80 FR 81786 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 251 (December 31, 2015)

Page Range		81786-81788
FR Document		2015-32848
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and Airbus Model A300 B4-600, B4- 600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This proposed AD was prompted by a report of cracking of the lower tension bolt area at the rib one junction (both sides) of the lower wing. This proposed AD would require repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the Frame (FR) 40 lower wing location, and corrective actions if necessary. We are proposing this AD to detect and correct crack initiation of the fittings of the FR40 lower wing locations, which could result in reduced structural integrity of the airplane.
Federal Register, Volume 80 Issue 251 (Thursday, December 31, 2015)
[Federal Register Volume 80, Number 251 (Thursday, December 31, 2015)]
[Proposed Rules]
[Pages 81786-81788]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-32848]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8134; Directorate Identifier 2014-NM-256-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 A300 series airplanes; and Airbus Model A300 B4-600, B4-
600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F 
airplanes (collectively called Model A300-600 series airplanes). This 
proposed AD was prompted by a report of cracking of the lower tension 
bolt area at the rib one junction (both sides) of the lower wing. This 
proposed AD would require repetitive inspections for cracking of the 
fasteners and of the fitting around the fastener holes at the Frame 
(FR) 40 lower wing location, and corrective actions if necessary. We 
are proposing this AD to detect and correct crack initiation of the 
fittings of the FR40 lower wing locations, which could result in 
reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by February 16, 
2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8134; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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: 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 proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-8134; 
Directorate Identifier 2014-NM-256-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0272, dated December 12, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; and Airbus Model A300 B4-600, B4-600R, and F4-600R 
series airplanes; and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). The MCAI states:

    Following the A300-600 Extended Service Goal (ESG2) exercise, 
specific inspections for cracks were performed in fittings of frame 
(FR) 40, in areas not covered by any existing task.
    Findings were identified on an A300-600 aeroplane withdrawn from 
service in the lower tension bolt area at rib one junction (both 
sides).
    This condition, if not detected and corrected, could lead to 
crack initiation, affecting the structural integrity of the 
aeroplane.
    To address this potential unsafe condition, an inspection 
programme was developed for the fitting around the fastener holes 
located at FR40 lower wing junction, left-hand (LH) and right-hand 
(RH) sides.
    For the reasons described above, this [EASA] AD requires 
repetitive High Frequency Eddy Current (HFEC) inspections and 
rototest inspections of the fitting around the fastener holes 
located at FR40 lower wing junction and, depending on findings, 
accomplishment of a repair.

    The corrective actions include a repair 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).
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8134.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletins A300-57-0257 and A300-57-6115, 
both dated April 4, 2014. The service information describes procedures 
for repetitive inspections for cracking of the fasteners and of the 
fitting around the fastener holes at the FR40 lower wing location. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation

[[Page 81787]]

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.

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

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in an airworthy condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 166 airplanes of U.S. 
registry.
    We also estimate that it would take about 12 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $169,320, or 
$1,020 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
AD.

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-2015-8134; Directorate Identifier 2014-NM-
256-AD.

(a) Comments Due Date

    We must receive comments by February 16, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a report of cracking of the lower 
tension bolt area at rib one junction (both sides) of the lower 
wing. We are issuing this AD to detect and correct crack initiation 
of the fittings of the Frame (FR) 40 lower wing locations, which 
could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive High Frequency Eddy Current Inspections

    Within 1,000 flight hours after the effective date of this AD: 
Do a high frequency eddy current (HFEC) inspection for cracking of 
fasteners 1 through 3 at the left-hand and right-hand sides of the 
FR40 lower junction, and of the fitting around the fastener holes, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletins A300-57-0257 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, 
B4-2C, B4-103, and B4-203 airplanes) or A300-57-6115 (for Model A300 
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, 
and C4-605R Variant F airplanes), both dated April 4, 2014, as 
applicable. If no cracking is found, repeat the HFEC inspection at 
intervals not to exceed 1,000 flight hours until a rototest 
inspection required by paragraph (h)(2) of this AD has been done.

[[Page 81788]]

(h) Repetitive Rototest Inspections

    Within 36 months after the effective date of this AD: Remove the 
fasteners and measure the diameter of the fastener holes; and, 
before further flight, do the applicable actions required by 
paragraph (h)(1) or (h)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-0257 
(for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes) or A300-57-6115 (for Model A300 B4-601, B4-603, B4-
620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant 
F airplanes), as applicable.
    (1) If one or more of the hole diameters is outside the 
tolerance of the nominal diameter, and outside the tolerance of the 
first and second oversize: Do the applicable corrective actions 
required by paragraph (i) of this AD.
    (2) If all of the hole diameters are within the tolerance of the 
nominal diameter or the first or second oversize: Do detailed and 
rototest inspections for cracking of the fastener holes at the left-
hand and right-hand sides of the FR40 lower junction, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletins 
A300-57-0257 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, 
B4-103, and B4-203 airplanes) or A300-57-6115 (for Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F airplanes), both dated April 4, 2014, as 
applicable. If no cracking is found, before further flight, install 
new fasteners of the same diameter in special clearance fit for 
fasteners 1 through 3 of the FR40 lower junction, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletins A300-57-
0257 or A300-57-6115, both dated April 4, 2014, as applicable. 
Repeat the rototest inspection thereafter at intervals not to exceed 
7,000 flight cycles. Accomplishment of a rototest inspection 
required by this paragraph terminates the repetitive HFEC 
inspections required by paragraph (g) of this AD.

(i) Corrective Actions

    If, during any inspection required by this AD, any crack is 
found, or one or more of the hole diameters are outside the 
tolerance of the nominal diameter: 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).

(j) 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: 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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2014-0272, dated December 12, 2014, 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 it in 
Docket No. FAA-2015-8134.
    (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 December 21, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32848 Filed 12-30-15; 8:45 am]
BILLING CODE 4910-13-P
81786 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules

Issued in Washington, DC, on December For service information identified in Directive 2014–0272, dated December
22, 2015. this proposed AD, contact Airbus SAS, 12, 2014 (referred to after this as the
Kathleen B. Hogan, Airworthiness Office—EAW, 1 Rond Mandatory Continuing Airworthiness
Deputy Assistant Secretary for Energy Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Efficiency, Energy Efficiency and Renewable Cedex, France; telephone +33 5 61 93 36 an unsafe condition for all Airbus
Energy. 96; fax +33 5 61 93 44 51; email Model A300 series airplanes; and
[FR Doc. 2015–32893 Filed 12–30–15; 8:45 am] account.airworth-eas@airbus.com; Airbus Model A300 B4–600, B4–600R,
BILLING CODE 6450–01–P Internet http://www.airbus.com. You and F4–600R series airplanes; and
may view this referenced service Model A300 C4–605R Variant F
information at the FAA, Transport airplanes (collectively called Model
DEPARTMENT OF TRANSPORTATION Airplane Directorate, 1601 Lind Avenue A300–600 series airplanes). The MCAI
SW., Renton, WA. For information on states:
Federal Aviation Administration the availability of this material at the Following the A300–600 Extended Service
FAA, call 425–227–1221. Goal (ESG2) exercise, specific inspections for
14 CFR Part 39 cracks were performed in fittings of frame
Examining the AD Docket
[Docket No. FAA–2015–8134; Directorate (FR) 40, in areas not covered by any existing
Identifier 2014–NM–256–AD] You may examine the AD docket on task.
the Internet at http:// Findings were identified on an A300–600
RIN 2120–AA64 www.regulations.gov by searching for aeroplane withdrawn from service in the
and locating Docket No. FAA–2015– lower tension bolt area at rib one junction
Airworthiness Directives; Airbus 8134; or in person at the Docket (both sides).
Airplanes This condition, if not detected and
Operations office between 9 a.m. and 5 corrected, could lead to crack initiation,
AGENCY: Federal Aviation p.m., Monday through Friday, except affecting the structural integrity of the
Administration (FAA), DOT. Federal holidays. The AD docket aeroplane.
ACTION: Notice of proposed rulemaking contains this proposed AD, the To address this potential unsafe condition,
(NPRM). regulatory evaluation, any comments an inspection programme was developed for
received, and other information. The the fitting around the fastener holes located
SUMMARY: We propose to adopt a new street address for the Docket Operations at FR40 lower wing junction, left-hand (LH)
airworthiness directive (AD) for all office (telephone (800) 647–5527) is in and right-hand (RH) sides.
For the reasons described above, this
Airbus Model A300 series airplanes; the ADDRESSES section. Comments will [EASA] AD requires repetitive High
and Airbus Model A300 B4–600, B4– be available in the AD docket shortly Frequency Eddy Current (HFEC) inspections
600R, and F4–600R series airplanes; and after receipt. and rototest inspections of the fitting around
Model A300 C4–605R Variant F FOR FURTHER INFORMATION CONTACT: Dan the fastener holes located at FR40 lower wing
airplanes (collectively called Model Rodina, Aerospace Engineer, junction and, depending on findings,
A300–600 series airplanes). This International Branch, ANM–116, accomplishment of a repair.
proposed AD was prompted by a report Transport Airplane Directorate, FAA, The corrective actions include a
of cracking of the lower tension bolt 1601 Lind Avenue SW., Renton, WA repair using a method approved by the
area at the rib one junction (both sides) 98057–3356; telephone 425–227–2125; Manager, International Branch, ANM–
of the lower wing. This proposed AD fax 425–227–1149. 116, Transport Airplane Directorate,
would require repetitive inspections for SUPPLEMENTARY INFORMATION: FAA; or the European Aviation Safety
cracking of the fasteners and of the Agency (EASA); or Airbus’s EASA
fitting around the fastener holes at the Comments Invited
Design Organization Approval (DOA).
Frame (FR) 40 lower wing location, and We invite you to send any written You may examine the MCAI in the
corrective actions if necessary. We are relevant data, views, or arguments about AD docket on the Internet at http://
proposing this AD to detect and correct this proposed AD. Send your comments www.regulations.gov by searching for
crack initiation of the fittings of the to an address listed under the and locating Docket No. FAA–2015–
FR40 lower wing locations, which could ADDRESSES section. Include ‘‘Docket No. 8134.
result in reduced structural integrity of FAA–2015–8134; Directorate Identifier
the airplane. 2014–NM–256–AD’’ at the beginning of Related Service Information Under 1
DATES: We must receive comments on your comments. We specifically invite CFR Part 51
this proposed AD by February 16, 2016. comments on the overall regulatory, We reviewed Airbus Service Bulletins
ADDRESSES: You may send comments by economic, environmental, and energy A300–57–0257 and A300–57–6115, both
any of the following methods: aspects of this proposed AD. We will dated April 4, 2014. The service
• Federal eRulemaking Portal: Go to consider all comments received by the information describes procedures for
http://www.regulations.gov. Follow the closing date and may amend this repetitive inspections for cracking of the
instructions for submitting comments. proposed AD based on those comments. fasteners and of the fitting around the
• Fax: (202) 493–2251. We will post all comments we fastener holes at the FR40 lower wing
• Mail: U.S. Department of receive, without change, to http:// location. This service information is
Transportation, Docket Operations, M– www.regulations.gov, including any reasonably available because the
30, West Building Ground Floor, Room personal information you provide. We interested parties have access to it
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each through their normal course of business
tkelley on DSK3SPTVN1PROD with PROPOSALS

Washington, DC 20590. substantive verbal contact we receive or by the means identified in the
• Hand Delivery: U.S. Department of about this proposed AD. ADDRESSES section of this NPRM.
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion FAA’s Determination and Requirements
W12–140, 1200 New Jersey Avenue SE., The European Aviation Safety Agency of This Proposed AD
Washington, DC, between 9 a.m. and 5 (EASA), which is the Technical Agent This product has been approved by
p.m., Monday through Friday, except for the Member States of the European the aviation authority of another
Federal holidays. Union, has issued EASA Airworthiness country, and is approved for operation

VerDate Sep<11>2014 16:32 Dec 30, 2015 Jkt 238001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\31DEP1.SGM 31DEP1
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81787

in the United States. Pursuant to our We have received no definitive data PART 39—AIRWORTHINESS
bilateral agreement with the State of that would enable us to provide a cost DIRECTIVES
Design Authority, we have been notified estimate for the on-condition actions
of the unsafe condition described in the specified in this proposed AD. ■ 1. The authority citation for part 39
MCAI and service information continues to read as follows:
Authority for This Rulemaking
referenced above. We are proposing this
Authority: 49 U.S.C. 106(g), 40113, 44701.
AD because we evaluated all pertinent Title 49 of the United States Code
information and determined an unsafe specifies the FAA’s authority to issue § 39.13 [Amended]
condition exists and is likely to exist or rules on aviation safety. Subtitle I,
develop on other products of the same ■ 2. The FAA amends § 39.13 by adding
section 106, describes the authority of
type design. the following new airworthiness
the FAA Administrator. ‘‘Subtitle VII:
directive (AD):
Explanation of ‘‘RC’’ Procedures and Aviation Programs,’’ describes in more
Tests in Service Information detail the scope of the Agency’s Airbus: Docket No. FAA–2015–8134;
authority. Directorate Identifier 2014–NM–256–AD.
The FAA worked in conjunction with
industry, under the Airworthiness We are issuing this rulemaking under (a) Comments Due Date
Directive Implementation Aviation the authority described in ‘‘Subtitle VII, We must receive comments by February
Rulemaking Committee (ARC), to Part A, Subpart III, Section 44701: 16, 2016.
enhance the AD system. One General requirements.’’ Under that
(b) Affected ADs
enhancement was a new process for section, Congress charges the FAA with
promoting safe flight of civil aircraft in None.
annotating which procedures and tests
in the service information are required air commerce by prescribing regulations (c) Applicability
for compliance with an AD. for practices, methods, and procedures This AD applies to all Airbus airplanes
Differentiating these procedures and the Administrator finds necessary for identified in paragraphs (c)(1) and (c)(2) of
tests from other tasks in the service safety in air commerce. This regulation this AD, certificated in any category.
information is expected to improve an is within the scope of that authority (1) Airbus Model A300 B2–1A, B2–1C,
owner’s/operator’s understanding of because it addresses an unsafe condition B2K–3C, B2–203, B4–2C, B4–103, and B4–
crucial AD requirements and help that is likely to exist or develop on 203 airplanes.
provide consistent judgment in AD products identified in this rulemaking (2) Airbus Model A300 B4–601, B4–603,
compliance. The procedures and tests action. B4–620, B4–622, B4–605R, B4–622R, F4–
605R, F4–622R, and C4–605R Variant F
identified as Required for Compliance Regulatory Findings airplanes.
(RC) in any service information have a
direct effect on detecting, preventing, We determined that this proposed AD (d) Subject
resolving, or eliminating an identified would not have federalism implications Air Transport Association (ATA) of
unsafe condition. under Executive Order 13132. This America Code 57, Wings.
As specified in a NOTE under the proposed AD would not have a (e) Reason
Accomplishment Instructions of the substantial direct effect on the States, on
specified service information, the relationship between the national This AD was prompted by a report of
procedures and tests that are identified cracking of the lower tension bolt area at rib
Government and the States, or on the
as RC in any service information must one junction (both sides) of the lower wing.
distribution of power and We are issuing this AD to detect and correct
be done to comply with the proposed responsibilities among the various crack initiation of the fittings of the Frame
AD. However, procedures and tests that levels of government. (FR) 40 lower wing locations, which could
are not identified as RC are For the reasons discussed above, I result in reduced structural integrity of the
recommended. Those procedures and certify this proposed regulation: airplane.
tests that are not identified as RC may
be deviated from using accepted 1. Is not a ‘‘significant regulatory (f) Compliance
methods in accordance with the action’’ under Executive Order 12866; Comply with this AD within the
operator’s maintenance or inspection 2. Is not a ‘‘significant rule’’ under the compliance times specified, unless already
program without obtaining approval of DOT Regulatory Policies and Procedures done.
an alternative method of compliance (44 FR 11034, February 26, 1979); (g) Repetitive High Frequency Eddy Current
(AMOC), provided the procedures and 3. Will not affect intrastate aviation in Inspections
tests identified as RC can be done and Alaska; and Within 1,000 flight hours after the effective
the airplane can be put back in an 4. Will not have a significant date of this AD: Do a high frequency eddy
airworthy condition. Any substitutions economic impact, positive or negative, current (HFEC) inspection for cracking of
or changes to procedures or tests on a substantial number of small entities fasteners 1 through 3 at the left-hand and
identified as RC will require approval of right-hand sides of the FR40 lower junction,
under the criteria of the Regulatory and of the fitting around the fastener holes,
an AMOC. Flexibility Act. in accordance with the Accomplishment
Costs of Compliance List of Subjects in 14 CFR Part 39 Instructions of Airbus Service Bulletins
We estimate that this proposed AD A300–57–0257 (for Model A300 B2–1A, B2–
affects 166 airplanes of U.S. registry. Air transportation, Aircraft, Aviation 1C, B2K–3C, B2–203, B4–2C, B4–103, and
safety, Incorporation by reference, B4–203 airplanes) or A300–57–6115 (for
tkelley on DSK3SPTVN1PROD with PROPOSALS

We also estimate that it would take
about 12 work-hours per product to Safety. Model A300 B4–601, B4–603, B4–620, B4–
622, B4–605R, B4–622R, F4–605R, F4–622R,
comply with the basic requirements of The Proposed Amendment and C4–605R Variant F airplanes), both dated
this proposed AD. The average labor April 4, 2014, as applicable. If no cracking is
rate is $85 per work-hour. Based on Accordingly, under the authority found, repeat the HFEC inspection at
these figures, we estimate the cost of delegated to me by the Administrator, intervals not to exceed 1,000 flight hours
this proposed AD on U.S. operators to the FAA proposes to amend 14 CFR part until a rototest inspection required by
be $169,320, or $1,020 per product. 39 as follows: paragraph (h)(2) of this AD has been done.

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81788 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules

(h) Repetitive Rototest Inspections Dan Rodina, Aerospace Engineer, DEPARTMENT OF TRANSPORTATION
Within 36 months after the effective date International Branch, ANM–116, Transport
of this AD: Remove the fasteners and Airplane Directorate, FAA, 1601 Lind Federal Aviation Administration
measure the diameter of the fastener holes; Avenue SW., Renton, WA 98057–3356;
and, before further flight, do the applicable telephone 425–227–2125; fax 425–227–1149. 14 CFR Part 39
actions required by paragraph (h)(1) or (h)(2) Information may be emailed to: 9-ANM-116-
of this AD, in accordance with the AMOC-REQUESTS@faa.gov. Before using [Docket No. FAA–2015–8130; Directorate
Accomplishment Instructions of Airbus any approved AMOC, notify your appropriate Identifier 2014–NM–175–AD]
Service Bulletin A300–57–0257 (for Model principal inspector, or lacking a principal RIN 2120–AA64
A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– inspector, the manager of the local flight
2C, B4–103, and B4–203 airplanes) or A300– standards district office/certificate holding Airworthiness Directives; The Boeing
57–6115 (for Model A300 B4–601, B4–603, district office. The AMOC approval letter
B4–620, B4–622, B4–605R, B4–622R, F4– Company Airplanes
must specifically reference this AD.
605R, F4–622R, and C4–605R Variant F AGENCY: Federal Aviation
(2) Contacting the Manufacturer: For any
airplanes), as applicable. Administration (FAA), DOT.
(1) If one or more of the hole diameters is requirement in this AD to obtain corrective
outside the tolerance of the nominal actions from a manufacturer, the action must ACTION: Notice of proposed rulemaking
diameter, and outside the tolerance of the be accomplished using a method approved (NPRM).
first and second oversize: Do the applicable by the Manager, International Branch, ANM–
corrective actions required by paragraph (i) of 116, Transport Airplane Directorate, FAA; or SUMMARY: We propose to adopt a new
this AD. the European Aviation Safety Agency airworthiness directive (AD) for certain
(2) If all of the hole diameters are within (EASA); or Airbus’s EASA Design The Boeing Company Model 777–200
the tolerance of the nominal diameter or the Organization Approval (DOA). If approved by and –300 series airplanes equipped with
first or second oversize: Do detailed and the DOA, the approval must include the Pratt and Whitney engines. This
rototest inspections for cracking of the DOA-authorized signature. proposed AD was prompted by reports
fastener holes at the left-hand and right-hand (3) Required for Compliance (RC): Except
sides of the FR40 lower junction, in of blocked drain lines at the engine
as required by paragraph (i) of this AD: If any forward strut that caused flammable
accordance with the Accomplishment service information contains procedures or
Instructions of Airbus Service Bulletins fluid to accumulate in a flammable
tests that are identified as RC, those
A300–57–0257 (for Model A300 B2–1A, B2– leakage zone. This proposed AD would
procedures and tests must be done to comply
1C, B2K–3C, B2–203, B4–2C, B4–103, and require doing the following actions on
B4–203 airplanes) or A300–57–6115 (for with this AD; any procedures or tests that are
not identified as RC are recommended. Those
the left strut and right strut: A one-time
Model A300 B4–601, B4–603, B4–620, B4– cleaning of certain forward strut drain
622, B4–605R, B4–622R, F4–605R, F4–622R, procedures and tests that are not identified
as RC may be deviated from using accepted lines; installing new forward strut drain
and C4–605R Variant F airplanes), both dated
April 4, 2014, as applicable. If no cracking is methods in accordance with the operator’s lines and insulation blankets; a leak
found, before further flight, install new maintenance or inspection program without check of the forward strut drain lines;
fasteners of the same diameter in special obtaining approval of an AMOC, provided and repair if any leak is found. This
clearance fit for fasteners 1 through 3 of the the procedures and tests identified as RC can proposed AD would also require
FR40 lower junction, in accordance with the be done and the airplane can be put back in revising the maintenance or inspection
Accomplishment Instructions of Airbus an airworthy condition. Any substitutions or program, as applicable, to incorporate a
Service Bulletins A300–57–0257 or A300– changes to procedures or tests identified as certain airworthiness limitation. We are
57–6115, both dated April 4, 2014, as RC require approval of an AMOC. proposing this AD to prevent blockage
applicable. Repeat the rototest inspection of forward strut drain lines, which
thereafter at intervals not to exceed 7,000 (k) Related Information
could cause flammable fluids to collect
flight cycles. Accomplishment of a rototest (1) Refer to Mandatory Continuing
inspection required by this paragraph in the forward strut area and potentially
Airworthiness Information (MCAI) European
terminates the repetitive HFEC inspections cause an uncontrolled fire or cause
Aviation Safety Agency (EASA)
required by paragraph (g) of this AD. failure of engine attachment structure
Airworthiness Directive 2014–0272, dated
December 12, 2014, for related information.
and consequent airplane loss.
(i) Corrective Actions
This MCAI may be found in the AD docket DATES: We must receive comments on
If, during any inspection required by this
on the Internet at http://www.regulations.gov this proposed AD by February 16, 2016.
AD, any crack is found, or one or more of the
hole diameters are outside the tolerance of by searching for and locating it in Docket No. ADDRESSES: You may send comments,
the nominal diameter: Repair before further FAA–2015–8134. using the procedures found in 14 CFR
flight using a method approved by the (2) For service information identified in 11.43 and 11.45, by any of the following
Manager, International Branch, ANM–116, this AD, contact Airbus SAS, Airworthiness methods:
Transport Airplane Directorate, FAA; or the Office—EAW, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to
European Aviation Safety Agency (EASA); or Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the
Airbus’s EASA Design Organization telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments.
Approval (DOA). 93 44 51; email account.airworth-eas@
• Fax: 202–493–2251.
airbus.com; Internet http://www.airbus.com.
(j) Other FAA AD Provisions • Mail: U.S. Department of
You may view this service information at the
The following provisions also apply to this FAA, Transport Airplane Directorate, 1601
Transportation, Docket Operations, M–
AD: Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room
(1) Alternative Methods of Compliance information on the availability of this W12–140, 1200 New Jersey Avenue SE.,
(AMOCs): The Manager, International material at the FAA, call 425–227–1221. Washington, DC 20590.
Branch, ANM–116, Transport Airplane • Hand Delivery: Deliver to Mail
tkelley on DSK3SPTVN1PROD with PROPOSALS

Directorate, FAA, has the authority to Issued in Renton, Washington, on
address above between 9 a.m. and 5
approve AMOCs for this AD, if requested December 21, 2015.
p.m., Monday through Friday, except
using the procedures found in 14 CFR 39.19. Michael Kaszycki,
In accordance with 14 CFR 39.19, send your Federal holidays.
Acting Manager, Transport Airplane For service information identified in
request to your principal inspector or local
Directorate, Aircraft Certification Service. this proposed AD, contact Boeing
Flight Standards District Office, as
appropriate. If sending information directly [FR Doc. 2015–32848 Filed 12–30–15; 8:45 am] Commercial Airplanes, Attention: Data
to the International Branch, send it to ATTN: BILLING CODE 4910–13–P & Services Management, P.O. Box 3707,

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Document Created: 2015-12-31 02:14:57
Document Modified: 2015-12-31 02:14:57
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by February 16, 2016.
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.
FR Citation		80 FR 81786
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 81786 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 251 (December 31, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
