequent this AD. We will consider all comments certify that this AD: reduced control of the airplane, damage to received by the closing date and may 1. Is not a ‘‘significant regulatory the airplane, and injury to persons on the action’’ under Executive Order 12866; ground. amend this AD based on those comments. 2. Is not a ‘‘significant rule’’ under the (f) Compliance We will post all comments we DOT Regulatory Policies and Procedures Comply with this AD within the receive, without change, to http:// (44 FR 11034, February 26, 1979); compliance times specified, unless already www.regulations.gov, including any 3. Will not affect intrastate aviation in done. personal information you provide. We Alaska; and (g) Identification of Affected Engines and will also post a report summarizing each Torque Check substantive verbal contact we receive 4. Will not have a significant about this AD. economic impact, positive or negative, Within 2 months after the effective date of on a substantial number of small entities this AD, accomplish the actions required by Costs of Compliance under the criteria of the Regulatory paragraphs (g)(1) and (g)(2) of this AD, as Flexibility Act. applicable. We estimate that this AD affects 126 (1) Identify each CFM56–5A engine that airplanes of U.S. registry. List of Subjects in 14 CFR Part 39 has been installed on the airplane as We also estimate that it will take specified in A318/A319/A320/A321 Airplane about 5 work-hours per product to Air transportation, Aircraft, Aviation Maintenance Manual (AMM) Task 71–00– comply with the basic requirements of safety, Incorporation by reference, 00–400–040–A01, ‘‘Installation of the Power this AD. The average labor rate is $85 Safety. Plant with Engine Positioner TWW–75E,’’ of per work-hour. Based on these figures, an AMM having a revision date between May Adoption of the Amendment 2013 and July 2015 (inclusive). A review of we estimate the cost of this AD on U.S. airplane maintenance records is acceptable in operators to be $53,550, or $425 per Accordingly, under the authority lieu of this determination if the date of the product. delegated to me by the Administrator, AMM revision used for the engine In addition, we estimate that any the FAA amends 14 CFR part 39 as installation can be conclusively determined necessary follow-on actions will take follows: from that review. about 1 work-hour for a cost of $85 per (2) For each engine installation determined product. We have no definitive costs for PART 39—AIRWORTHINESS to be affected as required by paragraph (g)(1) the engine mounting bolts, nuts, and DIRECTIVES of this AD, check the torque values applied washers, and no way of determining the on the forward engine mount bolts, in number of aircraft that might need this ■ 1. The authority citation for part 39 accordance with the instructions of action. continues to read as follows: paragraph 4.2.2 of Airbus Alert Operators Transmission (AOT) A71N010–15, dated Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. September 30, 2015. Title 49 of the United States Code § 39.13 [Amended] (h) On-Condition Actions specifies the FAA’s authority to issue If, during the torque check required by rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding paragraph (g)(2) of this AD, any bolt rotation section 106, describes the authority of the following new airworthiness is detected, accomplish the actions required the FAA Administrator. ‘‘Subtitle VII: directive (AD): by paragraphs (h)(1) and (h)(2) of this AD. Aviation Programs,’’ describes in more 2016–01–07 Airbus: Amendment 39–18366. (1) Before further flight, torque the affected detail the scope of the Agency’s Docket No. FAA–2015–8433; Directorate bolt, in accordance with the instructions of jstallworth on DSK7TPTVN1PROD with RULES authority. Identifier 2015–NM–194–AD. paragraph 4.2.3.1 of Airbus AOT A71N010– We are issuing this rulemaking under 15, dated September 30, 2015. (a) Effective Date (2) During the next engine removal, replace the authority described in ‘‘Subtitle VII, the forward engine mount bolts, nuts, and This AD becomes effective February 5, Part A, Subpart III, Section 44701: 2016. washers; accomplish a fluorescent penetrant General requirements.’’ Under that inspection and dimensional check of the section, Congress charges the FAA with (b) Affected ADs pylon bolt holes of the affected forward promoting safe flight of civil aircraft in None. engine mount platform for local deformation VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\21JAR1.SGM 21JAR1

Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3297 and cracks; and do all applicable corrective (m) Material Incorporated by Reference This AD also provides optional actions; in accordance with the instructions (1) The Director of the Federal Register terminating action for the door of paragraph 4.2.3.2 of Airbus AOT approved the incorporation by reference replacement. We are issuing this AD to A71N010–15, dated September 30, 2015. Do (IBR) of the service information listed in this prevent loss of an MLG door during all applicable corrective actions before paragraph under 5 U.S.C. 552(a) and 1 CFR flight, which could result in damage to further flight. part 51. the airplane. (i) Parts Installation Limitation (2) You must use this service information DATES: This AD becomes effective as applicable to do the actions required by As of the effective date of this AD, this AD, unless this AD specifies otherwise. February 25, 2016. installation of a CFM56–5A engine on an (i) Airbus Alert Operators Transmission The Director of the Federal Register airplane is permitted, provided that the (AOT) A71N010–15, dated September 30, approved the incorporation by reference installation is accomplished using the torque 2015. of certain publications listed in this AD values for forward engine mount bolts (ii) Reserved. as of February 25, 2016. specified in paragraph 4.2.3.1 of Airbus AOT (3) For service information identified in ADDRESSES: You may examine the AD A71N010–15, dated September 30, 2015. this AD, contact Airbus, Airworthiness docket on the Internet at http:// Note 1 to paragraph (i) of this AD: Office–EIAS, 1 Rond Point Maurice Bellonte, www.regulations.gov/ Additional guidance for the re-torque can be 31707 Blagnac Cedex, France; telephone +33 found in Airbus A318/A319/A320/A321 5 61 93 36 96; fax +33 5 61 93 44 51; email #!docketDetail;D=FAA-2015-1987; or in AMM, Task 71–00–00–400–040–A01, account.airworth-eas@airbus.com; Internet person at the Docket Management ‘‘Installation of the Power Plant with Engine http://www.airbus.com. Facility, U.S. Department of Positioner TWW 75E,’’ dated August 2015. (4) You may view this service information Transportation, Docket Operations, M– at the FAA, Transport Airplane Directorate, 30, West Building Ground Floor, Room (j) Special Flight Permits 1601 Lind Avenue SW., Renton, WA. For W12–140, 1200 New Jersey Avenue SE., Special flight permits, as described in information on the availability of this Washington, DC. Section 21.197 and Section 21.199 of the material at the FAA, call 425–227–1221. For service information identified in Federal Aviation Regulations (14 CFR 21.197 (5) You may view this service information this AD, contact Bombardier, Inc., 400 and 21.199), are not allowed. that is incorporated by reference at the Côte-Vertu Road West, Dorval, Québec National Archives and Records (k) Other FAA AD Provisions Administration (NARA). For information on H4S 1Y9, Canada; telephone 514–855– The following provisions also apply to this the availability of this material at NARA, call 5000; fax 514–855–7401; email thd.crj@ AD: 202–741–6030, or go to: http:// aero.bombardier.com; Internet http:// (1) Alternative Methods of Compliance www.archives.gov/federal-register/cfr/ibr- www.bombardier.com. You may view (AMOCs): The Manager, International locations.html. this referenced service information at Branch, ANM–116, Transport Airplane Issued in Renton, Washington, on the FAA, Transport Airplane Directorate, FAA, has the authority to December 28, 2015. Directorate, 1601 Lind Avenue SW., approve AMOCs for this AD, if requested Renton, WA. For information on the Phil Forde, using the procedures found in 14 CFR 39.19. availability of this material at the FAA, In accordance with 14 CFR 39.19, send your Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. call 425–227–1221. It is also available request to your principal inspector or local on the Internet at http:// Flight Standards District Office, as [FR Doc. 2016–01110 Filed 1–20–16; 8:45 am] appropriate. If sending information directly www.regulations.gov by searching for BILLING CODE 4910–13–P to the International Branch, send it to ATTN: and locating Docket No. FAA–2015– Sanjay Ralhan, Aerospace Engineer, 1987. International Branch, ANM–116, Transport DEPARTMENT OF TRANSPORTATION FOR FURTHER INFORMATION CONTACT: Aziz Airplane Directorate, FAA, 1601 Lind Ahmed, Aerospace Engineer, ANE–171, Avenue SW., Renton, WA 98057–3356; Federal Aviation Administration FAA, New York Aircraft Certification telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116- Office, 1600 Stewart Avenue, Suite 410, 14 CFR Part 39 Westbury, NY 11590; phone 516–228– AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate [Docket No. FAA–2015–1987; Directorate 7329; fax 516–794–5531. principal inspector, or lacking a principal Identifier 2014–NM–240–AD; Amendment SUPPLEMENTARY INFORMATION: inspector, the manager of the local flight 39–18377; AD 2016–01–17] standards district office/certificate holding Discussion district office. The AMOC approval letter RIN 2120–AA64 We issued a notice of proposed must specifically reference this AD. rulemaking (NPRM) to amend 14 CFR (2) Contacting the Manufacturer: For any Airworthiness Directives; Bombardier, part 39 by adding an AD that would requirement in this AD to obtain corrective Inc. Airplanes apply to certain Bombardier, Inc. Model actions from a manufacturer, the action must CL–600–2C10 (Regional Jet Series 700, AGENCY: Federal Aviation be accomplished using a method approved by the Manager, International Branch, ANM– Administration (FAA), Department of 701, & 702) airplanes. The NPRM 116, Transport Airplane Directorate, FAA; or Transportation (DOT). published in the Federal Register on the European Aviation Safety Agency ACTION: Final rule. June 30, 2015 (80 FR 37200). The NPRM (EASA); or Airbus’s EASA Design was prompted by reports of cracked Organization Approval (DOA). If approved by SUMMARY: We are adopting a new forward door members of the inboard the DOA, the approval must include the airworthiness directive (AD) for certain MLG doors. The NPRM proposed to DOA-authorized signature. Bombardier, Inc. Model CL–600–2C10 require repetitive inspections of the (l) Related Information (Regional Jet Series 700, 701, & 702) inboard MLG doors, repairs if necessary, jstallworth on DSK7TPTVN1PROD with RULES airplanes. This AD was prompted by and replacement of the inboard MLG Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD reports of cracked forward door doors. The NPRM also proposed 2015–0229, dated November 27, 2015, for members of the inboard main landing optional terminating action for the door related information. You may examine the gear (MLG) doors. This AD requires replacement. We are issuing this AD to MCAI on the Internet at http:// repetitive inspections of the inboard prevent loss of an MLG door during www.regulations.gov by searching for and MLG doors, repairs if necessary, and flight, which could result in damage to locating Docket No. FAA–2015–8433. replacement of the inboard MLG doors. the airplane. VerDate Sep<11>2014 15:08 Jan 20, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\21JAR1.SGM 21JAR1


Document Created: 2018-02-02 12:34:11
Document Modified: 2018-02-02 12:34:11
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD becomes effective February 5, 2016.
ContactSanjay 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.
FR Citation81 FR 3294 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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