82_FR_36058 82 FR 35911 - Airworthiness Directives; Airbus Airplanes

82 FR 35911 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 147 (August 2, 2017)

Page Range35911-35914
FR Document2017-16052

We propose to supersede Airworthiness Directive (AD) 2012-21- 04, which applies to all Airbus Model A300 series airplanes; Model A310 series airplanes; and 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). AD 2012-21-04 currently requires repetitive inspections for, and replacement of, any cracked hood halves of fuel pump canisters. Since we issued AD 2012-21-04, we allowed inspections of the outer tank and trim tank fuel pump canister hood halves to be terminated. However, we have received reports of new in-service events of outer tank fuel pump canister hood cracking. This proposed AD would retain the requirements of AD 2012-21-04, reinstate the terminated inspections, and add optional terminating actions. We are proposing this AD to address the unsafe condition on these products.

Federal Register, Volume 82 Issue 147 (Wednesday, August 2, 2017) 
[Federal Register Volume 82, Number 147 (Wednesday, August 2, 2017)]
[Proposed Rules]
[Pages 35911-35914]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-16052]


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

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

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


Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / 
Proposed Rules

[[Page 35911]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0714; Directorate Identifier 2017-NM-042-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) 2012-21-
04, which applies to all Airbus Model A300 series airplanes; Model A310 
series airplanes; and 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). AD 2012-21-04 currently 
requires repetitive inspections for, and replacement of, any cracked 
hood halves of fuel pump canisters. Since we issued AD 2012-21-04, we 
allowed inspections of the outer tank and trim tank fuel pump canister 
hood halves to be terminated. However, we have received reports of new 
in-service events of outer tank fuel pump canister hood cracking. This 
proposed AD would retain the requirements of AD 2012-21-04, reinstate 
the terminated inspections, and add optional terminating actions. We 
are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by September 18, 
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: account.airworth-eas@airbus.com; 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-
0714; 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 proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0714; 
Directorate Identifier 2017-NM-042-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 October 25, 2012, we issued AD 2012-21-04, Amendment 39-17220 
(77 FR 64701, October 23, 2012) (``AD 2012-21-04''), for all Airbus 
Model A300 series airplanes; Model A310 series airplanes; and Model 
A300 B4-600, B4-600R, and Model A300-600 series airplanes. AD 2012-21-
04 was prompted by reports of cracked fuel pump canister hoods located 
in fuel tanks. AD 2012-21-04 requires repetitive inspections for, and 
replacement of, any cracked hood halves of fuel pump canisters. We 
issued AD 2012-21-04 to prevent any detached canister hood fragments/
debris from being ingested into the fuel feed system, and becoming a 
potential source of ignition with consequent fire or explosion.
    Since we issued AD 2012-21-04 (which corresponds to European 
Aviation Safety Agency (EASA) AD 2011-0124, dated June 30, 2011), EASA 
has issued EASA AD 2011-0124R1, dated September 5, 2014. That EASA AD 
introduced optional terminating action for the wing inner and center 
fuel tanks, and cancelled the repetitive inspections of the fuel pump 
canister hood halves in outer wing and trim tanks, for which no cracks 
had been reported following the initial inspection. The FAA provided a 
global alternative method of compliance (AMOC) to AD 2012-21-04 
providing relief to operators from conducting the inspection for the 
fuel pump canister hoods in the outer wing and trim tanks. Since the 
FAA provided the global AMOC, we have received reports of new in-
service events of outer tank fuel pump canister hood cracking.
    EASA has issued AD 2017-0051, dated March 23, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; Model A310 series airplanes;

[[Page 35912]]

and Model A300-600 series airplanes. The MCAI states:

    Reports were received of finding cracked fuel pump canister 
hoods located in fuel tanks on in-service aeroplanes. Initial 
analyses, laboratory testing and examinations suggested that 
vibration-induced fatigue could have caused these cracks. However, 
initial data could not exclude some other potential contributing 
factors.
    This condition, if not detected and corrected, could lead to 
detached canister hood fragments or debris being ingested into the 
fuel feed system. In addition, metallic debris inside the fuel tank 
could result in a potential source of fuel vapour ignition, possibly 
resulting in a fire or fuel tank explosion and consequent loss of 
the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2011-
0124 (later revised) [FAA AD 2012-21-04 corresponds to EASA AD 2011-
0124] to require repetitive inspections of the canister hood halves 
installed on all fuel pump canisters and, if any damage was found, 
replacement. EASA AD 2011-0124R1 introduced an optional terminating 
action for the wing inner and centre fuel tanks, and cancelled the 
repetitive inspections of the fuel pump canister hoods in outer wing 
and trim tanks, for which no cracks had been reported following the 
initial inspection.
    Since that [EASA] AD was issued, new in service events of outer 
tank fuel pump canister hood cracking have been reported. 
Consequently, the canister hoods of the outer tank fuel pumps and 
trim tank fuel pumps will need to be inspected.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0124R1, which is superseded, retaining 
the repetitive inspections of fuel pump canister hoods in wing inner 
and centre tanks, and reintroduces repetitive detailed inspections 
(DET) for outer tank and trim tank fuel pump canister hoods. This 
[EASA] AD also retains the existing optional terminating action for 
the repetitive DET of wing inner and centre tank fuel pump canister 
hoods, and introduces a new optional terminating action for the 
repetitive DET of the outer and trim tank fuel pump canister hoods 
required by this [EASA] AD.

    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-
0714.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Mandatory Service Bulletin A300-28-0089, Revision 
03, dated December 16, 2016. This service information describes 
procedures for repetitive detailed inspections of all fuel pump 
locations (center, wing-inner, and wing-outer tank), and replacing any 
cracked hood halves of fuel pump canisters.
     Airbus Service Bulletin A300-28-0092, Revision 01, dated 
August 29, 2014; Airbus Service Bulletin A300-28-6110, Revision 01, 
dated August 29, 2014; and Airbus Service Bulletin A310-28-2175, 
Revision 01, dated August 29, 2014. This service information describes 
procedures for replacement of the hood halves of the fuel pump 
canisters with newer design hood halves for the wing-inner tank and the 
center tank fuel pumps. These documents are distinct since they apply 
to different airplane models.
     Airbus Service Bulletin A300-28-0094, Revision 00, dated 
January 9, 2017. This service information describes procedures for 
replacement of the hood halves of the fuel pump canisters with newer 
design hood halves for the wing-outer tank.
     Airbus Mandatory Service Bulletin A300-28-6106, Revision 
03, dated December 16, 2016; and Airbus Mandatory Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016. This service 
information describes procedures for repetitive detailed inspections of 
all fuel pump locations (center, wing-inner, wing-outer, and trim 
tank), and replacing any cracked hood halves of fuel pump canisters. 
These documents are distinct since they apply to different airplane 
models.
     Airbus Service Bulletin A300-28-6114, Revision 00, dated 
January 9, 2017; and Airbus Service Bulletin A310-28-2178, Revision 00, 
January 9, 2017. This service information describes procedures for 
replacement of the hood halves of the fuel pump canisters with newer 
design hood halves for the wing-outer tank and the trim tank fuel 
pumps. These documents are distinct since they apply to different 
airplane models.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

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

Costs of Compliance

    We estimate that this proposed AD affects 168 airplanes of U.S. 
registry.
    The actions required by AD 2012-21-04, and retained in this 
proposed AD take about 12 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 2012-21-04 is $1,020 per 
product.
    We also estimate that it would take about 9 work-hours per product 
to comply with the new basic requirements of this proposed AD, at an 
average labor rate of $85 per work-hour. Based on these figures, we 
estimate the cost of the new basic requirements of this proposed AD on 
U.S. operators to be $128,520, or $765 per product.
    In addition, we estimate that the optional terminating actions 
would take about 1 work-hour and require parts costing $255, for a cost 
of $340 per product. We have no way of determining the number of 
aircraft that might need these actions.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 35913]]

    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) 
2012-21-04, Amendment 39-17220 (77 FR 64701, October 23, 2012), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0714; Directorate Identifier 2017-NM-
042-AD.

(a) Comments Due Date

    We must receive comments by September 18, 2017.

(b) Affected ADs

    This AD replaces AD 2012-21-04, Amendment 39-17220 (77 FR 64701, 
October 23, 2012) (``AD 2012-21-04'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all certificated models, all manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.
    (3) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by reports of cracked fuel pump canister 
hoods located in fuel tanks and new in-service events of outer tank 
fuel pump canister hood cracking. We are issuing this AD to prevent 
any detached canister hood fragments/debris from being ingested into 
the fuel feed system, and becoming a potential source of ignition 
with consequent fire or explosion.

(f) Compliance

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

(g) Retained Initial Inspection and Replacement, With Revised 
Requirements and Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-21-04, with revised service information. Within 30 months after 
November 27, 2012 (the effective date of AD 2012-21-04), do a 
detailed inspection for cracking of the fuel pump canister hood 
halves installed on all wing center and inner tank fuel pump 
canisters having part numbers (P/N) 2052C11, 2052C12, and C93R51-
601, in accordance with the Accomplishment Instructions of the 
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD, as applicable. If any crack is found on any fuel pump 
canister hood half during any inspection, before further flight, 
replace the fuel pump canister hood half, in accordance with the 
Accomplishment Instructions of the service bulletin specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Mandatory Service 
Bulletin A300-28-0089, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A300-28-
0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Mandatory 
Service Bulletin A300-28-6106, Revision 01, including Inspection 
Findings--Reporting Sheet, dated April 15, 2011; or Airbus Service 
Bulletin A300-28-6106, Revision 03, dated December 16, 2016. As of 
the effective date of this AD, only use Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Mandatory Service 
Bulletin A310-28-2173, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A310-28-
2173, Revision 03, dated December 16, 2016.

(h) Retained Repetitive Inspections, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-21-04, with no changes. Within 30 months after accomplishing 
the actions specified in paragraph (g) of this AD, and thereafter at 
intervals not to exceed 30 months, repeat the detailed inspection 
specified in paragraph (g) of this AD.

(i) New Repetitive Inspections and Replacement of the Outer Tank and 
Trim Tank Fuel Pump Canister Hood Halves

    Within 30 months after the effective date of this AD, do a 
detailed inspection for cracking of the outer tank and trim tank, as 
applicable, fuel pump canister hood halves installed on all fuel 
pump canisters having part numbers (P/N) 2052C11, 2052C12, and 
C93R51-601, in accordance with the Accomplishment Instructions of 
the service bulletin specified in paragraph (i)(1), (i)(2), or 
(i)(3) of this AD, as applicable. Repeat the inspection thereafter 
at intervals not to exceed 30 months. If any crack is found on any 
fuel pump canister hood half during any inspection, before further 
flight, replace the fuel pump canister hood half, in accordance with 
the Accomplishment Instructions of the service bulletin specified in 
paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016.

(j) New Optional Terminating Actions

    Replacement of the fuel pump canister hood halves installed on 
all fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-
601, constitutes terminating action for the inspections required by 
paragraphs (g) and (h) of this AD. The replacement of the fuel pump 
canister hood halves must be done in accordance with the 
Accomplishment Instructions of the service information specified in 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0092, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-0094, Revision 00, dated January 9, 2017 (for outer 
tank fuel pump canister hood halves).
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6110, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-6114, Revision 00, dated January 9, 2017 (for outer 
tank and trim tank fuel pump canister hood halves).
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2175, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A310-28-2178, Revision 00, January 9, 2017 (for outer tank 
and trim tank fuel pump canister hood halves).

(k) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; or Airbus Service

[[Page 35914]]

Bulletin A300-28-0089, Revision 02, dated April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; or Airbus Service Bulletin A300-28-6106, Revision 02, dated 
April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; or Airbus Mandatory Service Bulletin A310-28-2173, Revision 
02, dated April 25, 2014.
    (2) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; Airbus Service Bulletin A300-28-0089, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A300-28-0089, Revision 02, 
dated April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; Airbus Service Bulletin A300-28-6106, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A300-28-6106, Revision 02, 
dated April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; Airbus Service Bulletin A310-28-2173, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A310-28-2173, Revision 02, 
dated April 25, 2014.
    (3) This paragraph provides credit for the actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A300-28-
6110, Revision 00, dated November 28, 2013.

(l) Other FAA AD Provisions

    (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 (m)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (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 2012-21-04, Amendment 39-
17220 (77 FR 64701, October 23, 2012), are not approved as AMOCs 
with 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 the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0051, dated March 23, 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-2017-0714.
    (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.
    (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: account.airworth-eas@airbus.com; 
Internet: http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 19, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-16052 Filed 8-1-17; 8:45 am]
 BILLING CODE 4910-13-P

35911 Proposed Rules Federal Register Vol. 82, No. 147 Wednesday, August 2, 2017 This section of the FEDERAL REGISTER • Mail: U.S. Department of consider all comments received by the contains notices to the public of the proposed Transportation, Docket Operations, M– closing date and may amend this issuance of rules and regulations. The 30, West Building Ground Floor, Room proposed AD based on those comments. purpose of these notices is to give interested W12–140, 1200 New Jersey Avenue SE., We will post all comments we persons an opportunity to participate in the Washington, DC 20590. receive, without change, to http:// rule making prior to the adoption of the final rules. • Hand Delivery: Deliver to Mail www.regulations.gov, including any address above between 9 a.m. and 5 personal information you provide. We p.m., Monday through Friday, except will also post a report summarizing each DEPARTMENT OF TRANSPORTATION Federal holidays. substantive verbal contact we receive For service information identified in about this proposed AD. Federal Aviation Administration this NPRM, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Discussion 14 CFR Part 39 Point Maurice Bellonte, 31707 Blagnac On October 25, 2012, we issued AD Cedex, France; telephone: +33 5 61 93 2012–21–04, Amendment 39–17220 (77 [Docket No. FAA–2017–0714; Directorate 36 96; fax: +33 5 61 93 44 51; email: FR 64701, October 23, 2012) (‘‘AD Identifier 2017–NM–042–AD] account.airworth-eas@airbus.com; 2012–21–04’’), for all Airbus Model RIN 2120–AA64 Internet: http://www.airbus.com. You A300 series airplanes; Model A310 may view this referenced service series airplanes; and Model A300 B4– Airworthiness Directives; Airbus information at the FAA, Transport 600, B4–600R, and Model A300–600 Airplanes Airplane Directorate, 1601 Lind Avenue series airplanes. AD 2012–21–04 was SW., Renton, WA. For information on prompted by reports of cracked fuel AGENCY: Federal Aviation the availability of this material at the pump canister hoods located in fuel Administration (FAA), DOT. FAA, call 425–227–1221. tanks. AD 2012–21–04 requires ACTION: Notice of proposed rulemaking repetitive inspections for, and (NPRM). Examining the AD Docket replacement of, any cracked hood You may examine the AD docket on halves of fuel pump canisters. We SUMMARY: We propose to supersede the Internet at http:// Airworthiness Directive (AD) 2012–21– issued AD 2012–21–04 to prevent any www.regulations.gov by searching for detached canister hood fragments/debris 04, which applies to all Airbus Model and locating Docket No. FAA–2017– A300 series airplanes; Model A310 from being ingested into the fuel feed 0714; or in person at the Docket system, and becoming a potential source series airplanes; and Model A300 B4– Management Facility between 9 a.m. 600, B4–600R, and F4–600R series of ignition with consequent fire or and 5 p.m., Monday through Friday, explosion. airplanes, and Model A300 C4–605R except Federal holidays. The AD docket Variant F airplanes (collectively called Since we issued AD 2012–21–04 contains this proposed AD, the (which corresponds to European Model A300–600 series airplanes). AD regulatory evaluation, any comments 2012–21–04 currently requires Aviation Safety Agency (EASA) AD received, and other information. The 2011–0124, dated June 30, 2011), EASA repetitive inspections for, and street address for the Docket Operations replacement of, any cracked hood has issued EASA AD 2011–0124R1, office (telephone: 800–647–5527) is in dated September 5, 2014. That EASA halves of fuel pump canisters. Since we the ADDRESSES section. Comments will issued AD 2012–21–04, we allowed AD introduced optional terminating be available in the AD docket shortly action for the wing inner and center fuel inspections of the outer tank and trim after receipt. tank fuel pump canister hood halves to tanks, and cancelled the repetitive FOR FURTHER INFORMATION CONTACT: Dan inspections of the fuel pump canister be terminated. However, we have received reports of new in-service Rodina, Aerospace Engineer, hood halves in outer wing and trim events of outer tank fuel pump canister International Branch, ANM–116, tanks, for which no cracks had been hood cracking. This proposed AD would Transport Airplane Directorate, FAA, reported following the initial retain the requirements of AD 2012–21– 1601 Lind Avenue SW., Renton, WA inspection. The FAA provided a global 04, reinstate the terminated inspections, 98057–3356; telephone: 425–227–2125; alternative method of compliance and add optional terminating actions. fax: 425–227–1149. (AMOC) to AD 2012–21–04 providing We are proposing this AD to address the SUPPLEMENTARY INFORMATION: relief to operators from conducting the unsafe condition on these products. inspection for the fuel pump canister Comments Invited hoods in the outer wing and trim tanks. DATES: We must receive comments on We invite you to send any written Since the FAA provided the global this proposed AD by September 18, relevant data, views, or arguments about AMOC, we have received reports of new 2017. this proposed AD. Send your comments in-service events of outer tank fuel jstallworth on DSKBBY8HB2PROD with PROPOSALS ADDRESSES: You may send comments, to an address listed under the pump canister hood cracking. using the procedures found in 14 CFR ADDRESSES section. Include ‘‘Docket No. EASA has issued AD 2017–0051, 11.43 and 11.45, by any of the following FAA–2017–0714; Directorate Identifier dated March 23, 2017 (referred to after methods: 2017–NM–042–AD’’ at the beginning of this as the Mandatory Continuing • Federal eRulemaking Portal: Go to your comments. We specifically invite Airworthiness Information, or ‘‘the http://www.regulations.gov. Follow the comments on the overall regulatory, MCAI’’), to correct an unsafe condition instructions for submitting comments. economic, environmental, and energy for all Airbus Model A300 series • Fax: 202–493–2251. aspects of this proposed AD. We will airplanes; Model A310 series airplanes; VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\02AUP1.SGM 02AUP1

35912 Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules and Model A300–600 series airplanes. • Airbus Service Bulletin A300–28– Costs of Compliance The MCAI states: 0092, Revision 01, dated August 29, We estimate that this proposed AD Reports were received of finding cracked 2014; Airbus Service Bulletin A300–28– affects 168 airplanes of U.S. registry. fuel pump canister hoods located in fuel 6110, Revision 01, dated August 29, The actions required by AD 2012–21– tanks on in-service aeroplanes. Initial 2014; and Airbus Service Bulletin 04, and retained in this proposed AD analyses, laboratory testing and examinations A310–28–2175, Revision 01, dated take about 12 work-hours per product, suggested that vibration-induced fatigue August 29, 2014. This service could have caused these cracks. However, at an average labor rate of $85 per work- information describes procedures for hour. Based on these figures, the initial data could not exclude some other replacement of the hood halves of the potential contributing factors. estimated cost of the actions that are This condition, if not detected and fuel pump canisters with newer design required by AD 2012–21–04 is $1,020 corrected, could lead to detached canister hood halves for the wing-inner tank and per product. hood fragments or debris being ingested into the center tank fuel pumps. These We also estimate that it would take the fuel feed system. In addition, metallic documents are distinct since they apply about 9 work-hours per product to debris inside the fuel tank could result in a to different airplane models. comply with the new basic potential source of fuel vapour ignition, • Airbus Service Bulletin A300–28– possibly resulting in a fire or fuel tank requirements of this proposed AD, at an 0094, Revision 00, dated January 9, average labor rate of $85 per work-hour. explosion and consequent loss of the aeroplane. 2017. This service information describes Based on these figures, we estimate the To address this potential unsafe condition, procedures for replacement of the hood cost of the new basic requirements of EASA issued AD 2011–0124 (later revised) halves of the fuel pump canisters with this proposed AD on U.S. operators to [FAA AD 2012–21–04 corresponds to EASA newer design hood halves for the wing- be $128,520, or $765 per product. AD 2011–0124] to require repetitive outer tank. In addition, we estimate that the inspections of the canister hood halves • Airbus Mandatory Service Bulletin optional terminating actions would take installed on all fuel pump canisters and, if about 1 work-hour and require parts any damage was found, replacement. EASA A300–28–6106, Revision 03, dated AD 2011–0124R1 introduced an optional December 16, 2016; and Airbus costing $255, for a cost of $340 per terminating action for the wing inner and Mandatory Service Bulletin A310–28– product. We have no way of centre fuel tanks, and cancelled the repetitive 2173, Revision 03, dated December 16, determining the number of aircraft that inspections of the fuel pump canister hoods 2016. This service information describes might need these actions. in outer wing and trim tanks, for which no procedures for repetitive detailed cracks had been reported following the initial Authority for This Rulemaking inspections of all fuel pump locations inspection. (center, wing-inner, wing-outer, and Title 49 of the United States Code Since that [EASA] AD was issued, new in trim tank), and replacing any cracked specifies the FAA’s authority to issue service events of outer tank fuel pump rules on aviation safety. Subtitle I, canister hood cracking have been reported. hood halves of fuel pump canisters. These documents are distinct since they section 106, describes the authority of Consequently, the canister hoods of the outer tank fuel pumps and trim tank fuel pumps apply to different airplane models. the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more will need to be inspected. • Airbus Service Bulletin A300–28– For the reasons described above, this detail the scope of the Agency’s 6114, Revision 00, dated January 9, [EASA] AD retains the requirements of EASA authority. 2017; and Airbus Service Bulletin AD 2011–0124R1, which is superseded, We are issuing this rulemaking under A310–28–2178, Revision 00, January 9, retaining the repetitive inspections of fuel the authority described in ‘‘Subtitle VII, pump canister hoods in wing inner and 2017. This service information describes Part A, Subpart III, Section 44701: centre tanks, and reintroduces repetitive procedures for replacement of the hood General requirements.’’ Under that detailed inspections (DET) for outer tank and halves of the fuel pump canisters with section, Congress charges the FAA with trim tank fuel pump canister hoods. This newer design hood halves for the wing- promoting safe flight of civil aircraft in [EASA] AD also retains the existing optional outer tank and the trim tank fuel pumps. terminating action for the repetitive DET of air commerce by prescribing regulations These documents are distinct since they wing inner and centre tank fuel pump for practices, methods, and procedures apply to different airplane models. canister hoods, and introduces a new the Administrator finds necessary for optional terminating action for the repetitive This service information is reasonably safety in air commerce. This regulation DET of the outer and trim tank fuel pump available because the interested parties is within the scope of that authority canister hoods required by this [EASA] AD. have access to it through their normal because it addresses an unsafe condition You may examine the MCAI in the course of business or by the means that is likely to exist or develop on AD docket on the Internet at http:// identified in the ADDRESSES section. products identified in this rulemaking www.regulations.gov by searching for FAA’s Determination and Requirements action. and locating Docket No. FAA–2017– of This Proposed AD Regulatory Findings 0714. This product has been approved by We determined that this proposed AD Related Service Information Under 1 the aviation authority of another would not have federalism implications CFR Part 51 country, and is approved for operation under Executive Order 13132. This Airbus has issued the following in the United States. Pursuant to our proposed AD would not have a service information. bilateral agreement with the State of substantial direct effect on the States, on • Airbus Mandatory Service Bulletin Design Authority, we have been notified the relationship between the national jstallworth on DSKBBY8HB2PROD with PROPOSALS A300–28–0089, Revision 03, dated of the unsafe condition described in the Government and the States, or on the December 16, 2016. This service MCAI and service information distribution of power and information describes procedures for referenced above. We are proposing this responsibilities among the various repetitive detailed inspections of all fuel AD because we evaluated all pertinent levels of government. pump locations (center, wing-inner, and information and determined an unsafe For the reasons discussed above, I wing-outer tank), and replacing any condition exists and is likely to exist or certify this proposed regulation: cracked hood halves of fuel pump develop on other products of these same 1. Is not a ‘‘significant regulatory canisters. type designs. action’’ under Executive Order 12866; VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\02AUP1.SGM 02AUP1

Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules 35913 2. Is not a ‘‘significant rule’’ under the are issuing this AD to prevent any detached (i) New Repetitive Inspections and DOT Regulatory Policies and Procedures canister hood fragments/debris from being Replacement of the Outer Tank and Trim (44 FR 11034, February 26, 1979); ingested into the fuel feed system, and Tank Fuel Pump Canister Hood Halves 3. Will not affect intrastate aviation in becoming a potential source of ignition with Within 30 months after the effective date Alaska; and consequent fire or explosion. of this AD, do a detailed inspection for 4. Will not have a significant cracking of the outer tank and trim tank, as (f) Compliance applicable, fuel pump canister hood halves economic impact, positive or negative, Comply with this AD within the installed on all fuel pump canisters having on a substantial number of small entities part numbers (P/N) 2052C11, 2052C12, and compliance times specified, unless already under the criteria of the Regulatory C93R51–601, in accordance with the done. Flexibility Act. Accomplishment Instructions of the service (g) Retained Initial Inspection and bulletin specified in paragraph (i)(1), (i)(2), or List of Subjects in 14 CFR Part 39 Replacement, With Revised Requirements (i)(3) of this AD, as applicable. Repeat the Air transportation, Aircraft, Aviation and Service Information inspection thereafter at intervals not to safety, Incorporation by reference, This paragraph restates the requirements of exceed 30 months. If any crack is found on Safety. any fuel pump canister hood half during any paragraph (g) of AD 2012–21–04, with inspection, before further flight, replace the The Proposed Amendment revised service information. Within 30 fuel pump canister hood half, in accordance months after November 27, 2012 (the with the Accomplishment Instructions of the Accordingly, under the authority effective date of AD 2012–21–04), do a service bulletin specified in paragraph (i)(1), delegated to me by the Administrator, detailed inspection for cracking of the fuel (i)(2), or (i)(3) of this AD, as applicable. the FAA proposes to amend 14 CFR part pump canister hood halves installed on all (1) For Model A300 series airplanes: 39 as follows: wing center and inner tank fuel pump Airbus Service Bulletin A300–28–0089, canisters having part numbers (P/N) Revision 03, dated December 16, 2016. PART 39—AIRWORTHINESS 2052C11, 2052C12, and C93R51–601, in (2) For Model A300–600 series airplanes: DIRECTIVES accordance with the Accomplishment Airbus Service Bulletin A300–28–6106, Instructions of the service bulletin specified Revision 03, dated December 16, 2016. ■ 1. The authority citation for part 39 in paragraph (g)(1), (g)(2), or (g)(3) of this AD, (3) For Model A310 series airplanes: continues to read as follows: Airbus Service Bulletin A310–28–2173, as applicable. If any crack is found on any Revision 03, dated December 16, 2016. Authority: 49 U.S.C. 106(g), 40113, 44701. fuel pump canister hood half during any inspection, before further flight, replace the (j) New Optional Terminating Actions § 39.13 [Amended] fuel pump canister hood half, in accordance Replacement of the fuel pump canister ■ 2. The FAA amends § 39.13 by with the Accomplishment Instructions of the hood halves installed on all fuel pump removing Airworthiness Directive (AD) service bulletin specified in paragraph (g)(1), canisters having P/Ns 2052C11, 2052C12, 2012–21–04, Amendment 39–17220 (77 (g)(2), or (g)(3) of this AD, as applicable. and C93R51–601, constitutes terminating FR 64701, October 23, 2012), and (1) For Model A300 series airplanes: action for the inspections required by adding the following new AD: Airbus Mandatory Service Bulletin A300–28– paragraphs (g) and (h) of this AD. The replacement of the fuel pump canister hood Airbus: Docket No. FAA–2017–0714; 0089, Revision 01, including Inspection halves must be done in accordance with the Directorate Identifier 2017–NM–042–AD. Findings—Reporting Sheet, dated April 15, Accomplishment Instructions of the service 2011; or Airbus Service Bulletin A300–28– information specified in paragraph (j)(1), (a) Comments Due Date 0089, Revision 03, dated December 16, 2016. (j)(2), or (j)(3) of this AD, as applicable. We must receive comments by September As of the effective date of this AD, only use (1) For Model A300 series airplanes: 18, 2017. Airbus Service Bulletin A300–28–0089, Airbus Service Bulletin A300–28–0092, Revision 03, dated December 16, 2016. Revision 01, dated August 29, 2014 (for wing (b) Affected ADs (2) For Model A300–600 series airplanes: center and inner tank fuel pump canister This AD replaces AD 2012–21–04, Airbus Mandatory Service Bulletin A300–28– hood halves); and Airbus Service Bulletin Amendment 39–17220 (77 FR 64701, October 6106, Revision 01, including Inspection A300–28–0094, Revision 00, dated January 9, 23, 2012) (‘‘AD 2012–21–04’’). 2017 (for outer tank fuel pump canister hood Findings—Reporting Sheet, dated April 15, halves). (c) Applicability 2011; or Airbus Service Bulletin A300–28– (2) For Model A300–600 series airplanes: This AD applies to the airplanes identified 6106, Revision 03, dated December 16, 2016. Airbus Service Bulletin A300–28–6110, in paragraphs (c)(1), (c)(2), and (c)(3) of this As of the effective date of this AD, only use Revision 01, dated August 29, 2014 (for wing AD, certificated in any category, all Airbus Service Bulletin A300–28–6106, center and inner tank fuel pump canister certificated models, all manufacturer serial Revision 03, dated December 16, 2016. hood halves); and Airbus Service Bulletin numbers. (3) For Model A310 series airplanes: A300–28–6114, Revision 00, dated January 9, (1) Airbus Model A300 B2–1A, B2–1C, Airbus Mandatory Service Bulletin A310–28– 2017 (for outer tank and trim tank fuel pump B2K–3C, B2–203, B4–2C, B4–103, and B4– 2173, Revision 01, including Inspection canister hood halves). 203 airplanes. Findings—Reporting Sheet, dated April 15, (3) For Model A310 series airplanes: (2) Airbus Model A310–203, –204, –221, 2011; or Airbus Service Bulletin A310–28– Airbus Service Bulletin A310–28–2175, –222, –304, –322, –324, and –325 airplanes. 2173, Revision 03, dated December 16, 2016. Revision 01, dated August 29, 2014 (for wing (3) Airbus Model A300 B4–601, B4–603, As of the effective date of this AD, only use center and inner tank fuel pump canister B4–620, and B4–622 airplanes, Model A300 Airbus Service Bulletin A310–28–2173, hood halves); and Airbus Service Bulletin B4–605R and B4–622R airplanes, Model Revision 03, dated December 16, 2016. A310–28–2178, Revision 00, January 9, 2017 A300 F4–605R and F4–622R airplanes, and (for outer tank and trim tank fuel pump Model A300 C4–605R Variant F airplanes. (h) Retained Repetitive Inspections, With No canister hood halves). jstallworth on DSKBBY8HB2PROD with PROPOSALS Changes (d) Subject (k) Credit for Previous Actions This paragraph restates the requirements of Air Transport Association (ATA) of (1) This paragraph provides credit for the paragraph (h) of AD 2012–21–04, with no actions required by paragraph (g) of this AD, America Code 28, Fuel. changes. Within 30 months after if those actions were performed before the (e) Reason accomplishing the actions specified in effective date of this AD using the service This AD was prompted by reports of paragraph (g) of this AD, and thereafter at information specified in paragraph (k)(1)(i), cracked fuel pump canister hoods located in intervals not to exceed 30 months, repeat the (k)(1)(ii), or (k)(1)(iii) of this AD. fuel tanks and new in-service events of outer detailed inspection specified in paragraph (g) (i) Airbus Service Bulletin A300–28–0089, tank fuel pump canister hood cracking. We of this AD. dated January 13, 2011; or Airbus Service VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\02AUP1.SGM 02AUP1

35914 Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules Bulletin A300–28–0089, Revision 02, dated the DOA, the approval must include the AD to correct the unsafe condition on April 25, 2014. DOA-authorized signature. these products. (ii) Airbus Service Bulletin A300–28–6106, (m) Related Information DATES: We must receive comments on dated January 13, 2011; or Airbus Service Bulletin A300–28–6106, Revision 02, dated (1) Refer to Mandatory Continuing this proposed AD by September 18, April 25, 2014. Airworthiness Information (MCAI) EASA AD 2017. (iii) Airbus Service Bulletin A310–28– 2017–0051, dated March 23, 2017, for related ADDRESSES: You may send comments, 2173, dated January 13, 2011; or Airbus information. This MCAI may be found in the using the procedures found in 14 CFR Mandatory Service Bulletin A310–28–2173, AD docket on the Internet at http:// 11.43 and 11.45, by any of the following Revision 02, dated April 25, 2014. www.regulations.gov by searching for and (2) This paragraph provides credit for the locating Docket No. FAA–2017–0714. methods: actions required by paragraph (h) of this AD, (2) For more information about this AD, • Federal eRulemaking Portal: Go to if those actions were performed before the contact Dan Rodina, Aerospace Engineer, http://www.regulations.gov. Follow the effective date of this AD using the service International Branch, ANM–116, Transport instructions for submitting comments. information specified in paragraph (k)(2)(i), Airplane Directorate, FAA, 1601 Lind • Fax: 202–493–2251. (k)(2)(ii), or (k)(2)(iii) of this AD. Avenue SW., Renton, WA 98057–3356; • Mail: U.S. Department of (i) Airbus Service Bulletin A300–28–0089, telephone: 425–227–2125; fax: 425–227– Transportation, Docket Operations, M– dated January 13, 2011; Airbus Service 1149. 30, West Building Ground Floor, Room Bulletin A300–28–0089, Revision 01, dated (3) For service information identified in W12–140, 1200 New Jersey Avenue SE., April 15, 2011; or Airbus Service Bulletin this AD, contact Airbus SAS, Airworthiness Washington, DC 20590. A300–28–0089, Revision 02, dated April 25, Office—EAW, 1 Rond Point Maurice • Hand Delivery: Deliver to Mail 2014. Bellonte, 31707 Blagnac Cedex, France; (ii) Airbus Service Bulletin A300–28–6106, telephone: +33 5 61 93 36 96; fax: +33 5 61 address above between 9 a.m. and 5 dated January 13, 2011; Airbus Service 93 44 51; email: account.airworth-eas@ p.m., Monday through Friday, except Bulletin A300–28–6106, Revision 01, dated airbus.com; Internet: http://www.airbus.com. Federal holidays. April 15, 2011; or Airbus Service Bulletin You may view this service information at the For service information identified in A300–28–6106, Revision 02, dated April 25, FAA, Transport Airplane Directorate, 1601 this NPRM, contact Honeywell 2014. Lind Avenue SW., Renton, WA. For International Inc., 111 S. 34th Street, (iii) Airbus Service Bulletin A310–28– information on the availability of this Phoenix, AZ 85034–2802; phone: 800– 2173, dated January 13, 2011; Airbus Service material at the FAA, call 425–227–1221. 601–3099; Internet: https:// Bulletin A310–28–2173, Revision 01, dated myaerospace.honeywell.com/wps/ Issued in Renton, Washington, on July 19, April 15, 2011; or Airbus Service Bulletin portal/!ut/. You may view this service 2017. A310–28–2173, Revision 02, dated April 25, 2014. Michael Kaszycki, information at the FAA, Engine & (3) This paragraph provides credit for the Acting Manager, Transport Airplane Propeller Directorate, 1200 District actions specified in paragraph (j) of this AD, Directorate, Aircraft Certification Service. Avenue, Burlington, MA 01803. For if those actions were performed before the [FR Doc. 2017–16052 Filed 8–1–17; 8:45 am] information on the availability of this effective date of this AD using Airbus Service BILLING CODE 4910–13–P material at the FAA, call (781) 238– Bulletin A300–28–6110, Revision 00, dated 7125. November 28, 2013. Examining the AD Docket (l) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION You may examine the AD docket on (1) Alternative Methods of Compliance Federal Aviation Administration the Internet at http:// (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane www.regulations.gov by searching for Directorate, FAA, has the authority to 14 CFR Part 39 and locating Docket No. FAA–2017– approve AMOCs for this AD, if requested 0020; or in person at the Docket [Docket No. FAA–2017–0020; Directorate using the procedures found in 14 CFR 39.19. Management Facility between 9 a.m. Identifier 2016–NE–33–AD] In accordance with 14 CFR 39.19, send your and 5 p.m., Monday through Friday, request to your principal inspector or local RIN 2120–AA64 except Federal holidays. The AD docket Flight Standards District Office, as contains this proposed AD, the appropriate. If sending information directly Airworthiness Directives; Honeywell regulatory evaluation, any comments to the International Branch, send it to the International Inc. Turbofan Engines received, and other information. The attention of the person identified in paragraph (m)(2) of this AD. Information may AGENCY: Federal Aviation street address for the Docket Office be emailed to: 9-ANM-116-AMOC- Administration (FAA), DOT. (phone: 800–647–5527) is in the REQUESTS@faa.gov. ADDRESSES section. Comments will be ACTION: Notice of proposed rulemaking (i) Before using any approved AMOC, available in the AD docket shortly after notify your appropriate principal inspector, (NPRM). receipt. or lacking a principal inspector, the manager FOR FURTHER INFORMATION CONTACT: SUMMARY: We propose to adopt a new of the local flight standards district office/ Joseph Costa, Aerospace Engineer, Los certificate holding district office. airworthiness directive (AD) for certain Honeywell International Inc. AS907 Angeles Aircraft Certification Office, (ii) AMOCs approved previously for AD 2012–21–04, Amendment 39–17220 (77 FR series turbofan engines. This proposed FAA, Transport Airplane Directorate, 64701, October 23, 2012), are not approved AD was prompted by two loss-of-thrust- 3960 Paramount Blvd., Lakewood, CA as AMOCs with this AD. control events, and two in-flight 90712–4137; phone: 562–627–5246; fax: (2) Contacting the Manufacturer: As of the shutdowns (IFSDs) of new production, 562–627–5210; email: joseph.costa@ jstallworth on DSKBBY8HB2PROD with PROPOSALS effective date of this AD, for any requirement low-time engines attributed to water faa.gov. in this AD to obtain corrective actions from intrusion of the engine electronic SUPPLEMENTARY INFORMATION: a manufacturer, the action must be control unit (ECU). This proposed AD accomplished using a method approved by Comments Invited the Manager, International Branch, ANM– would require applying sealant to 116, Transport Airplane Directorate, FAA; or identified areas of the ECU and requires We invite you to send any written the European Aviation Safety Agency inserting a copy of certain airplane relevant data, views, or arguments about (EASA); or Airbus’s EASA Design operating procedures into the applicable this NPRM. Send your comments to an Organization Approval (DOA). If approved by flight manuals. We are proposing this address listed under the ADDRESSES VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\02AUP1.SGM 02AUP1


Document Created: 2017-08-02 07:09:32
Document Modified: 2017-08-02 07:09:32
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by September 18, 2017.
ContactDan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149.
FR Citation82 FR 35911 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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