81_FR_59703 81 FR 59535 - Airworthiness Directives; Airbus Airplanes

81 FR 59535 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 168 (August 30, 2016)

Page Range59535-59539
FR Document2016-20681

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. The proposed AD was prompted by fatigue load analysis that determined the need for certain reduced inspection intervals and updated torque values of the forward mount pylon bolts. This proposed AD would require repetitive torque checks to determine if there are any loose or broken forward engine mount bolts, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. We are proposing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in flight, and damage to the airplane.

Federal Register, Volume 81 Issue 168 (Tuesday, August 30, 2016)
[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)]
[Proposed Rules]
[Pages 59535-59539]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-20681]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-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 A330-223F, -223, -321, -322, and -323 airplanes. The 
proposed AD was prompted by fatigue load analysis that determined the 
need for certain reduced inspection intervals and updated torque values 
of the forward mount pylon bolts. This proposed AD would require 
repetitive torque checks to determine if there are any loose or broken 
forward engine mount bolts, and, if necessary, replacement of all four 
forward engine mount bolts and associated nuts, inspection of the 
forward mount assembly, and repair. We are proposing this AD to detect 
and correct loose or broken bolts, which could lead to engine 
detachment in flight, and damage to the airplane.

DATES: We must receive comments on this proposed AD by October 14, 
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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
45 80; 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

[[Page 59536]]

the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8849; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8849; 
Directorate Identifier 2015-NM-174-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 21, 2013, we issued AD 2013-14-04, Amendment 39-17509 (78 
FR 68352, November 14, 2013) (``AD 2013-14-04''). AD 2013-14-04 
requires actions intended to address the unsafe condition identified in 
this NPRM on all Airbus Model A330-223F, -223, -321, -322, and -323 
airplanes.
    Since we issued AD 2013-14-04, we have determined that it is 
necessary to update the torque values of the forward mount pylon bolts.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0214, dated October 19, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330-223F, -223, -321, 
-322, and -323 airplanes. The MCAI states:

    The forward mount engine pylon bolts, Part Number (P/N) 51U615, 
fitted on Airbus A330 aeroplanes with Pratt & Whitney (PW) PW4000 
engines, are made from MP159 material. Analysis made by PW 
identified that MP159 material pylon bolts do not meet the full life 
cycle torque check interval requirement, in a bolt-out condition. 
Consequently, PW issued Alert Service Bulletin (ASB) PW4G-100-A71-
32, and the U.S. Federal Aviation Administration (FAA), as Engine 
Certification Authority, issued FAA AD 2006-16-05 [Amendment 39-
14705 (71 FR 44185, August 4, 2006) (``AD 2006-16-05'')] to require 
repetitive torque checks of MP159 material forward mount pylon bolts 
fitted on certain PW4000 series engines.
    However, the engine mount system is considered to be part of 
aeroplane certification rather than the engine certification. 
Following further fatigue load analysis by Airbus of the A330 engine 
mount system, it was determined that the torque check interval for 
MP159 material forward mount pylon bolts, as required by FAA AD 
2006-16-05 (2,700 flight cycles (FC)), provided an insufficient 
level of safety for Airbus A330 aeroplanes.
    This condition, if not detected and corrected, could ultimately 
lead to detachment of the engine from the aeroplane, possibly 
resulting in damage to the aeroplane and/or injury to persons on the 
ground.
    Consequently, EASA issued AD 2012-0094 [which corresponds to FAA 
AD 2013-14-04] to require accomplishment of repetitive torque checks 
of the forward mount pylon bolts installed on affected A330 
aeroplanes and, depending on findings, replacement of all four bolts 
and associated nuts, in accordance with PW ASB PW4G-100-A71-32 
Revision 01 and Airbus Service Bulletin (SB) A330-71-3028.
    Since that AD was issued, it has been concluded that a new 
torque value must be applied.
    Consequently, Airbus issued SB A330-71-3028 Revision 02 and PW 
issued ASB PW4G-100-A71-32 Revision 02 to update the torque value. 
Additional forward mount inspections are also provided in case of 
one or more forward engine mount bolts is found loose, broken or 
missing.
    For the reasons described above, this AD retains the 
requirements of EASA AD 2012-0094, which is superseded, introduces a 
new torque value, and requires additional inspections and, depending 
on findings, corrective action(s).

    Corrective actions include repetitive torque checks to determine if 
there are any loose or broken forward engine mount bolts on both 
engines, and, if necessary, replacement of all four forward engine 
mount bolts and associated nuts, inspection of the forward mount 
assembly, and repair. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-8849.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-71-3028, Revision 02, dated 
August 31, 2015. The service information describes procedures for 
repetitive torque checks to determine if there are any loose or broken 
forward engine mount bolts on both engines, replacement of all four 
forward engine mount bolts and associated nuts, and inspection of the 
forward mount assembly. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 41 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 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 $6,747 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $287,082, or $7,002 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 1 work-hour and require parts costing $6,747, for a cost of 
$6,832 per product. We have no way of determining the number of 
aircraft that might need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII:

[[Page 59537]]

Aviation Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-
174-AD.

(a) Comments Due Date

    We must receive comments by October 14, 2016.

(b) Affected ADs

    This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, 
August 4, 2006) (``AD 2006-16-05''); and AD 2013-14-04, Amendment 
39-17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'').

(c) Applicability

    This AD applies to Airbus Model A330-223F, -223, -321, -322, and 
-323 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by fatigue load analysis that determined 
the need for certain reduced inspection intervals and updated torque 
values of the forward mount pylon bolts. We are issuing this AD to 
detect and correct loose or broken bolts, which could lead to engine 
detachment in flight, and damage to the airplane.

(f) Compliance

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

(g) Torque Check and Replacement

    (1) At the applicable compliance time specified in table 1 to 
paragraph (g) of this AD, do a torque check to determine if there 
are any loose or broken forward engine mount bolts (4 positions/
engine) on both engines, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, 
dated August 31, 2015. Repeat the torque check at the applicable 
time intervals not to exceed the values specified in table 1 to 
paragraph (g) of this AD. For the purposes of this AD, the average 
flight time (AFT) is defined as a computation of the number of 
flight hours divided by the number of flight cycles accumulated 
since the most recent torque check or since the airplane's first 
flight, as applicable. Accomplishment of the initial torque check 
required by this AD terminates the requirements of AD 2013-14-05.

                                       Table 1 to Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
                                          Flight cycles
                                        accumulated as of
                                      December 19, 2013 (the
                                       effective date of AD
                                       2013-14-04), either
                                     since last torque check                               Torque check interval
          Airplane models              specified in Pratt &         Compliance time           (not to exceed)
                                      Whitney Alert Service
                                      Bulletin PW4G-100-A71-
                                     32, or since airplane's
                                         first flight, as
                                            applicable
----------------------------------------------------------------------------------------------------------------
Model A330-321, -322, and -323       0-1,850................  Within 2,350 flight cycles   2,350 flight cycles
 airplanes with AFT more than 132                              since the last torque        or 24,320 flight
 minutes; and Model A330-223                                   check as specified in        hours, whichever
 airplanes.                                                    Pratt & Whitney Alert        occurs first.
                                                               Service Bulletin PW4G-100-
                                                               A71-32, or since
                                                               airplane's first flight,
                                                               as applicable.
Model A330-321, -322, and -323       1,851-2,700............  Within 500 flight cycles     2,350 flight cycles
 airplanes with AFT more than 132                              after December 19, 2013      or 24,320 flight
 minutes; and Model A330-223                                   (the effective date of AD    hours, whichever
 airplanes.                                                    2013-14-04), without         occurs first.
                                                               exceeding 2,700 flight
                                                               cycles since last torque
                                                               check as specified in
                                                               Pratt & Whitney Alert
                                                               Service Bulletin PW4G-100-
                                                               A71-32, or since
                                                               airplane's first flight,
                                                               as applicable; or within 3
                                                               months after December 19,
                                                               2013; whichever occurs
                                                               later.

[[Page 59538]]

 
Model A330-321, -322, and -323       0-1,450................  Within 1,950 flight cycles   1,950 flight cycles
 airplanes with AFT 132 minutes or                             since the last torque        or 20,210 flight
 less; and Model A330-321, -322,                               check performed as           hours, whichever
 and -323 airplanes on which the                               specified in Pratt &         occurs first.
 AFT is not calculated on a regular                            Whitney Alert Service
 basis.                                                        Bulletin PW4G-100-A71-32,
                                                               or since airplane's first
                                                               flight, as applicable.
Model A330-321, -322, and -323       1,451-2,700............  Within 500 flight cycles     1,950 flight cycles
 airplanes with AFT 132 minutes or                             after December 19, 2013      or 20,210 flight
 less; and Model A330-321,-322, and                            (the effective date of AD    hours, whichever
 -323 airplanes on which the AFT is                            2013-14-04), without         occurs first.
 not calculated on a regular basis.                            exceeding 2,700 flight
                                                               cycles since last torque
                                                               check performed as
                                                               specified in Pratt &
                                                               Whitney Alert Service
                                                               Bulletin PW4-100-A71-32,
                                                               or since airplane's first
                                                               flight, as applicable; or
                                                               within 3 months after
                                                               December 19, 2013;
                                                               whichever occurs later.
Model A330-223F airplanes..........  Any....................  Within 2,140 flight cycles   2,140 flight cycles
                                                               or 6,600 flight hours,       or 6,600 flight
                                                               whichever occurs first       hours, whichever
                                                               since the last torque        occurs first.
                                                               check performed as
                                                               specified in Pratt &
                                                               Whitney Alert Service
                                                               Bulletin PW4G-100-A71-32,
                                                               or since airplane's first
                                                               flight, as applicable.
----------------------------------------------------------------------------------------------------------------

    (2) If any loose or broken bolt is detected during the check 
required by paragraph (g)(1) of this AD, before further flight, do 
the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015; 
except, where the service information specifies to contact the 
manufacturer for further actions, this AD requires repair before 
further flight 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).
    (i) Replace all four forward engine mount bolts and associated 
nuts, on the engine where the loose or broken bolt was detected, 
with new bolts and nuts.
    (ii) Do nondestructive inspections of the forward mount assembly 
for damage including cracks, dents, nicks, and scratches, and do all 
applicable corrective actions.
    (3) Replacement of bolts and nuts as required by paragraph 
(g)(2)(i) of this AD is not terminating action for the repetitive 
torque checks required by paragraph (g)(1) of this AD.

(h) Provisions for Compliance With AD 2006-16-05

    Accomplishment of the actions required by paragraph (g) of this 
AD constitutes compliance with the requirements specified in 
paragraph (g) of AD 2006-16-05.

(i) Parts Installation Prohibition

    As of December 19, 2013 (the effective date of AD 2013-14-04), 
no person may install any INCO718 material, forward mount pylon bolt 
having Pratt & Whitney part number 54T670 on any airplane.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g)(1) and (g)(2)(i) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-71-3028, dated December 16, 2011, or Airbus Service 
Bulletin A330-71-3028, Revision 01, dated February 20, 2012. This 
service information is not incorporated by reference in 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; 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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (g)(2) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) 2015-0214, dated October 19, 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-
2016-8849.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email:

[[Page 59539]]

[email protected]; Internet: http://www.airbus.com. 
You may view this service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on August 18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20681 Filed 8-29-16; 8:45 am]
 BILLING CODE 4910-13-P



                                                                           Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules                                          59535

                                                    (h) Repair of the Skin Inner Surface                    or lacking a principal inspector, the manager         DEPARTMENT OF TRANSPORTATION
                                                      If any damage is found during any                     of the local flight standards district office/
                                                    inspection required by paragraph (g) of this            certificate holding district office.                  Federal Aviation Administration
                                                    AD, before further flight, do all applicable               (3) An AMOC that provides an acceptable
                                                    related investigative and correction actions,           level of safety may be used for any repair,           14 CFR Part 39
                                                    in accordance with the Accomplishment                   modification, or alteration required by this
                                                    Instructions of Boeing Alert Service Bulletin                                                                 [Docket No. FAA–2016–8849; Directorate
                                                                                                            AD if it is approved by the Boeing
                                                    747–53A2878, dated May 19, 2016, except as                                                                    Identifier 2015–NM–174–AD]
                                                                                                            Commercial Airplanes Organization
                                                    required by paragraph (k)(2) of this AD.                                                                      RIN 2120–AA64
                                                                                                            Designation Authorization (ODA) that has
                                                    (i) Terminating Action                                  been authorized by the Manager, Seattle
                                                       Modification or repair of the inner skin             ACO, to make those findings. To be                    Airworthiness Directives; Airbus
                                                    surfaces in accordance with Part 3 of the               approved, the repair method, modification             Airplanes
                                                    Accomplishment Instructions of Boeing Alert             deviation, or alteration deviation must meet          AGENCY: Federal Aviation
                                                    Service Bulletin 747–53A2878, May 19, 2016,             the certification basis of the airplane, and the
                                                    terminates the repetitive inspections required
                                                                                                                                                                  Administration (FAA), DOT.
                                                                                                            approval must specifically refer to this AD.
                                                    by paragraph (g) of this AD.                               (4) Except as required by paragraph (k)(1)         ACTION: Notice of proposed rulemaking
                                                                                                            and (k)(2) of this AD: For service information        (NPRM).
                                                    (j) Post Repair Inspection and Repairs
                                                                                                            that contains steps that are labeled as               SUMMARY:   We propose to adopt a new
                                                       For airplanes on which a repair or
                                                                                                            Required for Compliance (RC), the provisions
                                                    modification has been done in accordance                                                                      airworthiness directive (AD) for all
                                                    with the Accomplishment Instructions of                 of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
                                                                                                                                                                  Airbus Model A330–223F, –223, –321,
                                                    Boeing Alert Service Bulletin 747–53A2878,              apply.
                                                                                                                                                                  –322, and –323 airplanes. The proposed
                                                    dated May 19, 2016: Except as required by                  (i) The steps labeled as RC, including
                                                                                                                                                                  AD was prompted by fatigue load
                                                    paragraph (k)(1) of this AD, at the applicable          substeps under an RC step and any figures
                                                                                                                                                                  analysis that determined the need for
                                                    time specified in table 3 of paragraph 1.E.,            identified in an RC step, must be done to
                                                    ‘‘Compliance,’’ of Boeing Alert Service                                                                       certain reduced inspection intervals and
                                                                                                            comply with the AD. An AMOC is required
                                                    Bulletin 747–53A2878, dated May 19, 2016,                                                                     updated torque values of the forward
                                                                                                            for any deviations to RC steps, including
                                                    do detailed inspections to detect damage of             substeps and identified figures.
                                                                                                                                                                  mount pylon bolts. This proposed AD
                                                    the repaired or modified areas, and do all                 (ii) Steps not labeled as RC may be
                                                                                                                                                                  would require repetitive torque checks
                                                    applicable corrective actions, in accordance
                                                                                                            deviated from using accepted methods in               to determine if there are any loose or
                                                    with Part 5 of the Accomplishment                                                                             broken forward engine mount bolts,
                                                    Instructions of Boeing Alert Service Bulletin           accordance with the operator’s maintenance
                                                                                                            or inspection program without obtaining               and, if necessary, replacement of all four
                                                    747–53A2878, May 19, 2016, except as                                                                          forward engine mount bolts and
                                                    required by paragraph (k)(2) of this AD. Do             approval of an AMOC, provided the RC steps,
                                                                                                            including substeps and identified figures, can        associated nuts, inspection of the
                                                    all applicable corrective actions before
                                                    further flight. Repeat the inspections                  still be done as specified, and the airplane          forward mount assembly, and repair.
                                                    thereafter at intervals not to exceed the               can be put back in an airworthy condition.            We are proposing this AD to detect and
                                                    applicable time specified in paragraph 1.E.,                                                                  correct loose or broken bolts, which
                                                    ‘‘Compliance,’’ of Boeing Alert Service                 (m) Related Information                               could lead to engine detachment in
                                                    Bulletin 747–53A2878, dated May 19, 2016.                  (1) For more information about this AD,            flight, and damage to the airplane.
                                                    (k) Exceptions                                          contact Nathan Weigand, Aerospace                     DATES: We must receive comments on
                                                                                                            Engineer, Airframe Branch, ANM–120S,                  this proposed AD by October 14, 2016.
                                                       (1) Where Boeing Alert Service Bulletin
                                                                                                            FAA, Seattle ACO, 1601 Lind Avenue SW.,               ADDRESSES: You may send comments,
                                                    747–53A2878, May 19, 2016, specifies a
                                                                                                            Renton, WA 98057–3356; phone: 425–917–
                                                    compliance time ‘‘after the original issue date                                                               using the procedures found in 14 CFR
                                                    of this service bulletin,’’ this AD requires            6428; fax: 425–917–6590; email:
                                                                                                                                                                  11.43 and 11.45, by any of the following
                                                    compliance within the specified compliance              nathan.p.weigand@faa.gov.
                                                                                                                                                                  methods:
                                                                                                               (2) For service information identified in
                                                    time after the effective date of this AD.                                                                        • Federal eRulemaking Portal: Go to
                                                       (2) If any cracking or corrosion is found            this AD, contact Boeing Commercial
                                                                                                                                                                  http://www.regulations.gov. Follow the
                                                    during any inspection required by this AD,              Airplanes, Attention: Data & Services
                                                    and Boeing Alert Service Bulletin 747–
                                                                                                                                                                  instructions for submitting comments.
                                                                                                            Management, P.O. Box 3707, MC 2H–65,
                                                    53A2878, May 19, 2016, specifies to contact                                                                      • Fax: 202–493–2251.
                                                                                                            Seattle, WA 98124–2207; telephone 206–
                                                    Boeing for appropriate action: Before further                                                                    • Mail: U.S. Department of
                                                                                                            544–5000, extension 1; fax 206–766–5680;
                                                    flight, repair the cracking or corrosion using                                                                Transportation, Docket Operations, M–
                                                                                                            Internet https://www.myboeingfleet.com. You
                                                    a method approved in accordance with the                                                                      30, West Building Ground Floor, Room
                                                                                                            may view this referenced service information
                                                    procedures specified in paragraph (l) of this
                                                                                                            at the FAA, Transport Airplane Directorate,
                                                                                                                                                                  W12–140, 1200 New Jersey Avenue SE.,
                                                    AD.                                                                                                           Washington, DC 20590.
                                                                                                            1601 Lind Avenue SW., Renton, WA. For
                                                    (l) Alternative Methods of Compliance                   information on the availability of this
                                                                                                                                                                     • Hand Delivery: Deliver to Mail
                                                    (AMOCs)                                                 material at the FAA, call 425–227–1221.               address above between 9 a.m. and 5
                                                       (1) The Manager, Seattle Aircraft                                                                          p.m., Monday through Friday, except
                                                                                                              Issued in Renton, Washington, on August             Federal holidays.
                                                    Certification Office (ACO), FAA, has the
                                                                                                            18, 2016.                                                For service information identified in
                                                    authority to approve AMOCs for this AD, if
                                                    requested using the procedures found in 14              Dorr M. Anderson,                                     this NPRM, contact Airbus SAS,
                                                    CFR 39.19. In accordance with 14 CFR 39.19,             Acting Manager, Transport Airplane                    Airworthiness Office—EAL, 1 Rond
                                                    send your request to your principal inspector           Directorate, Aircraft Certification Service.          Point Maurice Bellonte, 31707 Blagnac
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                                                    or local Flight Standards District Office, as           [FR Doc. 2016–20683 Filed 8–29–16; 8:45 am]           Cedex, France; telephone: +33 5 61 93
                                                    appropriate. If sending information directly                                                                  36 96; fax: +33 5 61 93 45 80; email:
                                                    to the manager of the ACO, send it to the               BILLING CODE 4910–13–P
                                                                                                                                                                  airworthiness.A330–A340@airbus.com;
                                                    attention of the person identified in
                                                    paragraph (m)(1) of this AD. Information may                                                                  Internet: http://www.airbus.com. You
                                                    be emailed to: 9-ANM-Seattle-ACO-AMOC-                                                                        may view this referenced service
                                                    Requests@faa.gov.                                                                                             information at the FAA, Transport
                                                       (2) Before using any approved AMOC,                                                                        Airplane Directorate, 1601 Lind Avenue
                                                    notify your appropriate principal inspector,                                                                  SW., Renton, WA. For information on


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                                                    59536                  Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules

                                                    the availability of this material at the                dated October 19, 2015 (referred to after             You may examine the MCAI in the AD
                                                    FAA, call 425–227–1221.                                 this as the Mandatory Continuing                      docket on the Internet at http://
                                                                                                            Airworthiness Information, or ‘‘the                   www.regulations.gov by searching for
                                                    Examining the AD Docket
                                                                                                            MCAI’’), to correct an unsafe condition               and locating Docket No. FAA–2016–
                                                       You may examine the AD docket on                     for all Airbus Model A330–223F, –223,                 8849.
                                                    the Internet at http://                                 –321, –322, and –323 airplanes. The
                                                    www.regulations.gov by searching for                                                                          Related Service Information Under 1
                                                                                                            MCAI states:
                                                    and locating Docket No. FAA–2016–                                                                             CFR Part 51
                                                                                                               The forward mount engine pylon bolts,
                                                    8849; or in person at the Docket                        Part Number (P/N) 51U615, fitted on Airbus              Airbus has issued Service Bulletin
                                                    Management Facility between 9 a.m.                      A330 aeroplanes with Pratt & Whitney (PW)             A330–71–3028, Revision 02, dated
                                                    and 5 p.m., Monday through Friday,                      PW4000 engines, are made from MP159                   August 31, 2015. The service
                                                    except Federal holidays. The AD docket                  material. Analysis made by PW identified              information describes procedures for
                                                    contains this proposed AD, the                          that MP159 material pylon bolts do not meet           repetitive torque checks to determine if
                                                    regulatory evaluation, any comments                     the full life cycle torque check interval             there are any loose or broken forward
                                                    received, and other information. The                    requirement, in a bolt-out condition.                 engine mount bolts on both engines,
                                                    street address for the Docket Operations                Consequently, PW issued Alert Service
                                                                                                            Bulletin (ASB) PW4G–100–A71–32, and the
                                                                                                                                                                  replacement of all four forward engine
                                                    office (telephone: 800–647–5527) is in                                                                        mount bolts and associated nuts, and
                                                                                                            U.S. Federal Aviation Administration (FAA),
                                                    the ADDRESSES section. Comments will                    as Engine Certification Authority, issued             inspection of the forward mount
                                                    be available in the AD docket shortly                   FAA AD 2006–16–05 [Amendment 39–14705                 assembly. This service information is
                                                    after receipt.                                          (71 FR 44185, August 4, 2006) (‘‘AD 2006–             reasonably available because the
                                                    FOR FURTHER INFORMATION CONTACT:                        16–05’’)] to require repetitive torque checks         interested parties have access to it
                                                    Vladimir Ulyanov, Aerospace Engineer,                   of MP159 material forward mount pylon                 through their normal course of business
                                                    International Branch, ANM–116,                          bolts fitted on certain PW4000 series engines.        or by the means identified in the
                                                    Transport Airplane Directorate, FAA,                       However, the engine mount system is
                                                                                                                                                                  ADDRESSES section.
                                                                                                            considered to be part of aeroplane
                                                    1601 Lind Avenue SW., Renton, WA                        certification rather than the engine
                                                    98057–3356; telephone: 425–227–1138;                                                                          FAA’s Determination and Requirements
                                                                                                            certification. Following further fatigue load         of This Proposed AD
                                                    fax: 425–227–1149.                                      analysis by Airbus of the A330 engine mount
                                                    SUPPLEMENTARY INFORMATION:                              system, it was determined that the torque               This product has been approved by
                                                                                                            check interval for MP159 material forward             the aviation authority of another
                                                    Comments Invited                                        mount pylon bolts, as required by FAA AD              country, and is approved for operation
                                                      We invite you to send any written                     2006–16–05 (2,700 flight cycles (FC)),                in the United States. Pursuant to our
                                                    relevant data, views, or arguments about                provided an insufficient level of safety for          bilateral agreement with the State of
                                                    this proposed AD. Send your comments                    Airbus A330 aeroplanes.                               Design Authority, we have been notified
                                                                                                               This condition, if not detected and
                                                    to an address listed under the                          corrected, could ultimately lead to                   of the unsafe condition described in the
                                                    ADDRESSES section. Include ‘‘Docket No.                 detachment of the engine from the aeroplane,          MCAI and service information
                                                    FAA–2016–8849; Directorate Identifier                   possibly resulting in damage to the aeroplane         referenced above. We are proposing this
                                                    2015–NM–174–AD’’ at the beginning of                    and/or injury to persons on the ground.               AD because we evaluated all pertinent
                                                    your comments. We specifically invite                      Consequently, EASA issued AD 2012–0094             information and determined an unsafe
                                                    comments on the overall regulatory,                     [which corresponds to FAA AD 2013–14–04]              condition exists and is likely to exist or
                                                    economic, environmental, and energy                     to require accomplishment of repetitive               develop on other products of the same
                                                    aspects of this proposed AD. We will                    torque checks of the forward mount pylon              type design.
                                                                                                            bolts installed on affected A330 aeroplanes
                                                    consider all comments received by the                   and, depending on findings, replacement of            Costs of Compliance
                                                    closing date and may amend this                         all four bolts and associated nuts, in
                                                    proposed AD based on those comments.                    accordance with PW ASB PW4G–100–A71–                     We estimate that this proposed AD
                                                      We will post all comments we                          32 Revision 01 and Airbus Service Bulletin            affects 41 airplanes of U.S. registry.
                                                    receive, without change, to http://                     (SB) A330–71–3028.                                       We also estimate that it would take
                                                    www.regulations.gov, including any                         Since that AD was issued, it has been              about 3 work-hours per product to
                                                    personal information you provide. We                    concluded that a new torque value must be             comply with the basic requirements of
                                                    will also post a report summarizing each                applied.                                              this proposed AD. The average labor
                                                    substantive verbal contact we receive                      Consequently, Airbus issued SB A330–71–            rate is $85 per work-hour. Required
                                                                                                            3028 Revision 02 and PW issued ASB                    parts would cost about $6,747 per
                                                    about this proposed AD.                                 PW4G–100–A71–32 Revision 02 to update
                                                                                                            the torque value. Additional forward mount
                                                                                                                                                                  product. Based on these figures, we
                                                    Discussion                                                                                                    estimate the cost of this proposed AD on
                                                                                                            inspections are also provided in case of one
                                                      On June 21, 2013, we issued AD                        or more forward engine mount bolts is found           U.S. operators to be $287,082, or $7,002
                                                    2013–14–04, Amendment 39–17509 (78                      loose, broken or missing.                             per product.
                                                    FR 68352, November 14, 2013) (‘‘AD                         For the reasons described above, this AD              In addition, we estimate that any
                                                    2013–14–04’’). AD 2013–14–04 requires                   retains the requirements of EASA AD 2012–             necessary follow-on actions would take
                                                    actions intended to address the unsafe                  0094, which is superseded, introduces a new           about 1 work-hour and require parts
                                                    condition identified in this NPRM on all                torque value, and requires additional                 costing $6,747, for a cost of $6,832 per
                                                    Airbus Model A330–223F, –223, –321,                     inspections and, depending on findings,               product. We have no way of
                                                                                                            corrective action(s).
                                                    –322, and –323 airplanes.                                                                                     determining the number of aircraft that
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                                                      Since we issued AD 2013–14–04, we                       Corrective actions include repetitive               might need these actions.
                                                    have determined that it is necessary to                 torque checks to determine if there are
                                                    update the torque values of the forward                 any loose or broken forward engine                    Authority for This Rulemaking
                                                    mount pylon bolts.                                      mount bolts on both engines, and, if                    Title 49 of the United States Code
                                                      The European Aviation Safety Agency                   necessary, replacement of all four                    specifies the FAA’s authority to issue
                                                    (EASA), which is the Technical Agent                    forward engine mount bolts and                        rules on aviation safety. Subtitle I,
                                                    for the Member States of the European                   associated nuts, inspection of the                    section 106, describes the authority of
                                                    Union, has issued EASA AD 2015–0214,                    forward mount assembly, and repair.                   the FAA Administrator. ‘‘Subtitle VII:


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                                                                           Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules                                                     59537

                                                    Aviation Programs,’’ describes in more                      on a substantial number of small entities                certificated in any category, all manufacturer
                                                    detail the scope of the Agency’s                            under the criteria of the Regulatory                     serial numbers.
                                                    authority.                                                  Flexibility Act.                                         (d) Subject
                                                       We are issuing this rulemaking under
                                                    the authority described in ‘‘Subtitle VII,                  List of Subjects in 14 CFR Part 39                        Air Transport Association (ATA) of
                                                                                                                  Air transportation, Aircraft, Aviation                 America Code 71, Powerplant.
                                                    Part A, Subpart III, Section 44701:
                                                    General requirements.’’ Under that                          safety, Incorporation by reference,                      (e) Reason
                                                    section, Congress charges the FAA with                      Safety.                                                    This AD was prompted by fatigue load
                                                    promoting safe flight of civil aircraft in                  The Proposed Amendment                                   analysis that determined the need for certain
                                                    air commerce by prescribing regulations                                                                              reduced inspection intervals and updated
                                                    for practices, methods, and procedures                        Accordingly, under the authority                       torque values of the forward mount pylon
                                                    the Administrator finds necessary for                       delegated to me by the Administrator,                    bolts. We are issuing this AD to detect and
                                                    safety in air commerce. This regulation                     the FAA proposes to amend 14 CFR part                    correct loose or broken bolts, which could
                                                    is within the scope of that authority                       39 as follows:                                           lead to engine detachment in flight, and
                                                    because it addresses an unsafe condition                                                                             damage to the airplane.
                                                    that is likely to exist or develop on                       PART 39—AIRWORTHINESS
                                                                                                                DIRECTIVES                                               (f) Compliance
                                                    products identified in this rulemaking
                                                                                                                                                                           Comply with this AD within the
                                                    action.                                                     ■ 1. The authority citation for part 39                  compliance times specified, unless already
                                                    Regulatory Findings                                         continues to read as follows:                            done.
                                                      We determined that this proposed AD                           Authority: 49 U.S.C. 106(g), 40113, 44701.           (g) Torque Check and Replacement
                                                    would not have federalism implications                      § 39.13      [Amended]                                      (1) At the applicable compliance time
                                                    under Executive Order 13132. This                                                                                    specified in table 1 to paragraph (g) of this
                                                                                                                ■ 2. The FAA amends § 39.13 by adding
                                                    proposed AD would not have a                                                                                         AD, do a torque check to determine if there
                                                                                                                the following new airworthiness
                                                    substantial direct effect on the States, on                                                                          are any loose or broken forward engine
                                                                                                                directive (AD):                                          mount bolts (4 positions/engine) on both
                                                    the relationship between the national
                                                    Government and the States, or on the                        Airbus: Docket No. FAA–2016–8849;                        engines, in accordance with the
                                                    distribution of power and                                       Directorate Identifier 2015–NM–174–AD.               Accomplishment Instructions of Airbus
                                                    responsibilities among the various                          (a) Comments Due Date                                    Service Bulletin A330–71–3028, Revision 02,
                                                                                                                                                                         dated August 31, 2015. Repeat the torque
                                                    levels of government.                                         We must receive comments by October 14,                check at the applicable time intervals not to
                                                      For the reasons discussed above, I                        2016.                                                    exceed the values specified in table 1 to
                                                    certify this proposed regulation:                                                                                    paragraph (g) of this AD. For the purposes of
                                                      1. Is not a ‘‘significant regulatory                      (b) Affected ADs
                                                                                                                   This AD affects AD 2006–16–05,                        this AD, the average flight time (AFT) is
                                                    action’’ under Executive Order 12866;                                                                                defined as a computation of the number of
                                                      2. Is not a ‘‘significant rule’’ under the                Amendment 39–14705 (71 FR 44185, August
                                                                                                                4, 2006) (‘‘AD 2006–16–05’’); and AD 2013–               flight hours divided by the number of flight
                                                    DOT Regulatory Policies and Procedures                                                                               cycles accumulated since the most recent
                                                                                                                14–04, Amendment 39–17509 (78 FR 68352,
                                                    (44 FR 11034, February 26, 1979);                           November 14, 2013) (‘‘AD 2013–14–04’’).                  torque check or since the airplane’s first
                                                      3. Will not affect intrastate aviation in                                                                          flight, as applicable. Accomplishment of the
                                                    Alaska; and                                                 (c) Applicability                                        initial torque check required by this AD
                                                      4. Will not have a significant                               This AD applies to Airbus Model A330–                 terminates the requirements of AD 2013–14–
                                                    economic impact, positive or negative,                      223F, –223, –321, –322, and –323 airplanes,              05.

                                                                                                               TABLE 1 TO PARAGRAPH (g) OF THIS AD
                                                                                    Flight cycles accumulated as of
                                                                                    December 19, 2013 (the effec-
                                                                                     tive date of AD 2013–14–04),
                                                                                     either since last torque check                                                                            Torque check interval
                                                          Airplane models                                                                              Compliance time
                                                                                       specified in Pratt & Whitney                                                                               (not to exceed)
                                                                                     Alert Service Bulletin PW4G–
                                                                                        100–A71–32, or since air-
                                                                                    plane’s first flight, as applicable

                                                    Model A330–321, –322,           0–1,850 .....................................   Within 2,350 flight cycles since the last torque check   2,350 flight cycles or
                                                     and –323 airplanes with                                                         as specified in Pratt & Whitney Alert Service Bul-        24,320 flight hours,
                                                     AFT more than 132                                                               letin PW4G–100–A71–32, or since airplane’s first          whichever occurs first.
                                                     minutes; and Model                                                              flight, as applicable.
                                                     A330–223 airplanes.
                                                    Model A330–321, –322,           1,851–2,700 ..............................      Within 500 flight cycles after December 19, 2013         2,350 flight cycles or
                                                     and –323 airplanes with                                                         (the effective date of AD 2013–14–04), without ex-        24,320 flight hours,
                                                     AFT more than 132                                                               ceeding 2,700 flight cycles since last torque check       whichever occurs first.
                                                     minutes; and Model                                                              as specified in Pratt & Whitney Alert Service Bul-
                                                     A330–223 airplanes.                                                             letin PW4G–100–A71–32, or since airplane’s first
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                                                                                                                                     flight, as applicable; or within 3 months after De-
                                                                                                                                     cember 19, 2013; whichever occurs later.




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                                                    59538                  Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules

                                                                                                     TABLE 1 TO PARAGRAPH (g) OF THIS AD—Continued
                                                                                    Flight cycles accumulated as of
                                                                                    December 19, 2013 (the effec-
                                                                                     tive date of AD 2013–14–04),
                                                                                     either since last torque check                                                                               Torque check interval
                                                          Airplane models                                                                                 Compliance time
                                                                                       specified in Pratt & Whitney                                                                                  (not to exceed)
                                                                                     Alert Service Bulletin PW4G–
                                                                                        100–A71–32, or since air-
                                                                                    plane’s first flight, as applicable

                                                    Model A330–321, –322,           0–1,450 .....................................      Within 1,950 flight cycles since the last torque check   1,950 flight cycles or
                                                     and –323 airplanes with                                                            performed as specified in Pratt & Whitney Alert           20,210 flight hours,
                                                     AFT 132 minutes or                                                                 Service Bulletin PW4G–100–A71–32, or since air-           whichever occurs first.
                                                     less; and Model A330–                                                              plane’s first flight, as applicable.
                                                     321, –322, and –323
                                                     airplanes on which the
                                                     AFT is not calculated on
                                                     a regular basis.
                                                    Model A330–321, –322,           1,451–2,700 ..............................         Within 500 flight cycles after December 19, 2013         1,950 flight cycles or
                                                     and –323 airplanes with                                                            (the effective date of AD 2013–14–04), without ex-        20,210 flight hours,
                                                     AFT 132 minutes or                                                                 ceeding 2,700 flight cycles since last torque check       whichever occurs first.
                                                     less; and Model A330–                                                              performed as specified in Pratt & Whitney Alert
                                                     321,–322, and –323 air-                                                            Service Bulletin PW4–100–A71–32, or since air-
                                                     planes on which the                                                                plane’s first flight, as applicable; or within 3
                                                     AFT is not calculated on                                                           months after December 19, 2013; whichever oc-
                                                     a regular basis.                                                                   curs later.
                                                    Model A330–223F air-            Any ............................................   Within 2,140 flight cycles or 6,600 flight hours,        2,140 flight cycles or
                                                     planes.                                                                            whichever occurs first since the last torque check        6,600 flight hours,
                                                                                                                                        performed as specified in Pratt & Whitney Alert           whichever occurs first.
                                                                                                                                        Service Bulletin PW4G–100–A71–32, or since air-
                                                                                                                                        plane’s first flight, as applicable.



                                                       (2) If any loose or broken bolt is detected                bolt having Pratt & Whitney part number                      (2) Contacting the Manufacturer: As of the
                                                    during the check required by paragraph (g)(1)                 54T670 on any airplane.                                   effective date of this AD, for any requirement
                                                    of this AD, before further flight, do the                                                                               in this AD to obtain corrective actions from
                                                                                                                  (j) Credit for Previous Actions                           a manufacturer, the action must be
                                                    actions specified by paragraphs (g)(2)(i) and
                                                    (g)(2)(ii) of this AD, in accordance with the                    This paragraph provides credit for the                 accomplished using a method approved by
                                                    Accomplishment Instructions of Airbus                         actions required by paragraphs (g)(1) and                 the Manager, International Branch, ANM–
                                                    Service Bulletin A330–71–3028, Revision 02,                   (g)(2)(i) of this AD, if those actions were               116, Transport Airplane Directorate, FAA; or
                                                    dated August 31, 2015; except, where the                      performed before the effective date of this AD            EASA; or Airbus’s EASA Design
                                                    service information specifies to contact the                  using Airbus Service Bulletin A330–71–3028,               Organization Approval (DOA). If approved by
                                                    manufacturer for further actions, this AD                     dated December 16, 2011, or Airbus Service                the DOA, the approval must include the
                                                                                                                  Bulletin A330–71–3028, Revision 01, dated                 DOA-authorized signature.
                                                    requires repair before further flight using a
                                                                                                                  February 20, 2012. This service information                  (3) Required for Compliance (RC): Except
                                                    method approved by the Manager,
                                                                                                                  is not incorporated by reference in this AD.              as required by paragraph (g)(2) of this AD: If
                                                    International Branch, ANM–116, Transport
                                                                                                                                                                            any service information contains procedures
                                                    Airplane Directorate, FAA; or the European                    (k) Other FAA AD Provisions                               or tests that are identified as RC, those
                                                    Aviation Safety Agency (EASA); or Airbus’s                       The following provisions also apply to this            procedures and tests must be done to comply
                                                    EASA Design Organization Approval (DOA).                      AD:                                                       with this AD; any procedures or tests that are
                                                       (i) Replace all four forward engine mount                     (1) Alternative Methods of Compliance                  not identified as RC are recommended. Those
                                                    bolts and associated nuts, on the engine                      (AMOCs): The Manager, International                       procedures and tests that are not identified
                                                    where the loose or broken bolt was detected,                  Branch, ANM–116, Transport Airplane                       as RC may be deviated from using accepted
                                                    with new bolts and nuts.                                      Directorate, FAA, has the authority to                    methods in accordance with the operator’s
                                                       (ii) Do nondestructive inspections of the                  approve AMOCs for this AD, if requested                   maintenance or inspection program without
                                                    forward mount assembly for damage                             using the procedures found in 14 CFR 39.19.               obtaining approval of an AMOC, provided
                                                    including cracks, dents, nicks, and scratches,                In accordance with 14 CFR 39.19, send your                the procedures and tests identified as RC can
                                                    and do all applicable corrective actions.                     request to your principal inspector or local              be done and the airplane can be put back in
                                                       (3) Replacement of bolts and nuts as                       Flight Standards District Office, as                      an airworthy condition. Any substitutions or
                                                    required by paragraph (g)(2)(i) of this AD is                 appropriate. If sending information directly              changes to procedures or tests identified as
                                                    not terminating action for the repetitive                     to the International Branch, send it to ATTN:             RC require approval of an AMOC.
                                                    torque checks required by paragraph (g)(1) of                 Vladimir Ulyanov, Aerospace Engineer,
                                                    this AD.                                                      International Branch, ANM–116, Transport                  (l) Related Information
                                                                                                                  Airplane Directorate, FAA, 1601 Lind                         (1) Refer to Mandatory Continuing
                                                    (h) Provisions for Compliance With AD                         Avenue SW., Renton, WA 98057–3356;                        Airworthiness Information (MCAI) 2015–
                                                    2006–16–05                                                    telephone: 425–227–1138; fax: 425–227–                    0214, dated October 19, 2015, for related
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                                                      Accomplishment of the actions required by                   1149. Information may be emailed to: 9-                   information. This MCAI may be found in the
                                                    paragraph (g) of this AD constitutes                          ANM-116-AMOC-REQUESTS@faa.gov.                            AD docket on the Internet at http://
                                                    compliance with the requirements specified                    Before using any approved AMOC, notify                    www.regulations.gov by searching for and
                                                    in paragraph (g) of AD 2006–16–05.                            your appropriate principal inspector, or                  locating Docket No. FAA–2016–8849.
                                                                                                                  lacking a principal inspector, the manager of                (2) For service information identified in
                                                    (i) Parts Installation Prohibition                            the local flight standards district office/               this AD, contact Airbus SAS, Airworthiness
                                                      As of December 19, 2013 (the effective date                 certificate holding district office. The AMOC             Office—EAL, 1 Rond Point Maurice Bellonte,
                                                    of AD 2013–14–04), no person may install                      approval letter must specifically reference               31707 Blagnac Cedex, France; telephone: +33
                                                    any INCO718 material, forward mount pylon                     this AD.                                                  5 61 93 36 96; fax: +33 5 61 93 45 80; email:



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                                                                           Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules                                              59539

                                                    airworthiness.A330–A340@airbus.com;                     Boulevard, Toronto, Ontario M3K 1Y5,                  Airworthiness Information, or ’’the
                                                    Internet: http://www.airbus.com. You may                Canada; telephone 416–375–4000; fax                   MCAI’’), to correct an unsafe condition
                                                    view this service information at the FAA,               416–375–4539; email thd.qseries@                      for certain Bombardier, Inc. Model
                                                    Transport Airplane Directorate, 1601 Lind               aero.bombardier.com; Internet http://                 DHC–8–400 series airplanes. The MCAI
                                                    Avenue SW., Renton, WA. For information
                                                    on the availability of this material at the
                                                                                                            www.bombardier.com. You may view                      states:
                                                    FAA, call 425–227–1221.                                 this referenced service information at                   There have been several reports of Interior
                                                                                                            the FAA, Transport Airplane                           Emergency Lights remaining ‘‘ON’’ following
                                                      Issued in Renton, Washington, on August               Directorate, 1601 Lind Avenue SW.,                    routine operational checks of the Emergency
                                                    18, 2016.
                                                                                                            Renton, WA. For information on the                    Light System. During these events, the
                                                    Dorr M. Anderson,                                       availability of this material at the FAA,             system could not be deactivated and the
                                                    Acting Manager, Transport Airplane                      call 425–227–1221.                                    associated circuit breaker was also found
                                                    Directorate, Aircraft Certification Service.                                                                  tripped. The events were caused by the
                                                    [FR Doc. 2016–20681 Filed 8–29–16; 8:45 am]             Examining the AD Docket                               overheating of the negative interlock and
                                                    BILLING CODE 4910–13–P                                     You may examine the AD docket on                   ground wires at the Emergency Light System
                                                                                                            the Internet at http://                               Power Supplies.
                                                                                                            www.regulations.gov by searching for                     Investigation has determined that the wire
                                                                                                                                                                  gauge of the negative interlock and ground
                                                    DEPARTMENT OF TRANSPORTATION                            and locating Docket No. FAA–2016–                     wiring is incompatible with the current load
                                                                                                            9054; or in person at the Docket                      experienced during the Emergency Light
                                                    Federal Aviation Administration                         Management Facility between 9 a.m.                    System operational check and this has led to
                                                                                                            and 5 p.m., Monday through Friday,                    the degradation of the wiring insulation.
                                                    14 CFR Part 39                                          except Federal holidays. The AD docket                   This [Canadian] AD is being issued to
                                                    [Docket No. FAA–2016–9054; Directorate                  contains this proposed AD, the                        mandate the change of the wiring gauge from
                                                                                                            regulatory evaluation, any comments                   22 to 20 American wire gauge (AWG) for the
                                                    Identifier 2016–NM–081–AD]
                                                                                                            received, and other information. The                  affected Emergency Lights Power Supplies
                                                    RIN 2120–AA64                                           street address for the Docket Operations              wiring.
                                                                                                            office (telephone 800–647–5527) is in                   You may examine the MCAI in the
                                                    Airworthiness Directives; Bombardier,                   the ADDRESSES section. Comments will                  AD docket on the Internet at http://
                                                    Inc. Airplanes                                          be available in the AD docket shortly                 www.regulations.gov by searching for
                                                    AGENCY: Federal Aviation                                after receipt.                                        and locating Docket No. FAA–2016–
                                                    Administration (FAA), DOT.                              FOR FURTHER INFORMATION CONTACT:                      9054.
                                                    ACTION: Notice of proposed rulemaking
                                                                                                            Assata Dessaline, Aerospace Engineer,
                                                                                                                                                                  Related Service Information Under 1
                                                    (NPRM).                                                 Avionics and Services Branch, ANE–
                                                                                                                                                                  CFR Part 51
                                                                                                            172, FAA, New York Aircraft
                                                    SUMMARY:   We propose to adopt a new                    Certification Office (ACO), 1600 Stewart                 We reviewed Bombardier Service
                                                    airworthiness directive (AD) for certain                Avenue, Suite 410, Westbury, NY                       Bulletin 84–33–12, Revision A, dated
                                                    Bombardier, Inc. Model DHC–8–400                        11590; telephone 516–228–7301; fax                    January 19, 2016. This service
                                                    series airplanes. This AD was prompted                  516–794–5531.                                         information describes procedures for
                                                    by reports of interior emergency lights                 SUPPLEMENTARY INFORMATION:                            changing the wiring gauge for the
                                                    remaining ‘‘ON’’ following routine                                                                            affected emergency lights power
                                                                                                            Comments Invited                                      supplies wiring to prevent overheating
                                                    operational checks of the emergency
                                                    light system. We are proposing this AD                    We invite you to send any written                   in the wires. This service information is
                                                    to require changing the wiring gauge for                relevant data, views, or arguments about              reasonably available because the
                                                    the affected emergency lights power                     this proposed AD. Send your comments                  interested parties have access to it
                                                    supplies wiring to prevent overheating                  to an address listed under the                        through their normal course of business
                                                    in the wires. Overheating can damage                    ADDRESSES section. Include ‘‘Docket No.               or by the means identified in the
                                                    the wire insulation, causing a fire.                    FAA–2016–9054; Directorate Identifier                 ADDRESSES section.
                                                                                                            2016–NM–081–AD’’ at the beginning of
                                                    DATES: We must receive comments on                                                                            FAA’s Determination and Requirements
                                                                                                            your comments. We specifically invite
                                                    this proposed AD by October 14, 2016.                                                                         of This Proposed AD
                                                                                                            comments on the overall regulatory,
                                                    ADDRESSES: You may send comments,                       economic, environmental, and energy                     This product has been approved by
                                                    using the procedures found in 14 CFR                    aspects of this proposed AD. We will                  the aviation authority of another
                                                    11.43 and 11.45, by any of the following                consider all comments received by the                 country, and is approved for operation
                                                    methods:                                                closing date and may amend this                       in the United States. Pursuant to our
                                                       • Federal eRulemaking Portal: Go to                  proposed AD based on those comments.                  bilateral agreement with the State of
                                                    http://www.regulations.gov. Follow the                    We will post all comments we                        Design Authority, we have been notified
                                                    instructions for submitting comments.                   receive, without change, to http://                   of the unsafe condition described in the
                                                       • Fax: 202–493–2251.                                 www.regulations.gov, including any                    MCAI and service information
                                                       • Mail: U.S. Department of                           personal information you provide. We                  referenced above. We are proposing this
                                                    Transportation, Docket Operations, M–                   will also post a report summarizing each              AD because we evaluated all pertinent
                                                    30, West Building Ground Floor, Room                    substantive verbal contact we receive                 information and determined an unsafe
                                                    W12–140, 1200 New Jersey Avenue SE.,                    about this proposed AD.                               condition exists and is likely to exist or
mstockstill on DSK3G9T082PROD with PROPOSALS




                                                    Washington, DC 20590.                                                                                         develop on other products of the same
                                                       • Hand Delivery: Deliver to Mail                     Discussion
                                                                                                                                                                  type design.
                                                    address above between 9 a.m. and 5                        Transport Canada Civil Aviation
                                                    p.m., Monday through Friday, except                     (TCCA), which is the aviation authority               Costs of Compliance
                                                    Federal holidays.                                       for Canada, has issued Canadian                          We estimate that this proposed AD
                                                       For service information identified in                Airworthiness Directive CF–2016–12,                   affects 52 airplanes of U.S. registry.
                                                    this NPRM, contact Bombardier, Inc., Q-                 dated May 11, 2016 (referred to after                    We estimate the following costs to
                                                    Series Technical Help Desk, 123 Garratt                 this as the Mandatory Continuing                      comply with this proposed AD:


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Document Created: 2018-02-09 11:42:20
Document Modified: 2018-02-09 11:42:20
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by October 14, 2016.
ContactVladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
FR Citation81 FR 59535 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

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