83 FR 24690 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 104 (May 30, 2018)

Page Range		24690-24694
FR Document		2018-11421
We propose to supersede Airworthiness Directive (AD) 98-18-24, which applies to certain Airbus Model A320 series airplanes. AD 98-18- 24 requires repetitive inspections to detect cracking in the inner flange of a certain door frame, and corrective actions, if necessary. AD 98-18-24 also provides an optional terminating action for the repetitive inspections. Since we issued AD 98-18-24, it has been determined that the compliance times for the repetitive inspections must be reduced. This proposed AD would continue to require the repetitive inspections of the inner flange of a certain door frame, with reduced repetitive inspection intervals, and corrective action if necessary. We are proposing this AD to address the unsafe condition on these products.
Federal Register, Volume 83 Issue 104 (Wednesday, May 30, 2018)
[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)]
[Proposed Rules]
[Pages 24690-24694]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-11421]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-18-24, 
which applies to certain Airbus Model A320 series airplanes. AD 98-18-
24 requires repetitive inspections to detect cracking in the inner 
flange of a certain door frame, and corrective actions, if necessary. 
AD 98-18-24 also provides an optional terminating action for the 
repetitive inspections. Since we issued AD 98-18-24, it has been 
determined that the compliance times for the repetitive inspections 
must be reduced. This proposed AD would continue to require the 
repetitive inspections of the inner flange of a certain door frame, 
with reduced repetitive inspection intervals, and corrective action if 
necessary. We are proposing this AD to address the unsafe condition on 
these products.

[[Page 24691]]


DATES: We must receive comments on this proposed AD by July 16, 2018.

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, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

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-2018-
0455; 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: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA; 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

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-2018-0455; 
Product Identifier 2017-NM-121-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

    We issued AD 98-18-24, Amendment 39-10740 (63 FR 49272, September 
15, 1998) (``AD 98-18-24''), for certain A320 series airplanes. AD 98-
18-24 was prompted by the results of a fatigue test on simulated 
flights which revealed cracks on the inner flange of door frame 66 at 
stringers 18 and 20. The cracks were located in the gusset plate 
attachment holes and were hidden by the gusset plates. AD 98-18-24 
requires repetitive inspections to detect cracking in the inner flange 
of door frame 66, and corrective actions if necessary. AD 98-18-24 also 
provides an optional terminating action for the repetitive inspections. 
We issued AD 98-18-24 to detect and correct fatigue cracking in the 
inner flange of door frame 66, which could result in reduced structural 
integrity of the airplane.
    Since we issued AD 98-18-24, based on the results from a full scale 
fatigue test, it has been determined that the repetitive inspection 
intervals must be reduced.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0128, dated July 24, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-211 and A320-231 airplanes. The MCAI states:

    During fatigue test on simulated flights, cracks developed on 
the inner flange of door frame 66 at stringer 18 and 20 positions. 
These cracks were located in the gusset plate attachment holes and 
were hidden by the plates.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1071, later revised, to provide 
instructions to inspect and repair the gusset plate attachment holes 
at frame 66, at stringers 18, 20 and 22 both left hand (LH) and 
right hand (RH) side of the fuselage (hereafter collectively 
referred to as ``the attachment holes'' in this [EASA] AD), and 
[Airbus] SB A320-53-1072, providing instructions for reworking of 
the attachment holes.
    Consequently, DGAC France issued [French] AD 1996-234-087, later 
revised [which corresponds to FAA AD 98-18-24], requiring repetitive 
inspections and, depending on findings, repair of the attachment 
holes, and including reference to a reworking procedure, which 
constitutes optional terminating action for the repetitive 
inspections of the attachment holes.
    Since that [French] AD was issued, based on results from a full 
scale fatigue test, it was determined that the inspection intervals 
must be reduced. Airbus issued SB A320-53-1071 Revision 03, 
modifying the inspection threshold and intervals, and not changing 
the inspection instructions.
    For the reason described above, this [EASA] AD retains the 
requirement of DGAC France AD 1996-234-087 R1, which is superseded, 
and requires reduction of the repetitive inspection interval.

    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-2018-
0455.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017. This service information describes procedures for 
detailed inspections of the gusset plate attachment holes at door frame 
66 for cracking and corrective action.
    Airbus also issued Service Bulletin A320-53-1072, Revision 02, 
dated May 5, 2016. This service information describes procedures for 
modification of the gusset frame attachment at door frame 66.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

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

Costs of Compliance

    We estimate that this proposed AD affects 3 airplanes of U.S. 
registry.

[[Page 24692]]

    The actions required by AD 98-18-24, and retained in this proposed 
AD take about 8 work-hours per product, at an average labor rate of $85 
per work-hour. Based on these figures, the estimated cost of the 
actions that are required by AD 98-18-24 is $680 per product.
    We estimate that it would take about 19 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 $4,845, or $1,615 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    In addition, we estimate that the optional terminating action would 
take about 20 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts costs would be about $60. Based on these 
figures, the estimated cost of the optional terminating action would be 
$1,760 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the proposed reporting requirement in this proposed AD. 
The average labor rate is $85 per hour. Based on these figures, we 
estimate the cost of reporting the inspection results on U.S. operators 
to be $255, or $85 per product.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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 removing Airworthiness Directive (AD) 
98-18-24 Amendment 39-10740 (63 FR 49272, September 15, 1998), and 
adding the following new AD:

Airbus: Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD.

(a) Comments Due Date

    We must receive comments by July 16, 2018.

(b) Affected ADs

    This AD replaces AD 98-18-24 Amendment 39-10740 (63 FR 49272, 
September 15, 1998) (``AD 98-18-24'').

(c) Applicability

    This AD applies to Airbus Model A320-211 and Model A320-231 
airplanes, certificated in any category, serial numbers 0029, 0045, 
0046, 0049 through 0057 inclusive, 0059, 0064, and 0065.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracks on the inner flange 
of door frame 66 at stringer 18 and 20 positions and by the results 
of a full scale fatigue test that indicated the intervals for the 
repetitive inspections required by AD 98-18-24 must be reduced. We 
are issuing this AD to detect and correct fatigue cracking in the 
inner flange of door frame 66, 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) Retained Eddy Current Inspection, With No Changes

    This paragraph restates the requirements of paragraph (a) of AD 
98-18-24, with no changes. For Model A320 series airplanes on which 
Airbus Modification 21778 (reference Airbus Service Bulletin A320-
53-1072, dated November 7, 1995, as revised by Change Notice 0A, 
dated July 5, 1996) has not been accomplished: Prior to the 
accumulation of 20,000 total flight cycles, or within 1 year after 
October 20, 1998 (the effective date of AD 98-18-24), whichever 
occurs later: Perform a rotating probe eddy current inspection to 
detect cracking around the edges of the gusset plate attachment 
holes of the inner flange of door frame 66, left and right, at 
stringer positions P18, P20, and P22, in accordance with Airbus 
Service Bulletin A320-53-1071, dated November 7, 1995, as revised by 
Change Notice 0A, dated July 5,

[[Page 24693]]

1996. If any crack is detected, prior to further flight, repair in 
accordance with a method approved by the Manager, International 
Section, Transport Standards Branch, FAA. Repeat the inspection 
thereafter at intervals not to exceed 20,000 flight cycles.

(h) Retained Optional Terminating Action, With No Changes

    This paragraph restates the optional terminating action of 
paragraph (b) of AD 98-18-24, with no changes. Modification of the 
gusset plate attachment holes of the inner flange of door frame 66, 
left and right (Airbus Modification 21778), in accordance with 
Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as 
revised by Change Notice 0A, dated July 5, 1996, constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (g) of this AD.

(i) New Requirement of This AD: Repetitive Inspections

    At the applicable compliance time specified in figure 1 to 
paragraph (i) of this AD, do a rotating probe eddy current 
inspection to detect cracking around the edges of the gusset plate 
attachment holes of the inner flange of door frame 66, left and 
right, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. 
Repeat the inspection thereafter at intervals not to exceed 10,900 
flight cycles.
[GRAPHIC] [TIFF OMITTED] TP30MY18.000

(j) Corrective Actions

    (1) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on a gusset plate attachment hole: Before 
further flight, repair the affected attachment hole, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1071, Revision 03, dated July 20, 2017, except as required 
by paragraph (n) of this AD.
    (2) If, during any inspection required by paragraph (i) of this 
AD, any crack is found on any other hole of the gusset plate: Before 
further flight, contact the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); 
for approved repair instructions and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(k) Terminating Action for This AD

    (1) Repair of an attachment hole area as required by paragraph 
(j)(1) of this AD terminates the repetitive inspections required by 
paragraph (i) of this AD for that attachment hole area on that 
airplane only.
    (2) Repair of any other hole of the gusset plate, as required by 
paragraph (j)(2) of this AD, does not terminate the repetitive 
inspections required by paragraph (i) of this AD for that airplane, 
unless specified otherwise in the repair instructions provided by 
the Manager, International Section, Transport Standards Branch, FAA; 
or the EASA; or Airbus's EASA DOA.
    (3) Accomplishing the initial inspection required by paragraph 
(i) of this AD terminates the inspections required by paragraph (g) 
of this AD.

(l) Optional Modification

    Modification of the gusset plate attachment holes of the inner 
flange of door frame 66, left and right, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1072, 
Revision 02, dated May 5, 2016, terminates the repetitive 
inspections required by paragraph (i) of this AD for that airplane.

(m) Reporting

    Report the results of the inspection required by paragraph (i) 
of this AD that are done on or after the effective date of this AD 
to Airbus Service Bulletin Reporting Online Application on Airbus 
World (https://w3.airbus.com/), or submit the results to Airbus in 
accordance with the instructions of

[[Page 24694]]

Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 
2017. Submit the report within 30 days after accomplishing the 
inspection required by paragraph (i) of this AD. The report must 
include the inspection results, a description of any discrepancies 
found, the airplane serial number, and the number of landings and 
flight hours on the airplane. If operators have reported findings as 
part of obtaining any corrective actions approved by the EASA DOA, 
operators are not required to report those findings as specified in 
this paragraph.

(n) Service Information Exception

    Where Airbus Service Bulletin A320-53-1071, Revision 03, dated 
July 20, 2017, specifies to contact Airbus for appropriate action, 
and specifies that action as ``RC'' (Required for Compliance): 
Before further flight, accomplish corrective actions in accordance 
with the procedures specified in paragraph (q)(2) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin 
A320-53-1071, Revision 02, dated May 5, 2016.
    (2) This paragraph provides credit for actions identified in 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1072, dated November 7, 1995, as revised by Change Notice 0A, dated 
July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01, 
dated July 4, 2002.

(p) Paperwork Reduction Act Burden Statement

    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 1 hour 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.

(q) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, 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 98-18-24 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 Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (n) 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 AD 2017-0128, dated July 24, 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-2018-0455.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on May 21, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11421 Filed 5-29-18; 8:45 am]
BILLING CODE 4910-13-P
24690 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules

(a) Comments Due Date acceptable for unscheduled maintenance as a including substeps and identified figures, can
We must receive comments by July 16, replacement only for another P/N MLD20– still be done as specified, and the airplane
2018. 626–1 and only into a stowage box P/N can be put back in an airworthy condition.
MXP806–1. If an oxygen mask/regulator
(b) Affected ADs having a part number other than P/N (k) Related Information
None. MLD20–626–1 is installed, it may not be (1) For more information about this AD,
replaced with P/N MLD20–626–1. For the contact Susan L. Monroe, Aerospace
(c) Applicability purposes of this AD, unscheduled Engineer, Cabin Safety and Environmental
This AD applies to all The Boeing maintenance is defined as maintenance that Systems Section, FAA, Seattle ACO Branch,
Company Model 747–8 and 747–8F series was not planned for or scheduled in advance, 2200 South 216th Street, Des Moines, WA
airplanes, certificated in any category. such as changing a defective or unserviceable 98198; phone and fax: 206–231–3570; email:
oxygen mask at dispatch. susan.l.monroe@faa.gov.
(d) Subject (2) For airplanes with an original certificate (2) For service information identified in
Air Transport Association (ATA) of of airworthiness or an original export this AD, contact Boeing Commercial
America Code 35, Oxygen. certificate of airworthiness issued after the Airplanes, Attention: Contractual & Data
effective date of this AD: As of the effective Services (C&DS), 2600 Westminster Blvd.,
(e) Unsafe Condition date of this AD, no person may install oxygen MC 110–SK57, Seal Beach, CA 90740–5600;
This AD was prompted by a report that mask/regulator P/N MLD20–626–1, on any telephone 562–797–1717; internet https://
flightcrew oxygen masks did not function as airplane. www.myboeingfleet.com. You may view this
designed during flight testing. We are issuing (3) For all airplanes: As of the effective referenced service information at the FAA,
this AD to address flightcrew oxygen masks/ date of this AD, no person may install oxygen Transport Standards Branch, 2200 South
regulators that do not deploy correctly, mask/regulator P/N MLD20–726–1, in 216th St., Des Moines, WA. For information
which could result in a delay for the combination with any stowage box part on the availability of this material at the
flightcrew to put on the masks, which may number that is not P/N MXP806–7, on any FAA, call 206–231–3195.
lead to hypoxia and loss of useful airplane. Issued in Des Moines, Washington, on May
consciousness, potentially resulting in loss of 21, 2018.
control of the airplane. (j) Alternative Methods of Compliance
(AMOCs) James Cashdollar,
(f) Compliance Acting Director, System Oversight Division,
(1) The Manager, Seattle ACO Branch,
Comply with this AD within the FAA, has the authority to approve AMOCs Aircraft Certification Service.
compliance times specified, unless already for this AD, if requested using the procedures [FR Doc. 2018–11426 Filed 5–29–18; 8:45 am]
done. found in 14 CFR 39.19. In accordance with BILLING CODE 4910–13–P
(g) Required Actions 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
For airplanes with an original certificate of District Office, as appropriate. If sending
airworthiness, or an original export DEPARTMENT OF TRANSPORTATION
information directly to the manager of the
certificate of airworthiness, issued on or certification office, send it to the attention of
before the effective date of this AD: Within Federal Aviation Administration
the person identified in paragraph (k)(1) of
72 months after the effective date of this AD,
this AD. Information may be emailed to: 9-
inspect for oxygen mask/regulator part
ANM-Seattle-ACO-AMOC-Requests@faa.gov.
14 CFR Part 39
number (P/N) MLD20–626–1 and stowage
(2) Before using any approved AMOC, [Docket No. FAA–2018–0455; Product
box P/N MXP806–1. If any oxygen mask/
notify your appropriate principal inspector, Identifier 2017–NM–121–AD]
regulator P/N MLD20–626–1 or stowage box
or lacking a principal inspector, the manager
P/N MXP806–1 is found, within 72 months RIN 2120–AA64
of the local flight standards district office/
after the effective date of this AD, do all
certificate holding district office.
applicable actions identified as ‘‘RC’’ Airworthiness Directives; Airbus
(3) An AMOC that provides an acceptable
(required for compliance) in, and in Airplanes
level of safety may be used for any repair,
accordance with, the Accomplishment
modification, or alteration required by this
Instructions of Boeing Special Attention
AD if it is approved by the Boeing
AGENCY: Federal Aviation
Service Bulletin 747–35–2133, Revision 1, Administration (FAA), DOT.
dated November 1, 2017, except as provided Commercial Airplanes Organization
Designation Authorization (ODA) that has ACTION: Notice of proposed rulemaking
by paragraph (h) of this AD. A review of
airplane maintenance records is acceptable in been authorized by the Manager, Seattle ACO (NPRM).
lieu of the part number inspection if the part Branch, to make those findings. To be
approved, the repair method, modification SUMMARY: We propose to supersede
numbers of the oxygen mask/regulator and
stowage box can be conclusively determined deviation, or alteration deviation must meet Airworthiness Directive (AD) 98–18–24,
from that review. the certification basis of the airplane, and the which applies to certain Airbus Model
approval must specifically refer to this AD. A320 series airplanes. AD 98–18–24
(h) Exceptions to Service Information (4) Except as required by paragraph (h) of requires repetitive inspections to detect
Specifications this AD: For service information that cracking in the inner flange of a certain
Where Boeing Special Attention Service contains steps that are labeled as RC, the
door frame, and corrective actions, if
Bulletin 747–35–2133, Revision 1, dated provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply. necessary. AD 98–18–24 also provides
November 1, 2017, refers to or specifies
installing a new (or changed) part, for this (i) The steps labeled as RC, including an optional terminating action for the
AD, a new or serviceable (or changed) part substeps under an RC step and any figures repetitive inspections. Since we issued
is acceptable. identified in an RC step, must be done to AD 98–18–24, it has been determined
comply with the AD. If a step or substep is that the compliance times for the
(i) Parts Installation Limitation labeled ‘‘RC Exempt,’’ then the RC repetitive inspections must be reduced.
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(1) For airplanes with an original certificate requirement is removed from that step or This proposed AD would continue to
of airworthiness, or an original export substep. An AMOC is required for any require the repetitive inspections of the
certificate of airworthiness, issued on or deviations to RC steps, including substeps
inner flange of a certain door frame,
before the effective date of this AD: As of the and identified figures.
effective date of this AD, no person may (ii) Steps not labeled as RC may be with reduced repetitive inspection
install an oxygen mask/regulator P/N deviated from using accepted methods in intervals, and corrective action if
MLD20–626–1 on any airplane, except that accordance with the operator’s maintenance necessary. We are proposing this AD to
prior to 72 months after the effective date of or inspection program without obtaining address the unsafe condition on these
this AD, installation of P/N MLD20–626–1 is approval of an AMOC, provided the RC steps, products.

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Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules 24691

DATES: We must receive comments on comments on the overall regulatory, [Airbus] SB A320–53–1072, providing
this proposed AD by July 16, 2018. economic, environmental, and energy instructions for reworking of the attachment
aspects of this proposed AD. We will holes.
ADDRESSES: You may send comments,
Consequently, DGAC France issued
using the procedures found in 14 CFR consider all comments received by the
[French] AD 1996–234–087, later revised
11.43 and 11.45, by any of the following closing date and may amend this [which corresponds to FAA AD 98–18–24],
methods: proposed AD based on those comments. requiring repetitive inspections and,
• Federal eRulemaking Portal: Go to We will post all comments we depending on findings, repair of the
http://www.regulations.gov. Follow the receive, without change, to http:// attachment holes, and including reference to
instructions for submitting comments. www.regulations.gov, including any a reworking procedure, which constitutes
• Fax: 202–493–2251. personal information you provide. We optional terminating action for the repetitive
• Mail: U.S. Department of will also post a report summarizing each inspections of the attachment holes.
substantive verbal contact we receive Since that [French] AD was issued, based
Transportation, Docket Operations, M–
about this proposed AD. on results from a full scale fatigue test, it was
30, West Building Ground Floor, Room determined that the inspection intervals must
W12–140, 1200 New Jersey Avenue SE, Discussion be reduced. Airbus issued SB A320–53–1071
Washington, DC 20590. Revision 03, modifying the inspection
• Hand Delivery: Deliver to Mail We issued AD 98–18–24, Amendment threshold and intervals, and not changing the
address above between 9 a.m. and 5 39–10740 (63 FR 49272, September 15, inspection instructions.
p.m., Monday through Friday, except 1998) (‘‘AD 98–18–24’’), for certain For the reason described above, this
Federal holidays. A320 series airplanes. AD 98–18–24 was [EASA] AD retains the requirement of DGAC
For service information identified in prompted by the results of a fatigue test France AD 1996–234–087 R1, which is
this NPRM, contact Airbus, on simulated flights which revealed superseded, and requires reduction of the
cracks on the inner flange of door frame repetitive inspection interval.
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac 66 at stringers 18 and 20. The cracks You may examine the MCAI in the
Cedex, France; telephone +33 5 61 93 36 were located in the gusset plate AD docket on the internet at http://
96; fax +33 5 61 93 44 51; email attachment holes and were hidden by www.regulations.gov by searching for
account.airworth-eas@airbus.com; the gusset plates. AD 98–18–24 requires and locating Docket No. FAA–2018–
internet http://www.airbus.com. You repetitive inspections to detect cracking 0455.
may view this referenced service in the inner flange of door frame 66, and
corrective actions if necessary. AD 98– Related Service Information Under 1
information at the FAA, Transport CFR Part 51
Standards Branch, 2200 South 216th St., 18–24 also provides an optional
Des Moines, WA. For information on the terminating action for the repetitive Airbus has issued Service Bulletin
availability of this material at the FAA, inspections. We issued AD 98–18–24 to A320–53–1071, Revision 03, dated July
call 206–231–3195. detect and correct fatigue cracking in 20, 2017. This service information
the inner flange of door frame 66, which describes procedures for detailed
Examining the AD Docket could result in reduced structural inspections of the gusset plate
You may examine the AD docket on integrity of the airplane. attachment holes at door frame 66 for
the internet at http:// Since we issued AD 98–18–24, based cracking and corrective action.
www.regulations.gov by searching for on the results from a full scale fatigue Airbus also issued Service Bulletin
and locating Docket No. FAA–2018– test, it has been determined that the A320–53–1072, Revision 02, dated May
0455; or in person at the Docket repetitive inspection intervals must be 5, 2016. This service information
Management Facility between 9 a.m. reduced. describes procedures for modification of
and 5 p.m., Monday through Friday, The European Aviation Safety Agency the gusset frame attachment at door
except Federal holidays. The AD docket (EASA), which is the Technical Agent frame 66.
contains this proposed AD, the for the Member States of the European This service information is reasonably
regulatory evaluation, any comments Union, has issued EASA Airworthiness available because the interested parties
received, and other information. The Directive 2017–0128, dated July 24, have access to it through their normal
street address for the Docket Operations 2017 (referred to after this as the course of business or by the means
office (telephone 800–647–5527) is in Mandatory Continuing Airworthiness identified in the ADDRESSES section.
the ADDRESSES section. Comments will Information, or ‘‘the MCAI’’), to correct
FAA’s Determination and Requirements
be available in the AD docket shortly an unsafe condition for certain Airbus
of This Proposed AD
after receipt. Model A320–211 and A320–231
airplanes. The MCAI states: This product has been approved by
FOR FURTHER INFORMATION CONTACT: the aviation authority of another
Sanjay Ralhan, Aerospace Engineer, During fatigue test on simulated flights,
cracks developed on the inner flange of door
country, and is approved for operation
International Section, Transport in the United States. Pursuant to our
frame 66 at stringer 18 and 20 positions.
Standards Branch, FAA; 2200 South bilateral agreement with the State of
These cracks were located in the gusset plate
216th St., Des Moines, WA 98198; attachment holes and were hidden by the Design Authority, we have been notified
telephone and fax 206–231–3223. plates. of the unsafe condition described in the
SUPPLEMENTARY INFORMATION: This condition, if not detected and MCAI and service information
corrected, could affect the structural integrity referenced above. We are proposing this
Comments Invited of the fuselage.
sradovich on DSK3GMQ082PROD with PROPOSALS

AD because we evaluated all pertinent
We invite you to send any written To address this potential unsafe condition, information and determined an unsafe
relevant data, views, or arguments about Airbus issued Service Bulletin (SB) A320–
53–1071, later revised, to provide
condition exists and is likely to exist or
this proposal. Send your comments to develop on other products of the same
instructions to inspect and repair the gusset
an address listed under the ADDRESSES plate attachment holes at frame 66, at type design.
section. Include ‘‘Docket No. FAA– stringers 18, 20 and 22 both left hand (LH)
2018–0455; Product Identifier 2017– Costs of Compliance
and right hand (RH) side of the fuselage
NM–121–AD’’ at the beginning of your (hereafter collectively referred to as ‘‘the We estimate that this proposed AD
comments. We specifically invite attachment holes’’ in this [EASA] AD), and affects 3 airplanes of U.S. registry.

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24692 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules

The actions required by AD 98–18–24, the FAA Administrator. ‘‘Subtitle VII: PART 39—AIRWORTHINESS
and retained in this proposed AD take Aviation Programs,’’ describes in more DIRECTIVES
about 8 work-hours per product, at an detail the scope of the Agency’s
average labor rate of $85 per work-hour. authority. ■ 1. The authority citation for part 39
Based on these figures, the estimated We are issuing this rulemaking under continues to read as follows:
cost of the actions that are required by the authority described in ‘‘Subtitle VII, Authority: 49 U.S.C. 106(g), 40113, 44701.
AD 98–18–24 is $680 per product. Part A, Subpart III, Section 44701:
We estimate that it would take about General requirements.’’ Under that § 39.13 [Amended]
19 work-hours per product to comply section, Congress charges the FAA with ■ 2. The FAA amends § 39.13 by
with the basic requirements of this promoting safe flight of civil aircraft in removing Airworthiness Directive (AD)
proposed AD. The average labor rate is air commerce by prescribing regulations 98–18–24 Amendment 39–10740 (63 FR
$85 per work-hour. Based on these for practices, methods, and procedures 49272, September 15, 1998), and adding
figures, we estimate the cost of this the Administrator finds necessary for the following new AD:
proposed AD on U.S. operators to be safety in air commerce. This regulation Airbus: Docket No. FAA–2018–0455; Product
$4,845, or $1,615 per product. is within the scope of that authority Identifier 2017–NM–121–AD.
We have received no definitive data because it addresses an unsafe condition
that would enable us to provide cost (a) Comments Due Date
that is likely to exist or develop on
estimates for the on-condition actions products identified in this rulemaking We must receive comments by July 16,
specified in this proposed AD. 2018.
action.
In addition, we estimate that the This AD is issued in accordance with (b) Affected ADs
optional terminating action would take authority delegated by the Executive This AD replaces AD 98–18–24
about 20 work-hours per product, at an Director, Aircraft Certification Service, Amendment 39–10740 (63 FR 49272,
average labor rate of $85 per work-hour. as authorized by FAA Order 8000.51C. September 15, 1998) (‘‘AD 98–18–24’’).
Required parts costs would be about In accordance with that order, issuance (c) Applicability
$60. Based on these figures, the of ADs is normally a function of the
estimated cost of the optional This AD applies to Airbus Model A320–
Compliance and Airworthiness 211 and Model A320–231 airplanes,
terminating action would be $1,760 per Division, but during this transition certificated in any category, serial numbers
product. period, the Executive Director has 0029, 0045, 0046, 0049 through 0057
We also estimate that it would take delegated the authority to issue ADs inclusive, 0059, 0064, and 0065.
about 1 work-hour per product to applicable to transport category
comply with the proposed reporting (d) Subject
airplanes to the Director of the System
requirement in this proposed AD. The Oversight Division. Air Transport Association (ATA) of
average labor rate is $85 per hour. Based America Code 53, Fuselage.
on these figures, we estimate the cost of Regulatory Findings
(e) Reason
reporting the inspection results on U.S. We determined that this proposed AD This AD was prompted by a report of
operators to be $255, or $85 per product. would not have federalism implications cracks on the inner flange of door frame 66
Paperwork Reduction Act under Executive Order 13132. This at stringer 18 and 20 positions and by the
proposed AD would not have a results of a full scale fatigue test that
A federal agency may not conduct or substantial direct effect on the States, on indicated the intervals for the repetitive
sponsor, and a person is not required to the relationship between the national inspections required by AD 98–18–24 must
respond to, nor shall a person be subject Government and the States, or on the be reduced. We are issuing this AD to detect
to penalty for failure to comply with a distribution of power and and correct fatigue cracking in the inner
collection of information subject to the flange of door frame 66, which could result
responsibilities among the various
requirements of the Paperwork in reduced structural integrity of the
levels of government. airplane.
Reduction Act unless that collection of For the reasons discussed above, I
information displays a current valid certify this proposed regulation: (f) Compliance
OMB control number. The control 1. Is not a ‘‘significant regulatory Comply with this AD within the
number for the collection of information action’’ under Executive Order 12866; compliance times specified, unless already
required by this AD is 2120–0056. The 2. Is not a ‘‘significant rule’’ under the done.
paperwork cost associated with this AD DOT Regulatory Policies and Procedures (g) Retained Eddy Current Inspection, With
has been detailed in the Costs of (44 FR 11034, February 26, 1979); No Changes
Compliance section of this document 3. Will not affect intrastate aviation in
and includes time for reviewing This paragraph restates the requirements of
Alaska; and paragraph (a) of AD 98–18–24, with no
instructions, as well as completing and 4. Will not have a significant changes. For Model A320 series airplanes on
reviewing the collection of information. economic impact, positive or negative, which Airbus Modification 21778 (reference
Therefore, all reporting associated with on a substantial number of small entities Airbus Service Bulletin A320–53–1072,
this AD is mandatory. Comments under the criteria of the Regulatory dated November 7, 1995, as revised by
concerning the accuracy of this burden Flexibility Act. Change Notice 0A, dated July 5, 1996) has
and suggestions for reducing the burden not been accomplished: Prior to the
should be directed to the FAA at 800 List of Subjects in 14 CFR Part 39 accumulation of 20,000 total flight cycles, or
Air transportation, Aircraft, Aviation within 1 year after October 20, 1998 (the
sradovich on DSK3GMQ082PROD with PROPOSALS

Independence Ave. SW, Washington,
DC 20591, ATTN: Information safety, Incorporation by reference, effective date of AD 98–18–24), whichever
occurs later: Perform a rotating probe eddy
Collection Clearance Officer, AES–200. Safety.
current inspection to detect cracking around
Authority for This Rulemaking The Proposed Amendment the edges of the gusset plate attachment holes
of the inner flange of door frame 66, left and
Title 49 of the United States Code Accordingly, under the authority right, at stringer positions P18, P20, and P22,
specifies the FAA’s authority to issue delegated to me by the Administrator, in accordance with Airbus Service Bulletin
rules on aviation safety. Subtitle I, the FAA proposes to amend 14 CFR part A320–53–1071, dated November 7, 1995, as
section 106, describes the authority of 39 as follows: revised by Change Notice 0A, dated July 5,

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24694 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Proposed Rules

Airbus Service Bulletin A320–53–1071, Office, as appropriate. If sending information DEPARTMENT OF TRANSPORTATION
Revision 03, dated July 20, 2017. Submit the directly to the International Section, send it
report within 30 days after accomplishing the to the attention of the person identified in Federal Aviation Administration
inspection required by paragraph (i) of this paragraph (r)(2) of this AD. Information may
AD. The report must include the inspection be emailed to: 9-ANM-116-AMOC-
results, a description of any discrepancies REQUESTS@faa.gov.
14 CFR Part 39
found, the airplane serial number, and the (i) Before using any approved AMOC, [Docket No. FAA–2018–0453; Product
number of landings and flight hours on the notify your appropriate principal inspector, Identifier 2018–NM–028–AD]
airplane. If operators have reported findings or lacking a principal inspector, the manager
as part of obtaining any corrective actions of the local flight standards district office/ RIN 2120–AA64
approved by the EASA DOA, operators are certificate holding district office.
not required to report those findings as (ii) AMOCs approved previously for AD Airworthiness Directives; Bombardier,
specified in this paragraph. 98–18–24 are approved as AMOCs for the Inc., Airplanes
corresponding provisions of this AD.
(n) Service Information Exception (2) Contacting the Manufacturer: As of the AGENCY: Federal Aviation
Where Airbus Service Bulletin A320–53– effective date of this AD, for any requirement Administration (FAA), DOT.
1071, Revision 03, dated July 20, 2017, in this AD to obtain corrective actions from ACTION: Notice of proposed rulemaking
specifies to contact Airbus for appropriate a manufacturer, the action must be (NPRM).
action, and specifies that action as ‘‘RC’’ accomplished using a method approved by
(Required for Compliance): Before further the Manager, International Section, Transport SUMMARY: We propose to adopt a new
flight, accomplish corrective actions in Standards Branch, FAA; or the EASA; or airworthiness directive (AD) for certain
accordance with the procedures specified in Airbus’s EASA DOA. If approved by the Bombardier, Inc., Model DHC–8–400
paragraph (q)(2) of this AD. DOA, the approval must include the DOA-
authorized signature.
series airplanes. This proposed AD was
(o) Credit for Previous Actions prompted by reports of the nose landing
(3) Required for Compliance (RC): Except
(1) This paragraph provides credit for as required by paragraph (n) of this AD: If gear (NLG) locking in a partially
actions required by paragraph (i) of this AD, any service information contains procedures extended position due to loose bushings
if those actions were performed before the or tests that are identified as RC, those on the lock link of the NLG locking
effective date of this AD using Airbus Service procedures and tests must be done to comply mechanism. This proposed AD would
Bulletin A320–53–1071, Revision 01, dated with this AD; any procedures or tests that are require inspecting the bushings and the
July 4, 2002; or Airbus Service Bulletin not identified as RC are recommended. Those
A320–53–1071, Revision 02, dated May 5, lower lock link of the NLG for
procedures and tests that are not identified
2016. as RC may be deviated from using accepted
discrepancies, and corrective actions if
(2) This paragraph provides credit for methods in accordance with the operator’s necessary. We are proposing this AD to
actions identified in paragraph (l) of this AD, maintenance or inspection program without address the unsafe condition on these
if those actions were performed before the obtaining approval of an AMOC, provided products.
effective date of this AD using Airbus Service the procedures and tests identified as RC can
Bulletin A320–53–1072, dated November 7, DATES: We must receive comments on
be done and the airplane can be put back in
1995, as revised by Change Notice 0A, dated an airworthy condition. Any substitutions or this proposed AD by July 16, 2018.
July 5, 1996; or Airbus Service Bulletin changes to procedures or tests identified as ADDRESSES: You may send comments,
A320–53–1072, Revision 01, dated July 4, RC require approval of an AMOC. using the procedures found in 14 CFR
2002. 11.43 and 11.45, by any of the following
(r) Related Information
(p) Paperwork Reduction Act Burden methods:
(1) Refer to Mandatory Continuing • Federal eRulemaking Portal: Go to
Statement
Airworthiness Information (MCAI) EASA AD
A federal agency may not conduct or 2017–0128, dated July 24, 2017, for related
http://www.regulations.gov. Follow the
sponsor, and a person is not required to information. This MCAI may be found in the instructions for submitting comments.
respond to, nor shall a person be subject to AD docket on the internet at http:// • Fax: 202–493–2251.
a penalty for failure to comply with a www.regulations.gov by searching for and • Mail: U.S. Department of
collection of information subject to the locating Docket No. FAA–2018–0455. Transportation, Docket Operations, M–
requirements of the Paperwork Reduction (2) For more information about this AD, 30, West Building Ground Floor, Room
Act unless that collection of information contact Sanjay Ralhan, Aerospace Engineer, W12–140, 1200 New Jersey Avenue SE,
displays a current valid OMB Control International Section, Transport Standards
Number. The OMB Control Number for this
Washington, DC 20590.
information collection is 2120–0056. Public
Branch, FAA; 2200 South 216th St., Des • Hand Delivery: Deliver to Mail
Moines, WA 98198; telephone and fax 206– address above between 9 a.m. and 5
reporting for this collection of information is 231–3223.
estimated to be approximately 1 hour per (3) For service information identified in
p.m., Monday through Friday, except
response, including the time for reviewing this AD, contact Airbus, Airworthiness Federal holidays.
instructions, completing and reviewing the Office—EIAS, 1 Rond Point Maurice For service information identified in
collection of information. All responses to Bellonte, 31707 Blagnac Cedex, France; this NPRM, contact Bombardier, Inc., Q-
this collection of information are mandatory. telephone +33 5 61 93 36 96; fax +33 5 61 Series Technical Help Desk, 123 Garratt
Comments concerning the accuracy of this 93 44 51; email account.airworth-eas@ Boulevard, Toronto, Ontario M3K 1Y5,
burden and suggestions for reducing the airbus.com; internet http://www.airbus.com.
burden should be directed to the FAA at: 800 Canada; telephone: 416–375–4000; fax:
You may view this service information at the 416–375–4539; email: thd.qseries@
Independence Ave. SW, Washington, DC FAA, Transport Standards Branch, 2200
20591, Attn: Information Collection aero.bombardier.com; internet: http://
South 216th St., Des Moines, WA. For
Clearance Officer, AES–200.
information on the availability of this
www.bombardier.com. You may view
this service information at the FAA,
sradovich on DSK3GMQ082PROD with PROPOSALS

(q) Other FAA AD Provisions material at the FAA, call 206–231–3195.
Transport Standards Branch, 2200
(1) Alternative Methods of Compliance Issued in Des Moines, Washington, on May South 216th St., Des Moines, WA. For
(AMOCs): The Manager, International 21, 2018.
Section, Transport Standards Branch, FAA, information on the availability of this
James Cashdollar, material at the FAA, call 206–231–3195.
has the authority to approve AMOCs for this
Acting Director, System Oversight Division,
AD, if requested using the procedures found Examining the AD Docket
Aircraft Certification Service.
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal [FR Doc. 2018–11421 Filed 5–29–18; 8:45 am] You may examine the AD docket on
inspector or local Flight Standards District BILLING CODE 4910–13–P the internet at http://

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Document Created: 2018-05-30 01:01:28
Document Modified: 2018-05-30 01:01:28
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 July 16, 2018.
Contact		Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA; 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
FR Citation		83 FR 24690
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
83 FR 24690 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 104 (May 30, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
