81_FR_32355 81 FR 32256 - Airworthiness Directives; Airbus Airplanes

81 FR 32256 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 99 (May 23, 2016)

Page Range32256-32258
FR Document2016-11681

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300B4-203 and A300B4-2C airplanes. This proposed AD was prompted by cracks found on pylon side panels (upper section) at rib 8. This proposed AD would require a detailed inspection for crack indications of the pylon side panels, a high frequency eddy current (HFEC) inspection to confirm any crack indications, modification of the pylon side panels, and repetitive inspections and repair if necessary. We are proposing this AD to detect and correct cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine.

Federal Register, Volume 81 Issue 99 (Monday, May 23, 2016) 
[Federal Register Volume 81, Number 99 (Monday, May 23, 2016)]
[Proposed Rules]
[Pages 32256-32258]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-11681]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed 
Rules

[[Page 32256]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-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 
certain Airbus Model A300B4-203 and A300B4-2C airplanes. This proposed 
AD was prompted by cracks found on pylon side panels (upper section) at 
rib 8. This proposed AD would require a detailed inspection for crack 
indications of the pylon side panels, a high frequency eddy current 
(HFEC) inspection to confirm any crack indications, modification of the 
pylon side panels, and repetitive inspections and repair if necessary. 
We are proposing this AD to detect and correct cracking of the pylon 
side panels. Such cracking could result in pylon structural failure and 
in-flight loss of an engine.

DATES: We must receive comments on this proposed AD by July 7, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: 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--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

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-
6671; 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 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-6671; 
Directorate Identifier 2015-NM-164-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 because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0201, dated October 7, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300B4-203 and A300B4-2C airplanes. The MCAI states:

    Cracks were found on pylon side panels (upper section) at rib 8 
on Airbus A300, A310 and A300-600 aeroplanes equipped with General 
Electric engines. Investigation of these findings indicated that 
this problem was likely to also affect aeroplanes of this type 
design with other engine installations.
    This condition, if not detected and corrected, could lead to 
reduced strength of the pylon primary structure, possibly resulting 
in pylon structural failure and in-flight loss of an engine.
    Prompted by these findings, EASA issued AD 2008-0181 [which 
corresponded to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010; corrected May 4, 2010 (75 FR 23572))] to require 
repetitive detailed visual inspections and, depending on aeroplane 
configuration and/or findings, the accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD 2008-0181 was issued, a fleet survey and 
updated Fatigue and Damage Tolerance analyses have been performed in 
order to substantiate the second A300-600 Extended Service Goal 
(ESG2) exercise. The results of these analyses have shown that the 
risk for these aeroplanes is higher than initially determined and 
consequently, the threshold and interval were reduced to allow 
timely detection of these cracks and the accomplishment of 
applicable corrective action(s).
    Consequently, EASA AD 2013-0136 was published to supersede EASA 
AD 2008-0181 and to require the inspections to be accomplished 
within reduced thresholds and intervals. Afterwards, [EASA] AD 2013-
0136 was mistakenly revised [EASA AD 2013-0136R1 corresponds to FAA 
AD 2015-26-06, Amendment 39-18354 (81 FR January 14,2016)] to reduce 
the Applicability, because it was considered at the time that 
aeroplanes on which Airbus mod 03599 was embodied, were not 
concerned by the requirements of EASA AD 2013-0136.
    Since EASA AD 2013-0136R1 was issued, a more thorough analysis 
determined that post-mod 03599 aeroplanes could be affected by this 
unsafe condition after all.
    [During] further deeper review, a list of nineteen A300 
aeroplanes was identified as

[[Page 32257]]

missing in the [EASA] AD 2013-0136R1 applicability, (aeroplanes 
post-mod 03599).
    For the reasons described above this AD retains the requirements 
of EASA AD 2013-0136R1 and mandates these requirements for the 19 
missing A300 aeroplanes MSNs.

    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-
6671.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-54-0075, Revision 04, dated 
May 26, 2015. The service information describes procedures for an 
inspection for crack indications of the pylons, a HFEC inspection to 
confirm cracking, modification of the pylon side panels, and repairs if 
cracks are found.
    Airbus has also issued Service Bulletin A300-54-0081, dated August 
11, 1993. This service information describes installation of a doubler 
on the left pylon 1 and right pylon 2, on pylon side panels (upper 
section) at Rib 8.
    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 these 
same type designs.

Differences Between Proposed Rule and Service Bulletin

    Unlike the procedures described in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015, this proposed AD would not 
permit further flight if cracks are detected in the pylon or pylon side 
panels. We have determined that because of the safety implications and 
consequences associated with that cracking, any cracked pylon or pylon 
side panel must be repaired or modified before further flight. This 
difference has been coordinated with EASA.

Costs of Compliance

    We estimate that this proposed AD affects 4 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost             Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection of the pylon side panels  30 work-hours x $85 per      $2,550 per inspection   $10,200 per inspection
                                      hour = $2,550 per            cycle.                  cycle.
                                      inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of airplanes that might need this 
repair.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Crack Repair.......................  56 work-hours x $85 per      $3,910 per repair.....  $8,670 per repair.
                                      hour = $4,760 per repair.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, 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-2016-6671; Directorate Identifier 2015-NM-
164-AD.

[[Page 32258]]

(a) Comments Due Date

    We must receive comments by July 7, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300B4-203 and A300B4-2C 
airplanes, certificated in any category, manufacturer serial numbers 
210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259, 
261, 274, 277, 292, 299, and 302.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Reason

    This AD was prompted by cracks found on pylon side panels (upper 
section) at rib 8. We are proposing this AD to detect and correct 
cracking of the pylon side panels. Such cracking could result in 
pylon structural failure and in-flight loss of an engine.

(f) Compliance

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

(g) Detailed Inspection of Pylons and Corrections

    At the applicable time specified in Airbus Service Bulletin 
A300-54-0075, Revision 04, dated May 26, 2015: Do a detailed 
inspection for crack indications of the pylons 1 and 2 side panels 
(upper section) at rib 8, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-54-0075, Revision 04, 
dated May 26, 2015.

(h) Crack Confirmation

    If any crack indication is found during the inspection required 
by paragraph (g) of this AD: Before further flight, do a high 
frequency eddy current (HFEC) inspection to confirm the crack, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-0075, Revision 04, dated May 26, 2015.

(i) Follow-On Actions for No Crack/Indication

    If the inspection required by paragraph (g) of this AD reveals 
no crack indication, or if the HFEC inspection specified by 
paragraph (h) of this AD confirms no crack: Do the actions specified 
in either paragraph (i)(1) or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (g) of this AD 
at the applicable time specified in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015.
    (2) At the applicable time specified in Airbus Service Bulletin 
A300-54-0081, dated August 11, 1993: Modify the pylons, in 
accordance with Airbus Service Bulletin 300-54-0081, dated August 
11, 1993. Thereafter, repeat the HFEC inspection specified in 
paragraph (h) of this AD at the applicable interval specified in 
Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 
2015, and repair any crack 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).

(j) Follow-On Actions for Crack Findings

    If any crack is confirmed during the inspection required by 
paragraph (h) of this AD, repair before further flight using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), and (j) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (k)(1) through (k)(4) of this 
AD.
    (1) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, 
which was incorporated by referenced in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 
23572).
    (2) Airbus Service Bulletin A300-54-0075, Revision 01, dated 
November 9, 2007, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A300-54-0075, Revision 02, dated 
June 26, 2008, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A300-54-0075, Revision 03, dated 
March 27, 2013, which is not incorporated by reference in this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0201, dated October 7, 
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-2016-6671.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com. You may view this 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 May 11, 2016.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-11681 Filed 5-20-16; 8:45 am]
BILLING CODE 4910-13-P

32256 Proposed Rules Federal Register Vol. 81, No. 99 Monday, May 23, 2016 This section of the FEDERAL REGISTER For service information identified in substantive verbal contact we receive contains notices to the public of the proposed this NPRM, contact Airbus SAS, about this proposed AD. issuance of rules and regulations. The Airworthiness Office—EAW, 1 Rond purpose of these notices is to give interested Discussion Point Maurice Bellonte, 31707 Blagnac persons an opportunity to participate in the Cedex, France; telephone +33 5 61 93 36 The European Aviation Safety Agency rule making prior to the adoption of the final (EASA), which is the Technical Agent rules. 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; for the Member States of the European Internet http://www.airbus.com. You Union, has issued EASA Airworthiness DEPARTMENT OF TRANSPORTATION may view this referenced service Directive 2015–0201, dated October 7, information at the FAA, Transport 2015 (referred to after this as the Federal Aviation Administration Airplane Directorate, 1601 Lind Avenue Mandatory Continuing Airworthiness SW., Renton, WA. For information on Information, or ‘‘the MCAI’’), to correct 14 CFR Part 39 the availability of this material at the an unsafe condition for certain Airbus FAA, call 425–227–1221. Model A300B4–203 and A300B4–2C [Docket No. FAA–2016–6671; Directorate airplanes. The MCAI states: Identifier 2015–NM–164–AD] Examining the AD Docket Cracks were found on pylon side panels RIN 2120–AA64 You may examine the AD docket on (upper section) at rib 8 on Airbus A300, A310 the Internet at http:// and A300–600 aeroplanes equipped with Airworthiness Directives; Airbus www.regulations.gov by searching for General Electric engines. Investigation of Airplanes and locating Docket No. FAA–2016– these findings indicated that this problem 6671; or in person at the Docket was likely to also affect aeroplanes of this AGENCY: Federal Aviation type design with other engine installations. Administration (FAA), DOT. Management Facility between 9 a.m. This condition, if not detected and ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, corrected, could lead to reduced strength of (NPRM). except Federal holidays. The AD docket the pylon primary structure, possibly contains this proposed AD, the resulting in pylon structural failure and in- SUMMARY: We propose to adopt a new regulatory evaluation, any comments flight loss of an engine. airworthiness directive (AD) for certain received, and other information. The Prompted by these findings, EASA issued Airbus Model A300B4–203 and street address for the Docket Office AD 2008–0181 [which corresponded to FAA A300B4–2C airplanes. This proposed (phone: 800–647–5527) is in the AD 2010–06–04, Amendment 39–16228 (75 AD was prompted by cracks found on ADDRESSES section. Comments will be FR 11428, March 11, 2010; corrected May 4, available in the AD docket shortly after 2010 (75 FR 23572))] to require repetitive pylon side panels (upper section) at rib detailed visual inspections and, depending 8. This proposed AD would require a receipt. on aeroplane configuration and/or findings, detailed inspection for crack indications FOR FURTHER INFORMATION CONTACT: Dan the accomplishment of applicable corrective of the pylon side panels, a high Rodina, Aerospace Engineer, action(s). frequency eddy current (HFEC) International Branch, ANM–116, Since that [EASA] AD 2008–0181 was inspection to confirm any crack Transport Airplane Directorate, FAA, issued, a fleet survey and updated Fatigue indications, modification of the pylon 1601 Lind Avenue SW., Renton, WA and Damage Tolerance analyses have been side panels, and repetitive inspections 98057–3356; telephone 425–227–2125; performed in order to substantiate the second and repair if necessary. We are A300–600 Extended Service Goal (ESG2) fax 425–227–1149. exercise. The results of these analyses have proposing this AD to detect and correct SUPPLEMENTARY INFORMATION: shown that the risk for these aeroplanes is cracking of the pylon side panels. Such higher than initially determined and cracking could result in pylon structural Comments Invited consequently, the threshold and interval failure and in-flight loss of an engine. We invite you to send any written were reduced to allow timely detection of DATES: We must receive comments on relevant data, views, or arguments about these cracks and the accomplishment of this proposed AD by July 7, 2016. this proposal. Send your comments to applicable corrective action(s). an address listed under the ADDRESSES Consequently, EASA AD 2013–0136 was ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA– published to supersede EASA AD 2008–0181 using the procedures found in 14 CFR and to require the inspections to be 11.43 and 11.45, by any of the following 2016–6671; Directorate Identifier 2015– accomplished within reduced thresholds and methods: NM–164–AD’’ at the beginning of your intervals. Afterwards, [EASA] AD 2013–0136 • Federal eRulemaking Portal: Go to comments. We specifically invite was mistakenly revised [EASA AD 2013– http://www.regulations.gov. Follow the comments on the overall regulatory, 0136R1 corresponds to FAA AD 2015–26–06, instructions for submitting comments. economic, environmental, and energy Amendment 39–18354 (81 FR January • Fax: 202–493–2251. aspects of this proposed AD. We will 14,2016)] to reduce the Applicability, • Mail: U.S. Department of consider all comments received by the because it was considered at the time that sradovich on DSK3TPTVN1PROD with PROPOSALS Transportation, Docket Operations, closing date and may amend this aeroplanes on which Airbus mod 03599 was M–30, West Building Ground Floor, proposed AD because of those embodied, were not concerned by the requirements of EASA AD 2013–0136. Room W12–140, 1200 New Jersey comments. Since EASA AD 2013–0136R1 was issued, Avenue SE., Washington, DC 20590. We will post all comments we a more thorough analysis determined that • Hand Delivery: Deliver to Mail receive, without change, to http:// post-mod 03599 aeroplanes could be affected address above between 9 a.m. and 5 www.regulations.gov, including any by this unsafe condition after all. p.m., Monday through Friday, except personal information you provide. We [During] further deeper review, a list of Federal holidays. will also post a report summarizing each nineteen A300 aeroplanes was identified as VerDate Sep<11>2014 16:06 May 20, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\23MYP1.SGM 23MYP1

Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed Rules 32257 missing in the [EASA] AD 2013–0136R1 describes installation of a doubler on develop on other products of these same applicability, (aeroplanes post-mod 03599). the left pylon 1 and right pylon 2, on type designs. For the reasons described above this AD pylon side panels (upper section) at Rib retains the requirements of EASA AD 2013– Differences Between Proposed Rule and 0136R1 and mandates these requirements for 8. Service Bulletin the 19 missing A300 aeroplanes MSNs. This service information is reasonably available because the interested parties Unlike the procedures described in You may examine the MCAI in the Airbus Service Bulletin A300–54–0075, have access to it through their normal AD docket on the Internet at http:// Revision 04, dated May 26, 2015, this course of business or by the means www.regulations.gov by searching for proposed AD would not permit further and locating Docket No. FAA–2016– identified in the ADDRESSES section. flight if cracks are detected in the pylon 6671. FAA’s Determination and Requirements or pylon side panels. We have Related Service Information Under 1 of This Proposed AD determined that because of the safety CFR Part 51 This product has been approved by implications and consequences Airbus has issued Service Bulletin the aviation authority of another associated with that cracking, any A300–54–0075, Revision 04, dated May country, and is approved for operation cracked pylon or pylon side panel must 26, 2015. The service information in the United States. Pursuant to our be repaired or modified before further describes procedures for an inspection bilateral agreement with the State of flight. This difference has been for crack indications of the pylons, a Design Authority, we have been notified coordinated with EASA. HFEC inspection to confirm cracking, of the unsafe condition described in the Costs of Compliance modification of the pylon side panels, MCAI and service information and repairs if cracks are found. referenced above. We are proposing this We estimate that this proposed AD Airbus has also issued Service AD because we evaluated all pertinent affects 4 airplanes of U.S. registry. Bulletin A300–54–0081, dated August information and determined an unsafe We estimate the following costs to 11, 1993. This service information condition exists and is likely to exist or comply with this proposed AD: ESTIMATED COSTS Action Labor cost Cost per product Cost on U.S. operators Inspection of the pylon side 30 work-hours × $85 per hour = $2,550 per inspection $2,550 per inspection cycle $10,200 per inspection panels. cycle. cycle. We estimate the following costs to do required based on the results of the determining the number of airplanes any necessary repairs that would be proposed inspection. We have no way of that might need this repair. ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Crack Repair ........................ 56 work-hours × $85 per hour = $4,760 per repair ...... $3,910 per repair ............... $8,670 per repair. Authority for This Rulemaking Regulatory Findings List of Subjects in 14 CFR Part 39 Title 49 of the United States Code We determined that this proposed AD Air transportation, Aircraft, Aviation specifies the FAA’s authority to issue would not have federalism implications safety, Incorporation by reference, rules on aviation safety. Subtitle I, under Executive Order 13132. This Safety. section 106, describes the authority of proposed AD would not have a substantial direct effect on the States, on The Proposed Amendment the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more the relationship between the national Accordingly, under the authority Government and the States, or on the detail the scope of the Agency’s delegated to me by the Administrator, distribution of power and authority. the FAA proposes to amend 14 CFR part responsibilities among the various We are issuing this rulemaking under 39 as follows: levels of government. the authority described in ‘‘Subtitle VII, For the reasons discussed above, I PART 39—AIRWORTHINESS Part A, Subpart III, Section 44701: certify this proposed regulation: DIRECTIVES General requirements.’’ Under that 1. Is not a ‘‘significant regulatory section, Congress charges the FAA with action’’ under Executive Order 12866; ■ 1. The authority citation for part 39 promoting safe flight of civil aircraft in 2. Is not a ‘‘significant rule’’ under the continues to read as follows: air commerce by prescribing regulations DOT Regulatory Policies and Procedures sradovich on DSK3TPTVN1PROD with PROPOSALS for practices, methods, and procedures (44 FR 11034, February 26, 1979); Authority: 49 U.S.C. 106(g), 40113, 44701. the Administrator finds necessary for 3. Will not affect intrastate aviation in § 39.13 [Amended] safety in air commerce. This regulation Alaska; and is within the scope of that authority 4. Will not have a significant ■ 2. The FAA amends § 39.13 by adding because it addresses an unsafe condition economic impact, positive or negative, the following new airworthiness that is likely to exist or develop on on a substantial number of small entities directive (AD): products identified in this rulemaking under the criteria of the Regulatory Airbus: Docket No. FAA–2016–6671; action. Flexibility Act. Directorate Identifier 2015–NM–164–AD. VerDate Sep<11>2014 16:06 May 20, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\23MYP1.SGM 23MYP1

32258 Federal Register / Vol. 81, No. 99 / Monday, May 23, 2016 / Proposed Rules (a) Comments Due Date 116, Transport Airplane Directorate, FAA; or October 7, 2015, for related information. This We must receive comments by July 7, 2016. the European Aviation Safety Agency MCAI may be found in the AD docket on the (EASA); or Airbus’s EASA Design Internet at http://www.regulations.gov by (b) Affected ADs Organization Approval (DOA). searching for and locating Docket No. FAA– None. 2016–6671. (j) Follow-On Actions for Crack Findings (2) For service information identified in (c) Applicability If any crack is confirmed during the this AD, contact Airbus SAS, Airworthiness This AD applies to Airbus Model A300B4– inspection required by paragraph (h) of this Office—EAW, 1 Rond Point Maurice 203 and A300B4–2C airplanes, certificated in AD, repair before further flight using a Bellonte, 31707 Blagnac Cedex, France; any category, manufacturer serial numbers method approved by the Manager, telephone +33 5 61 93 36 96; fax +33 5 61 210, 212, 218, 220, 227, 234, 235, 236, 239, International Branch, ANM–116, Transport 93 44 51; email account.airworth-eas@ 247, 255, 256, 259, 261, 274, 277, 292, 299, Airplane Directorate, FAA; or EASA; or airbus.com; Internet http://www.airbus.com. and 302. Airbus’s EASA DOA. You may view this service information at the (k) Credit for Previous Actions FAA, Transport Airplane Directorate, 1601 (d) Subject Lind Avenue SW., Renton, WA. For Air Transport Association (ATA) of This paragraph provides credit for actions information on the availability of this America Code 54, Nacelles/Pylons. required by paragraphs (g), (h), (i), and (j) of material at the FAA, call 425–227–1221. this AD, if those actions were performed (e) Reason before the effective date of this AD using the Issued in Renton, Washington, on May 11, This AD was prompted by cracks found on service information specified in paragraphs 2016. pylon side panels (upper section) at rib 8. We (k)(1) through (k)(4) of this AD. Suzanne Masterson, are proposing this AD to detect and correct (1) Airbus Service Bulletin A300–54–0075, Acting Manager, Transport Airplane cracking of the pylon side panels. Such dated August 11, 1993, which was Directorate, Aircraft Certification Service. cracking could result in pylon structural incorporated by referenced in AD 2010–06– 04, Amendment 39–16228 (75 FR 11428, [FR Doc. 2016–11681 Filed 5–20–16; 8:45 am] failure and in-flight loss of an engine. March 11, 2010); corrected May 4, 2010 (75 BILLING CODE 4910–13–P (f) Compliance FR 23572). Comply with this AD within the (2) Airbus Service Bulletin A300–54–0075, compliance times specified, unless already Revision 01, dated November 9, 2007, which done. is not incorporated by reference in this AD. DEPARTMENT OF HEALTH AND (3) Airbus Service Bulletin A300–54–0075, HUMAN SERVICES (g) Detailed Inspection of Pylons and Revision 02, dated June 26, 2008, which is Corrections not incorporated by reference in this AD. Food and Drug Administration At the applicable time specified in Airbus (4) Airbus Service Bulletin A300–54–0075, Service Bulletin A300–54–0075, Revision 04, Revision 03, dated March 27, 2013, which is 21 CFR Parts 882 and 895 dated May 26, 2015: Do a detailed inspection not incorporated by reference in this AD. for crack indications of the pylons 1 and 2 [Docket No. FDA–2016–N–1111] side panels (upper section) at rib 8, in (l) Other FAA AD Provisions accordance with the Accomplishment The following provisions also apply to this Banned Devices; Proposal To Ban Instructions of Airbus Service Bulletin A300– AD: Electrical Stimulation Devices Used To 54–0075, Revision 04, dated May 26, 2015. (1) Alternative Methods of Compliance Treat Self-Injurious or Aggressive (AMOCs): The Manager, International Behavior; Extension of Comment (h) Crack Confirmation Branch, ANM–116, FAA, has the authority to Period If any crack indication is found during the approve AMOCs for this AD, if requested inspection required by paragraph (g) of this using the procedures found in 14 CFR 39.19. AGENCY: Food and Drug Administration, AD: Before further flight, do a high frequency In accordance with 14 CFR 39.19, send your HHS. eddy current (HFEC) inspection to confirm request to your principal inspector or local the crack, in accordance with the Flight Standards District Office, as Proposed rule; extension of ACTION: Accomplishment Instructions of Airbus appropriate. If sending information directly comment period. Service Bulletin A300–54–0075, Revision 04, to the International Branch, send it to ATTN: dated May 26, 2015. Dan Rodina, Aerospace Engineer, SUMMARY: The Food and Drug International Branch, ANM–116, Transport Administration (FDA) is extending the (i) Follow-On Actions for No Crack/ Airplane Directorate, FAA, 1601 Lind comment period for the proposed rule Indication Avenue SW., Renton, WA 98057–3356; that appeared in the Federal Register of If the inspection required by paragraph (g) telephone 425–227–2125; fax 425–227–1149. April 25, 2016. In the proposed rule, of this AD reveals no crack indication, or if Information may be emailed to: 9-ANM-116- the HFEC inspection specified by paragraph FDA requested comments for a ban on AMOC-REQUESTS@faa.gov. Before using (h) of this AD confirms no crack: Do the any approved AMOC, notify your appropriate electrical stimulation devices (ESDs) actions specified in either paragraph (i)(1) or principal inspector, or lacking a principal used for self-injurious or aggressive (i)(2) of this AD. inspector, the manager of the local flight behavior (SIB or AB). The Agency is (1) Repeat the inspection required by standards district office/certificate holding taking this action in response to paragraph (g) of this AD at the applicable district office. The AMOC approval letter requests for an extension to allow time specified in Airbus Service Bulletin must specifically reference this AD. interested persons additional time to A300–54–0075, Revision 04, dated May 26, (2) Contacting the Manufacturer: For any submit comments. 2015. requirement in this AD to obtain corrective (2) At the applicable time specified in actions from a manufacturer, the action must DATES: FDA is extending the comment Airbus Service Bulletin A300–54–0081, be accomplished using a method approved period on the proposed rule published dated August 11, 1993: Modify the pylons, in by the Manager, International Branch, ANM– April 25, 2016 (81 FR 24386). Submit sradovich on DSK3TPTVN1PROD with PROPOSALS accordance with Airbus Service Bulletin 116, Transport Airplane Directorate, FAA; or either electronic or written comments 300–54–0081, dated August 11, 1993. the EASA; or Airbus’s EASA DOA. If by July 25, 2016. Thereafter, repeat the HFEC inspection approved by the DOA, the approval must ADDRESSES: You may submit comments specified in paragraph (h) of this AD at the include the DOA-authorized signature. applicable interval specified in Airbus as follows: Service Bulletin A300–54–0075, Revision 04, (m) Related Information Electronic Submissions dated May 26, 2015, and repair any crack (1) Refer to Mandatory Continuing before further flight using a method approved Airworthiness Information (MCAI) EASA Submit electronic comments in the by the Manager, International Branch, ANM– Airworthiness Directive 2015–0201, dated following way: VerDate Sep<11>2014 16:06 May 20, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\23MYP1.SGM 23MYP1


Document Created: 2018-02-07 15:07:14
Document Modified: 2018-02-07 15:07:14
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 July 7, 2016.
ContactDan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149.
FR Citation81 FR 32256 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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