82 FR 34891 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 143 (July 27, 2017)

Page Range		34891-34894
FR Document		2017-15553
We propose to supersede Airworthiness Directive (AD) AD 2016- 20-11, for certain 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); and Airbus Model A310 series airplanes. AD 2016-20-11 requires repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. Since we issued AD 2016-20-11, we have determined that reinforcement of the aft cargo door sill beam area is necessary to address the unsafe condition, which constitutes terminating action for the repetitive inspections. This proposed AD would retain the inspections for cracking, and repair if necessary; and require reinforcement of the aft cargo door sill beam area. We are proposing this AD to address the unsafe condition on these products.
Federal Register, Volume 82 Issue 143 (Thursday, July 27, 2017)
[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Proposed Rules]
[Pages 34891-34894]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-15553]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-035-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) AD 2016-
20-11, for certain 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); and Airbus Model 
A310 series airplanes. AD 2016-20-11 requires repetitive inspections of 
the external area of the aft cargo door sill beam for cracking, 
repetitive inspections for fatigue cracking of the cargo door sill 
beam, lock fitting, and torsion box plate, and repair if necessary. 
Since we issued AD 2016-20-11, we have determined that reinforcement of 
the aft cargo door sill beam area is necessary to address the unsafe 
condition, which constitutes terminating action for the repetitive 
inspections. This proposed AD would retain the inspections for 
cracking, and repair if necessary; and require reinforcement of the aft 
cargo door sill beam area. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 11, 
2017.

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-2017-
0708; 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: 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-2017-0708; 
Directorate Identifier 2017-NM-035-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 September 28, 2016, we issued AD 2016-20-11, Amendment 39-18677 
(81 FR 85837, November 29, 2016) (``AD 2016-20-11''), for certain 
Airbus Model A300-600 series airplanes; and Airbus Model A310 series 
airplanes. AD 2016-20-11 was prompted by reports of fatigue cracks on 
the cargo door sill beam, lock fitting, and torsion box plate. AD 2016-
20-11 requires repetitive ultrasonic and detailed inspections of the 
external area of the aft cargo door sill beam for cracking, repetitive 
high frequency eddy current (HFEC) inspections for fatigue cracking of 
the cargo door sill beam, lock fitting, and torsion box plate, and 
repair if necessary. We issued AD 2016-20-11 to detect and correct 
fatigue cracking of the cargo door sill beam, lock fitting, and torsion 
box plate, which could result in the loss of the door locking function 
and subsequently, loss of the cargo door in flight and rapid 
decompression.
    Since we issued AD 2016-20-11, Airbus has developed a reinforcement 
modification of the aft cargo door sill beam area, which constitutes 
terminating action for the repetitive inspections. We have determined 
the reinforcement of the aft cargo door sill beam area is necessary to 
address the unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0048, dated March 15, 2017; corrected April 20, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300-600 series airplanes; and Airbus Model A310 series airplanes. The 
MCAI states:

    In the frame of the widespread fatigue damage (WFD) compliance 
study and after an in-service occurrence, the area of the aft cargo 
door sill beam and adjacent structure was identified as sensitive to 
the fatigue loads.
    This condition, if not detected and corrected, could lead to 
failure of multiple lock fittings, possibly resulting in loss of the 
cargo door in flight and consequent explosive decompression of the 
aeroplane.

[[Page 34892]]

    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A53W005-14 providing inspection 
instructions and, consequently, EASA issued Emergency AD 2014-0097-E 
[which corresponded to FAA AD 2014-12-06] to require repetitive 
ultrasonic inspections (US) or detailed inspections (DET) of the aft 
cargo door sill beam area [and corrective actions if necessary].
    After that [EASA] AD was issued, further analysis indicated that 
repetitive high frequency eddy current (HFEC) inspections needed to 
be introduced, and Airbus published Service Bulletin (SB) A310-53-
2139 and SB A300-53-6179 to provide instructions. Prompted by this 
determination, EASA issued AD 2015-0150, retaining the requirements 
of EASA Emergency AD 2014-0097-E, which was superseded, and required 
repetitive HFEC inspections of the concerned areas. The first HFEC 
inspection terminated the repetitive US/DET inspections. That [EASA] 
AD also required the inspection results to be reported.
    Since that [EASA] AD was issued, Airbus developed a 
reinforcement modification of the aft cargo door sill beam area, and 
published Airbus SB A310-53-2141 and SB A300-53-6181, which were 
revised lately, to make this available for in-service application.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0150 [which corresponded to FAA AD 
2016-20-11], which is superseded, and requires modification 
[reinforcement] of the aft cargo door sill beam, which constitutes 
terminating action for the repetitive inspections.
    This [EASA] AD is re-published to correct the compliance time 
description in Table 4.

    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-2017-
0708.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A300-53-6181, Revision 
01, dated July 2, 2015; and A310-53-2141, Revision 01, dated July 2, 
2015. This service information describes procedures for reinforcing the 
aft cargo door sill beam. These service bulletins are distinct since 
they apply to different airplane models.
    Airbus has issued Airbus Service Bulletin A300-53-6179, dated 
December 12, 2014; and A310-53-2139, dated December 12, 2014. This 
service information describes procedures for repetitive HFEC 
inspections of the cargo door sill beam, lock fitting, and torsion box 
plate. These service bulletins are distinct since they apply to 
different airplane models.
    Airbus has also issued AOT A53W005-14, Revision 01, dated April 29, 
2014, which describes procedures for doing an ultrasonic inspection or 
detailed inspection of the aft cargo door sill beam external area for 
cracking.
    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 AD affects 75 airplanes of U.S. registry. We 
estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from  12 work-hours x $85             N/A  $1,020 per           $76,500 per
 AD 2016-20-11).                    per hour = $1,020                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
Modification (new proposed         40 work-hours x $85         $96,890  $100,290...........  $7,521,750.
 action).                           per hour = $3,400.
Reporting........................  1 work-hour x $85                 0  $85 per inspection   $6,375 per
(retained action from AD 2016-20-   per hour = $85 per                   cycle.               inspection cycle.
 11).                               inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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

[[Page 34893]]

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 removing Airworthiness Directive (AD) 
2016-20-11, Amendment 39-18677 (81 FR 85837, November 29, 2016), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0708; Directorate Identifier 2017-NM-
035-AD.

(a) Comments Due Date

    We must receive comments by September 11, 2017.

(b) Affected ADs

    This AD replaces AD 2016-20-11, Amendment 39-18677 (81 FR 85837, 
November 29, 2016) (``AD 2016-20-11'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers on which Airbus Modification 05438 has 
been embodied in production, except those on which Airbus 
Modification 12046 has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of fatigue cracks on the cargo 
door sill beam, lock fitting, and torsion box plate. We are issuing 
this AD to prevent fatigue cracking of the cargo door sill beam, 
lock fitting, and torsion box plate, which could result in the loss 
of the door locking function and subsequently, loss of the cargo 
door in flight and rapid decompression.

(f) Compliance

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

(g) Retained Inspection, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-20-11, with no changes. Within the compliance time identified 
in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Do 
an ultrasonic inspection or detailed inspection of the aft cargo 
door sill beam external area for cracking, in accordance with Airbus 
Alert Operators Transmission (AOT) A53W005-14, dated April 22, 2014; 
or Airbus AOT A53W005-14, Revision 01, dated April 29, 2014. Repeat 
the inspection thereafter at intervals not to exceed 275 flight 
cycles. As of January 3, 2017 (the effective date of AD 2016-20-11), 
use only AOT A53W005-14, Revision 01, dated April 29, 2014, to 
comply with the requirements of this paragraph.
    (1) For airplanes that have accumulated 30,000 flight cycles or 
more since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06, Amendment 39-17867, (79 FR 34403, 
June 17, 2014) (``AD 2014-12-06'')): Within 50 flight cycles after 
July 2, 2014.
    (2) For airplanes that have accumulated 18,000 flight cycles or 
more, but fewer than 30,000 flight cycles since the airplane's first 
flight as of July 2, 2014 (the effective date of AD 2014-12-06): 
Within 275 flight cycles after July 2, 2014.
    (3) For airplanes that have accumulated fewer than 18,000 flight 
cycles since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Before exceeding 18,275 flight 
cycles since the airplane's first flight.

(h) Retained Optional Terminating Action, With No Changes

    This paragraph restates the provisions of paragraph (h) of AD 
2016-20-11, with no changes. Accomplishment of a high frequency eddy 
current (HFEC) inspection for cracking, in accordance with Airbus 
AOT A53W005-14, dated April 22, 2014; or AOT A53W005-14, Revision 
01, dated April 29, 2014; terminates the repetitive inspections 
required by paragraph (g) of this AD for that airplane. If any 
cracking is found during the HFEC inspection, before further flight, 
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).

(i) Retained Reporting Requirement, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2016-20-11, with no changes. Submit a report of the findings (both 
positive and negative) of the inspection required by paragraph (g) 
of this AD to ``Airbus Service Bulletin Reporting Online 
Application'' on Airbus World (https://w3.airbus.com/), at the 
applicable time specified in paragraph (i)(1) or (i)(2) of this AD. 
The report must include the inspection results, including no 
findings.
    (1) If the inspection was done on or after January 3, 2017 (the 
effective date of AD 2016-20-11): Submit the report within 30 days 
after the inspection.
    (2) If the inspection was done before January 3, 2017 (the 
effective date of AD 2016-20-11): Submit the report within 30 days 
after January 3, 2017.

(j) Retained Definition of Airplane Groups, With No Changes

    This paragraph restates the definitions specified in paragraph 
(j) of AD 2016-20-11, with no changes. Paragraphs (k)(1), (k)(2), 
and (k)(3) of this AD refer to airplane groups, as identified in 
paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
    (1) Airplanes on which an HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14.
    (2) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated more than 
18,000 total flight cycles as of January 3, 2017 (the effective date 
of AD 2016-20-11).
    (3) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated 18,000 
total flight cycles or fewer as of January 3, 2017 (the effective 
date of AD 2016-20-11).

(k) Retained Repetitive HFEC Inspections, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2016-20-11, with no changes. At the applicable time specified in 
paragraph (k)(1), (k)(2), or (k)(3) of this AD: Do an HFEC 
inspection for fatigue cracking of the cargo door sill beam, lock 
fitting, and torsion box plate, in accordance with Airbus Service 
Bulletin A300-53-6179, dated December 12, 2014; or Airbus Service 
Bulletin A310-53-2139, dated December 12, 2014; as applicable. 
Repeat the HFEC inspection thereafter at intervals not to exceed 
4,600 flight cycles.
    (1) For airplanes identified in paragraph (j)(1) of this AD: 
Inspect within 4,600 flight cycles after the most recent HFEC 
inspection specified in Airbus AOT A53W005-14.
    (2) For airplanes identified in paragraph (j)(2) of this AD: 
Inspect within 2,000 flight cycles after January 3, 2017 (the 
effective date of AD 2016-20-11).
    (3) For airplanes identified in paragraph (j)(3) of this AD: 
Inspect before exceeding 13,000 total flight cycles since the 
airplane's

[[Page 34894]]

first flight, or within 2,000 flight cycles after January 3, 2017 
(the effective date of AD 2016-20-11), whichever occurs later.

(l) Retained Corrective Action, With No Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2016-20-11, with no changes. If any crack is found during any 
inspection required by paragraph (g) or (k) of this AD: Before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(m) Retained Terminating Action for Repetitive Inspections in Paragraph 
(g) of This AD, With No Changes

    This paragraph restates the terminating action of paragraph 
(m)(1) of AD 2016-20-11, with no changes. For any airplane 
identified in paragraphs (j)(2) and (j)(3) of this AD, 
accomplishment of the initial inspection required by paragraph (k) 
of this AD terminates the repetitive inspections required by 
paragraph (g) of this AD.

(n) New Cargo Door Reinforcement

    At the latest of the applicable times specified in paragraphs 
(n)(1), (n)(2), and (n)(3) of this AD: Reinforce the aft cargo door 
sill beam area, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A310-53-2141, Revision 01, dated July 2, 
2015; or Airbus Service Bulletin A300-53-6181, Revision 01, dated 
July 2, 2015; as applicable.
    (1) Before exceeding 19,600 flight cycles since first flight of 
the airplane.
    (2) Within 2,300 flight cycles after the last HFEC or detailed 
inspection required by this AD that was accomplished before the 
effective date of this AD.
    (3) Within 12 months after the effective date of this AD.

(o) New Terminating Action

    Modification of an airplane as required by paragraph (n) of this 
AD constitutes terminating action for the repetitive inspections 
required by paragraphs (g) and (k) of this AD for that airplane.

(p) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(n) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A300-53-6181, dated 
June 26, 2015; or Airbus Service Bulletin A310-53-2141, dated June 
26, 2015; as applicable.

(q) 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 the attention of 
the person identified in paragraph (r)(2) of this AD. Information 
may be emailed to: [email protected].
    (i) 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.
    (ii) AMOCs approved previously for AD 2016-20-11 are approved as 
AMOCs for the corresponding provisions of 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 DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.
    (4) Required for Compliance (RC): Except as required by 
paragraph (l) 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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0048, dated March 15, 2017; 
corrected April 20, 2017, 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-2017-0708.
    (2) For more information about this AD, 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. You may view this 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA.
    (3) 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. For information on the availability 
of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15553 Filed 7-26-17; 8:45 am]
 BILLING CODE 4910-13-P
Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules 34891

phone: 562–627–5239; fax: 562–627–5210; ADDRESSES: You may send comments, economic, environmental, and energy
email: chandraduth.ramdoss@faa.gov. using the procedures found in 14 CFR aspects of this proposed AD. We will
(2) For service information identified in 11.43 and 11.45, by any of the following consider all comments received by the
this AD, contact Boeing Commercial
methods: closing date and may amend this
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., • Federal eRulemaking Portal: Go to proposed AD based on those comments.
MC 110–SK57, Seal Beach, CA 90740; http://www.regulations.gov. Follow the We will post all comments we
telephone: 562–797–1717; Internet: https:// instructions for submitting comments. receive, without change, to http://
www.myboeingfleet.com. You may view this • Fax: 202–493–2251. www.regulations.gov, including any
referenced service information at the FAA, • Mail: U.S. Department of personal information you provide. We
Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M– will also post a report summarizing each
Avenue SW., Renton, WA. For information substantive verbal contact we receive
30, West Building Ground Floor, Room
on the availability of this material at the about this proposed AD.
FAA, call 425–227–1221. W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590. Discussion
Issued in Renton, Washington, on July 18, • Hand Delivery: Deliver to Mail
2017. On September 28, 2016, we issued AD
address above between 9 a.m. and 5
Victor Wicklund,
p.m., Monday through Friday, except 2016–20–11, Amendment 39–18677 (81
Acting Manager, Transport Airplane Federal holidays. FR 85837, November 29, 2016) (‘‘AD
Directorate, Aircraft Certification Service.
For service information identified in 2016–20–11’’), for certain Airbus Model
[FR Doc. 2017–15554 Filed 7–26–17; 8:45 am] this NPRM, contact Airbus SAS, A300–600 series airplanes; and Airbus
BILLING CODE 4910–13–P Airworthiness Office—EAW, 1 Rond Model A310 series airplanes. AD 2016–
Point Maurice Bellonte, 31707 Blagnac 20–11 was prompted by reports of
Cedex, France; telephone +33 5 61 93 36 fatigue cracks on the cargo door sill
DEPARTMENT OF TRANSPORTATION beam, lock fitting, and torsion box plate.
96; fax +33 5 61 93 44 51; email
AD 2016–20–11 requires repetitive
Federal Aviation Administration account.airworth-eas@airbus.com;
ultrasonic and detailed inspections of
Internet http://www.airbus.com. You
the external area of the aft cargo door
14 CFR Part 39 may view this referenced service
sill beam for cracking, repetitive high
information at the FAA, Transport
[Docket No. FAA–2017–0708; Directorate frequency eddy current (HFEC)
Airplane Directorate, 1601 Lind Avenue
Identifier 2017–NM–035–AD] inspections for fatigue cracking of the
SW., Renton, WA. For information on
cargo door sill beam, lock fitting, and
RIN 2120–AA64 the availability of this material at the
torsion box plate, and repair if
FAA, call 425–227–1221.
Airworthiness Directives; Airbus necessary. We issued AD 2016–20–11 to
Airplanes Examining the AD Docket detect and correct fatigue cracking of the
cargo door sill beam, lock fitting, and
You may examine the AD docket on
AGENCY: Federal Aviation torsion box plate, which could result in
Administration (FAA), DOT. the Internet at http://
the loss of the door locking function and
www.regulations.gov by searching for
ACTION: Notice of proposed rulemaking subsequently, loss of the cargo door in
and locating Docket No. FAA–2017–
(NPRM). flight and rapid decompression.
0708; or in person at the Docket Since we issued AD 2016–20–11,
SUMMARY: We propose to supersede Management Facility between 9 a.m. Airbus has developed a reinforcement
Airworthiness Directive (AD) AD 2016– and 5 p.m., Monday through Friday, modification of the aft cargo door sill
20–11, for certain Airbus Model A300 except Federal holidays. The AD docket beam area, which constitutes
B4–600, B4–600R, and F4–600R series contains this proposed AD, the terminating action for the repetitive
airplanes, and Model A300 C4–605R regulatory evaluation, any comments inspections. We have determined the
Variant F airplanes (collectively called received, and other information. The reinforcement of the aft cargo door sill
Model A300–600 series airplanes); and street address for the Docket Operations beam area is necessary to address the
Airbus Model A310 series airplanes. AD office (telephone 800–647–5527) is in unsafe condition.
2016–20–11 requires repetitive the ADDRESSES section. Comments will The European Aviation Safety Agency
inspections of the external area of the aft be available in the AD docket shortly (EASA), which is the Technical Agent
cargo door sill beam for cracking, after receipt. for the Member States of the European
repetitive inspections for fatigue FOR FURTHER INFORMATION CONTACT: Dan Union, has issued EASA AD 2017–0048,
cracking of the cargo door sill beam, Rodina, Aerospace Engineer, dated March 15, 2017; corrected April
lock fitting, and torsion box plate, and International Branch, ANM–116, 20, 2017 (referred to after this as the
repair if necessary. Since we issued AD Transport Airplane Directorate, FAA, Mandatory Continuing Airworthiness
2016–20–11, we have determined that 1601 Lind Avenue SW., Renton, WA Information, or ‘‘the MCAI’’), to correct
reinforcement of the aft cargo door sill 98057–3356; telephone 425–227–2125; an unsafe condition for certain Airbus
beam area is necessary to address the fax 425–227–1149. Model A300–600 series airplanes; and
unsafe condition, which constitutes SUPPLEMENTARY INFORMATION: Airbus Model A310 series airplanes.
terminating action for the repetitive The MCAI states:
inspections. This proposed AD would Comments Invited
In the frame of the widespread fatigue
retain the inspections for cracking, and We invite you to send any written damage (WFD) compliance study and after an
mstockstill on DSK30JT082PROD with PROPOSALS

repair if necessary; and require relevant data, views, or arguments about in-service occurrence, the area of the aft
reinforcement of the aft cargo door sill this proposal. Send your comments to cargo door sill beam and adjacent structure
beam area. We are proposing this AD to an address listed under the ADDRESSES was identified as sensitive to the fatigue
address the unsafe condition on these section. Include ‘‘Docket No. FAA– loads.
products. This condition, if not detected and
2017–0708; Directorate Identifier 2017– corrected, could lead to failure of multiple
DATES: We must receive comments on NM–035–AD’’ at the beginning of your lock fittings, possibly resulting in loss of the
this proposed AD by September 11, comments. We specifically invite cargo door in flight and consequent explosive
2017. comments on the overall regulatory, decompression of the aeroplane.

VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1
34892 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules

To address this potential unsafe condition, terminating action for the repetitive 29, 2014, which describes procedures
Airbus issued Alert Operators Transmission inspections. for doing an ultrasonic inspection or
(AOT) A53W005–14 providing inspection This [EASA] AD is re-published to correct detailed inspection of the aft cargo door
instructions and, consequently, EASA issued the compliance time description in Table 4.
Emergency AD 2014–0097–E [which
sill beam external area for cracking.
corresponded to FAA AD 2014–12–06] to You may examine the MCAI in the This service information is reasonably
require repetitive ultrasonic inspections (US) AD docket on the Internet at http:// available because the interested parties
or detailed inspections (DET) of the aft cargo www.regulations.gov by searching for have access to it through their normal
door sill beam area [and corrective actions if and locating Docket No. FAA–2017– course of business or by the means
necessary]. 0708.
After that [EASA] AD was issued, further
identified in the ADDRESSES section.
analysis indicated that repetitive high Related Service Information Under 1 FAA’s Determination and Requirements
frequency eddy current (HFEC) inspections CFR Part 51 of This Proposed AD
needed to be introduced, and Airbus
published Service Bulletin (SB) A310–53–
Airbus has issued Airbus Service
Bulletin A300–53–6181, Revision 01, This product has been approved by
2139 and SB A300–53–6179 to provide
dated July 2, 2015; and A310–53–2141, the aviation authority of another
instructions. Prompted by this determination,
EASA issued AD 2015–0150, retaining the Revision 01, dated July 2, 2015. This country, and is approved for operation
requirements of EASA Emergency AD 2014– service information describes in the United States. Pursuant to our
0097–E, which was superseded, and required procedures for reinforcing the aft cargo bilateral agreement with the State of
repetitive HFEC inspections of the concerned door sill beam. These service bulletins Design Authority, we have been notified
areas. The first HFEC inspection terminated of the unsafe condition described in the
are distinct since they apply to different
the repetitive US/DET inspections. That MCAI and service information
[EASA] AD also required the inspection airplane models.
Airbus has issued Airbus Service referenced above. We are proposing this
results to be reported.
Since that [EASA] AD was issued, Airbus Bulletin A300–53–6179, dated AD because we evaluated all pertinent
developed a reinforcement modification of December 12, 2014; and A310–53–2139, information and determined an unsafe
the aft cargo door sill beam area, and dated December 12, 2014. This service condition exists and is likely to exist or
published Airbus SB A310–53–2141 and SB information describes procedures for develop on other products of the same
A300–53–6181, which were revised lately, to repetitive HFEC inspections of the cargo type design.
make this available for in-service application. door sill beam, lock fitting, and torsion
For the reasons described above, this Costs of Compliance
[EASA] AD retains the requirements of EASA box plate. These service bulletins are
AD 2015–0150 [which corresponded to FAA distinct since they apply to different We estimate that this AD affects 75
AD 2016–20–11], which is superseded, and airplane models. airplanes of U.S. registry. We estimate
requires modification [reinforcement] of the Airbus has also issued AOT the following costs to comply with this
aft cargo door sill beam, which constitutes A53W005–14, Revision 01, dated April proposed AD:

ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection (retained actions 12 work-hours × $85 per hour N/A $1,020 per inspection cycle ... $76,500 per inspection cycle.
from AD 2016–20–11). = $1,020 per inspection
cycle.
Modification (new proposed 40 work-hours × $85 per hour $96,890 $100,290 ................................ $7,521,750.
action). = $3,400.
Reporting ................................ 1 work-hour × $85 per hour = 0 $85 per inspection cycle ........ $6,375 per inspection cycle.
(retained action from AD $85 per inspection cycle.
2016–20–11).

We have received no definitive data instructions, as well as completing and We are issuing this rulemaking under
that would enable us to provide cost reviewing the collection of information. the authority described in ‘‘Subtitle VII,
estimates for the on-condition actions Therefore, all reporting associated with Part A, Subpart III, Section 44701:
specified in this proposed AD. this AD is mandatory. Comments General requirements.’’ Under that
concerning the accuracy of this burden section, Congress charges the FAA with
Paperwork Reduction Act promoting safe flight of civil aircraft in
and suggestions for reducing the burden
A federal agency may not conduct or should be directed to the FAA at 800 air commerce by prescribing regulations
sponsor, and a person is not required to Independence Ave. SW., Washington, for practices, methods, and procedures
respond to, nor shall a person be subject DC 20591, ATTN: Information the Administrator finds necessary for
to penalty for failure to comply with a Collection Clearance Officer, AES–200. safety in air commerce. This regulation
collection of information subject to the is within the scope of that authority
requirements of the Paperwork Authority for This Rulemaking because it addresses an unsafe condition
Reduction Act unless that collection of that is likely to exist or develop on
Title 49 of the United States Code
mstockstill on DSK30JT082PROD with PROPOSALS

information displays a current valid products identified in this rulemaking
specifies the FAA’s authority to issue action.
OMB control number. The control rules on aviation safety. Subtitle I,
number for the collection of information section 106, describes the authority of Regulatory Findings
required by this AD is 2120–0056. The the FAA Administrator. ‘‘Subtitle VII:
paperwork cost associated with this AD Aviation Programs,’’ describes in more We determined that this proposed AD
has been detailed in the Costs of detail the scope of the Agency’s would not have federalism implications
Compliance section of this document under Executive Order 13132. This
authority.
and includes time for reviewing proposed AD would not have a

VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1
Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules 34893

substantial direct effect on the States, on (4) Airbus Model A300 C4–605R Variant F International Branch, ANM–116, Transport
the relationship between the national airplanes. Airplane Directorate, FAA; or the European
Government and the States, or on the (5) Airbus Model A310–203, –204, –221, Aviation Safety Agency (EASA); or Airbus’s
–222, –304, –322, –324, and –325 airplanes. EASA Design Organization Approval (DOA).
distribution of power and
responsibilities among the various (d) Subject (i) Retained Reporting Requirement, With
levels of government. Air Transport Association (ATA) of No Changes
For the reasons discussed above, I America Code 53, Fuselage. This paragraph restates the requirements of
certify this proposed regulation: paragraph (i) of AD 2016–20–11, with no
(e) Reason changes. Submit a report of the findings (both
1. Is not a ‘‘significant regulatory
This AD was prompted by reports of positive and negative) of the inspection
action’’ under Executive Order 12866; fatigue cracks on the cargo door sill beam, required by paragraph (g) of this AD to
2. Is not a ‘‘significant rule’’ under the lock fitting, and torsion box plate. We are ‘‘Airbus Service Bulletin Reporting Online
DOT Regulatory Policies and Procedures issuing this AD to prevent fatigue cracking of Application’’ on Airbus World (https://
(44 FR 11034, February 26, 1979); the cargo door sill beam, lock fitting, and w3.airbus.com/), at the applicable time
3. Will not affect intrastate aviation in torsion box plate, which could result in the specified in paragraph (i)(1) or (i)(2) of this
Alaska; and loss of the door locking function and AD. The report must include the inspection
4. Will not have a significant subsequently, loss of the cargo door in flight results, including no findings.
and rapid decompression. (1) If the inspection was done on or after
economic impact, positive or negative,
January 3, 2017 (the effective date of AD
on a substantial number of small entities (f) Compliance 2016–20–11): Submit the report within 30
under the criteria of the Regulatory Comply with this AD within the days after the inspection.
Flexibility Act. compliance times specified, unless already (2) If the inspection was done before
done. January 3, 2017 (the effective date of AD
List of Subjects in 14 CFR Part 39 2016–20–11): Submit the report within 30
(g) Retained Inspection, With No Changes
Air transportation, Aircraft, Aviation days after January 3, 2017.
safety, Incorporation by reference, This paragraph restates the requirements of
paragraph (g) of AD 2016–20–11, with no (j) Retained Definition of Airplane Groups,
Safety. changes. Within the compliance time With No Changes
The Proposed Amendment identified in paragraph (g)(1), (g)(2), or (g)(3) This paragraph restates the definitions
of this AD, as applicable: Do an ultrasonic specified in paragraph (j) of AD 2016–20–11,
Accordingly, under the authority inspection or detailed inspection of the aft with no changes. Paragraphs (k)(1), (k)(2),
delegated to me by the Administrator, cargo door sill beam external area for and (k)(3) of this AD refer to airplane groups,
the FAA proposes to amend 14 CFR part cracking, in accordance with Airbus Alert as identified in paragraphs (j)(1), (j)(2), and
39 as follows: Operators Transmission (AOT) A53W005–14, (j)(3) of this AD.
dated April 22, 2014; or Airbus AOT (1) Airplanes on which an HFEC
PART 39—AIRWORTHINESS A53W005–14, Revision 01, dated April 29, inspection was accomplished as specified in
DIRECTIVES 2014. Repeat the inspection thereafter at Airbus AOT A53W005–14.
intervals not to exceed 275 flight cycles. As (2) Airplanes on which no HFEC
■ 1. The authority citation for part 39 of January 3, 2017 (the effective date of AD inspection was accomplished as specified in
2016–20–11), use only AOT A53W005–14, Airbus AOT A53W005–14, that have
continues to read as follows: Revision 01, dated April 29, 2014, to comply accumulated more than 18,000 total flight
Authority: 49 U.S.C. 106(g), 40113, 44701. with the requirements of this paragraph. cycles as of January 3, 2017 (the effective
(1) For airplanes that have accumulated date of AD 2016–20–11).
§ 39.13 [Amended] 30,000 flight cycles or more since the (3) Airplanes on which no HFEC
■ 2. The FAA amends § 39.13 by airplane’s first flight as of July 2, 2014 (the inspection was accomplished as specified in
removing Airworthiness Directive (AD) effective date of AD 2014–12–06, Airbus AOT A53W005–14, that have
2016–20–11, Amendment 39–18677 (81 Amendment 39–17867, (79 FR 34403, June accumulated 18,000 total flight cycles or
17, 2014) (‘‘AD 2014–12–06’’)): Within 50 fewer as of January 3, 2017 (the effective date
FR 85837, November 29, 2016), and flight cycles after July 2, 2014. of AD 2016–20–11).
adding the following new AD: (2) For airplanes that have accumulated
Airbus: Docket No. FAA–2017–0708; 18,000 flight cycles or more, but fewer than (k) Retained Repetitive HFEC Inspections,
Directorate Identifier 2017–NM–035–AD. 30,000 flight cycles since the airplane’s first With No Changes
flight as of July 2, 2014 (the effective date of This paragraph restates the requirements of
(a) Comments Due Date AD 2014–12–06): Within 275 flight cycles paragraph (k) of AD 2016–20–11, with no
We must receive comments by September after July 2, 2014. changes. At the applicable time specified in
11, 2017. (3) For airplanes that have accumulated paragraph (k)(1), (k)(2), or (k)(3) of this AD:
fewer than 18,000 flight cycles since the Do an HFEC inspection for fatigue cracking
(b) Affected ADs airplane’s first flight as of July 2, 2014 (the of the cargo door sill beam, lock fitting, and
This AD replaces AD 2016–20–11, effective date of AD 2014–12–06): Before torsion box plate, in accordance with Airbus
Amendment 39–18677 (81 FR 85837, exceeding 18,275 flight cycles since the Service Bulletin A300–53–6179, dated
November 29, 2016) (‘‘AD 2016–20–11’’). airplane’s first flight. December 12, 2014; or Airbus Service
Bulletin A310–53–2139, dated December 12,
(c) Applicability (h) Retained Optional Terminating Action, 2014; as applicable. Repeat the HFEC
This AD applies to the airplanes identified With No Changes inspection thereafter at intervals not to
in paragraphs (c)(1) through (c)(5) of this AD, This paragraph restates the provisions of exceed 4,600 flight cycles.
certificated in any category, all manufacturer paragraph (h) of AD 2016–20–11, with no (1) For airplanes identified in paragraph
serial numbers on which Airbus Modification changes. Accomplishment of a high (j)(1) of this AD: Inspect within 4,600 flight
mstockstill on DSK30JT082PROD with PROPOSALS

05438 has been embodied in production, frequency eddy current (HFEC) inspection for cycles after the most recent HFEC inspection
except those on which Airbus Modification cracking, in accordance with Airbus AOT specified in Airbus AOT A53W005–14.
12046 has been embodied in production. A53W005–14, dated April 22, 2014; or AOT (2) For airplanes identified in paragraph
(1) Airbus Model A300 B4–601, B4–603, A53W005–14, Revision 01, dated April 29, (j)(2) of this AD: Inspect within 2,000 flight
B4–620, and B4–622 airplanes. 2014; terminates the repetitive inspections cycles after January 3, 2017 (the effective date
(2) Airbus Model A300 B4–605R and B4– required by paragraph (g) of this AD for that of AD 2016–20–11).
622R airplanes. airplane. If any cracking is found during the (3) For airplanes identified in paragraph
(3) Airbus Model A300 F4–605R and F4– HFEC inspection, before further flight, repair (j)(3) of this AD: Inspect before exceeding
622R airplanes. using a method approved by the Manager, 13,000 total flight cycles since the airplane’s

VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1
34894 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules

first flight, or within 2,000 flight cycles after attention of the person identified in Avenue SW., Renton, WA 98057–3356;
January 3, 2017 (the effective date of AD paragraph (r)(2) of this AD. Information may telephone 425–227–2125; fax 425–227–1149.
2016–20–11), whichever occurs later. be emailed to: 9-ANM-116-AMOC- You may view this service information at the
REQUESTS@faa.gov. FAA, Transport Airplane Directorate, 1601
(l) Retained Corrective Action, With No (i) Before using any approved AMOC, Lind Avenue SW., Renton, WA.
Changes notify your appropriate principal inspector, (3) For service information identified in
This paragraph restates the requirements of or lacking a principal inspector, the manager this AD, contact Airbus SAS, Airworthiness
paragraph (l) of AD 2016–20–11, with no of the local flight standards district office/ Office—EAW, 1 Rond Point Maurice
changes. If any crack is found during any certificate holding district office. Bellonte, 31707 Blagnac Cedex, France;
inspection required by paragraph (g) or (k) of (ii) AMOCs approved previously for AD telephone +33 5 61 93 36 96; fax +33 5 61
this AD: Before further flight, repair using a 2016–20–11 are approved as AMOCs for the 93 44 51; email account.airworth-eas@
method approved by the Manager, corresponding provisions of this AD. airbus.com; Internet http://www.airbus.com.
International Branch, ANM–116, Transport (2) Contacting the Manufacturer: As of the For information on the availability of this
Airplane Directorate, FAA; or the EASA; or effective date of this AD, for any requirement material at the FAA, call 425–227–1221.
Airbus’s EASA DOA. in this AD to obtain corrective actions from Issued in Renton, Washington, on July 14,
(m) Retained Terminating Action for a manufacturer, the action must be 2017.
Repetitive Inspections in Paragraph (g) of accomplished using a method approved by
the Manager, International Branch, ANM– Dionne Palermo,
This AD, With No Changes Acting Manager, Transport Airplane
116, Transport Airplane Directorate, FAA; or
This paragraph restates the terminating EASA; or Airbus’s EASA DOA. If approved Directorate, Aircraft Certification Service.
action of paragraph (m)(1) of AD 2016–20–11, by the DOA, the approval must include the [FR Doc. 2017–15553 Filed 7–26–17; 8:45 am]
with no changes. For any airplane identified DOA-authorized signature. BILLING CODE 4910–13–P
in paragraphs (j)(2) and (j)(3) of this AD, (3) Reporting Requirements: A federal
accomplishment of the initial inspection agency may not conduct or sponsor, and a
required by paragraph (k) of this AD person is not required to respond to, nor
terminates the repetitive inspections required shall a person be subject to a penalty for DEPARTMENT OF COMMERCE
by paragraph (g) of this AD. failure to comply with a collection of
information subject to the requirements of Bureau of Economic Analysis
(n) New Cargo Door Reinforcement
the Paperwork Reduction Act unless that
At the latest of the applicable times 15 CFR Part 801
collection of information displays a current
specified in paragraphs (n)(1), (n)(2), and
valid OMB Control Number. The OMB
(n)(3) of this AD: Reinforce the aft cargo door [Docket No.: 170322304–7304–01]
Control Number for this information
sill beam area, in accordance with the
collection is 2120–0056. Public reporting for RIN 0691–AA86
Accomplishment Instructions of Airbus
this collection of information is estimated to
Service Bulletin A310–53–2141, Revision 01,
be approximately 5 minutes per response, Direct Investment Surveys: BE–12,
dated July 2, 2015; or Airbus Service Bulletin
including the time for reviewing instructions, Benchmark Survey of Foreign Direct
A300–53–6181, Revision 01, dated July 2,
completing and reviewing the collection of Investment in the United States
2015; as applicable.
(1) Before exceeding 19,600 flight cycles information. All responses to this collection
since first flight of the airplane. of information are mandatory. Comments AGENCY: Bureau of Economic Analysis,
(2) Within 2,300 flight cycles after the last concerning the accuracy of this burden and Commerce.
HFEC or detailed inspection required by this suggestions for reducing the burden should ACTION: Notice of proposed rulemaking.
AD that was accomplished before the be directed to the FAA at: 800 Independence
effective date of this AD. Ave. SW., Washington, DC 20591, Attn: SUMMARY: This proposed rule would
(3) Within 12 months after the effective Information Collection Clearance Officer, amend regulations of the Department of
date of this AD. AES–200. Commerce’s Bureau of Economic
(4) Required for Compliance (RC): Except
(o) New Terminating Action as required by paragraph (l) of this AD: If any
Analysis (BEA) to set forth the reporting
service information contains procedures or requirements for the 2017 BE–12,
Modification of an airplane as required by
paragraph (n) of this AD constitutes tests that are identified as RC, those Benchmark Survey of Foreign Direct
terminating action for the repetitive procedures and tests must be done to comply Investment in the United States. The
inspections required by paragraphs (g) and with this AD; any procedures or tests that are BE–12 survey is conducted every five
(k) of this AD for that airplane. not identified as RC are recommended. Those years; the prior survey covered 2012.
procedures and tests that are not identified The benchmark survey covers the
(p) Credit for Previous Actions as RC may be deviated from using accepted universe of foreign direct investment in
This paragraph provides credit for actions methods in accordance with the operator’s the United States and is BEA’s most
required by paragraph (n) of this AD, if those maintenance or inspection program without
actions were performed before the effective obtaining approval of an AMOC, provided
detailed survey of such investment. For
date of this AD using Airbus Service Bulletin the procedures and tests identified as RC can the 2017 benchmark survey, BEA
A300–53–6181, dated June 26, 2015; or be done and the airplane can be put back in proposes changes in data items
Airbus Service Bulletin A310–53–2141, an airworthy condition. Any substitutions or collected, the design of the survey
dated June 26, 2015; as applicable. changes to procedures or tests identified as forms, and the reporting requirements
RC require approval of an AMOC. for the survey to satisfy changing data
(q) Other FAA AD Provisions
(r) Related Information needs, improve data quality and the
The following provisions also apply to this effectiveness and efficiency of data
AD: (1) Refer to Mandatory Continuing
(1) Alternative Methods of Compliance Airworthiness Information (MCAI) EASA
collection.
(AMOCs): The Manager, International Airworthiness Directive 2017–0048, dated DATES: Comments on this proposed rule
mstockstill on DSK30JT082PROD with PROPOSALS

Branch, ANM–116, Transport Airplane March 15, 2017; corrected April 20, 2017, for will receive consideration if submitted
Directorate, FAA, has the authority to related information. This MCAI may be in writing on or before 5 p.m. September
approve AMOCs for this AD, if requested found in the AD docket on the Internet at 25, 2017.
using the procedures found in 14 CFR 39.19. http://www.regulations.gov by searching for
ADDRESSES: You may submit comments,
In accordance with 14 CFR 39.19, send your and locating Docket No. FAA–2017–0708.
request to your principal inspector or local (2) For more information about this AD, identified by RIN 0691–AA86, and
Flight Standards District Office, as contact Dan Rodina, Aerospace Engineer, referencing the agency name (Bureau of
appropriate. If sending information directly International Branch, ANM–116, Transport Economic Analysis), by any of the
to the International Branch, send it to the Airplane Directorate, FAA, 1601 Lind following methods:

VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1
Document Created: 2017-07-27 02:07:35
Document Modified: 2017-07-27 02:07:35
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 September 11, 2017.
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		82 FR 34891
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
82 FR 34891 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 143 (July 27, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
