Airworthiness Directives; Airbus Airplanes, 32503-32507 [2017-14590]
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Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules
specified compliance time unless it has
already been accomplished prior to that time.
(e) Compliance
You are responsible for performing each
action required by this AD within the
(1) Before further flight, amend the EC120B
Rotorcraft Flight Manual Supplement (RFMS)
for the emergency flotation gear Aerazur, by
(2) Before each flight over water:
(i) Perform a functional check to determine
whether flight over water is permitted under
the Limitations section in paragraph (f)(1) of
this AD. For purposes of this AD, ‘‘flight over
water’’ means flight beyond the power-off
gliding distance from shore. ‘‘Shore’’ is an
area of land adjacent to the water and above
the high water mark but does not include
land area that is intermittently under water.
The actions required by this paragraph may
be performed by the owner/operator (pilot)
holding at least a private pilot certificate, and
must be entered into the aircraft records
showing compliance with this AD in
accordance with 14 CFR 43.9 (a)(1) through
(4) and 14 CFR 91.417(a)(2)(v). The record
must be maintained as required by 14 CFR
91.417, 121.380, or 135.439.
(ii) If the LACU fails the functional check
required by paragraph (f)(2)(i) of this AD,
place a placard over the ‘‘float arm’’
pushbutton that reads ‘‘INOP.’’
(3) Within 300 hours time-in-service,
replace float arm pushbutton P/N
045004A111A with float arm pushbutton
P/N 304–2500–00. Installing float arm
pushbutton
P/N 304–2500–00 is terminating action for
the functional check and placard required by
paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(4) Do not install float arm pushbutton
P/N 045004A111A on any helicopter.
operating any aircraft complying with this
AD through an AMOC.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: George Schwab,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
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(f) Required Actions
(1) Airbus Helicopters Emergency Alert
Service Bulletin No. 04A007, Revision 1,
dated June 30, 2016, and Airbus Helicopters
Alert Service Bulletin No. EC120–31A008,
dated June 30, 2016, which are not
incorporated by reference, contain additional
information about the subject of this AD. For
service information identified in this AD,
contact Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://
www.airbushelicopters.com/website/
technical-expert/. You may review a copy of
the service information at the FAA, Office of
the Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2016–0180, dated September 13, 2016.
You may view the EASA AD on the Internet
at https://www.regulations.gov in the AD
Docket.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 2560 Emergency Equipment.
Issued in Fort Worth, Texas, on June 28,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2017–14373 Filed 7–13–17; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(h) Additional Information
BILLING CODE 4910–13–P
inserting a copy of this AD into the
Limitations section of the RFMS or by
making pen and ink changes to that section
to add the information in figure 1 to
paragraph (f)(1) of this AD:
14 CFR Part 39
[Docket No. FAA–2017–0695; Directorate
Identifier 2016–NM–173–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2009–18–
16, for certain Airbus Model A310–203,
–204, –221, –222, –304, –322, –324, and
–325 airplanes. AD 2009–18–16 requires
an inspection for cracking of certain
fastener holes on certain frames, and
related investigative and corrective
actions if necessary; and modification of
certain fastener holes. Since we issued
AD 2009–18–16, an evaluation by the
design approval holder (DAH) indicated
that the compliance times should be
reduced. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 28, 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
DATES:
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(d) Comments Due Date
We must receive comments by September
12, 2017.
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Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules
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: https://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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0695; 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:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0695; Directorate Identifier 2016–
NM–173–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 https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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substantive verbal contact we receive
about this proposed AD.
Discussion
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage. It is associated with
general degradation of large areas of
structure with similar structural details
and stress levels. As an airplane ages,
widespread fatigue damage (WFD) will
likely occur, and will certainly occur if
the airplane is operated long enough
without any intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
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development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
On August 24, 2009, we issued AD
2009–18–16, Amendment 39–16012 (74
FR 46342, September 9, 2009) (‘‘AD
2009–18–16’’), for certain Airbus Model
A310–203, –204, –221, –222, –304,
–322, –324, and –325 airplanes. AD
2009–18–16 was prompted by an
identification of a structural
modification that falls within the scope
of the work related to the extension of
the service life of the affected airplanes
and widespread fatigue damage
evaluations. AD 2009–18–16 requires
inspecting by rotating probe for cracking
of fastener holes H1 through H29 on
frames (FRs) 43 through 46 inclusive,
and inspecting fastener holes H1
through H29 on FRs 43 through 46
inclusive, to determine the edge
distance of the fastener hole, and
corrective actions if necessary. We
issued AD 2009–18–16 to prevent
fatigue cracking of the frame foot runouts, which could lead to rupture of the
frame foot and cracking in adjacent
frames and skin, and which could result
in reduced structural integrity of the
fuselage.
Since we issued AD 2009–18–16, the
manufacturer has conducted a new
investigation as part of the WFD
program and determined that the
compliance times 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 AD 2016–0197,
dated October 5, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), for all Airbus Model A310–
203, –204, –221, –222, –304, –322, –324,
and –325 airplanes. EASA AD 2016–
0197 supersedes EASA AD 2008–0212,
dated December 4, 2008. EASA AD
2008–0212 was the MCAI referred to in
FAA AD 2009–18–16. The new MCAI
states:
Within the scope of work related to the
extension of the service life of A310 design
and widespread fatigue damage evaluations,
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD F–2005–078 (EASA
approval 2005–3957) [which corresponds to
FAA AD 2006–02–06, Amendment 39–14458
(71 FR 3214, January 20, 2006)] to require a
structural modification, as defined in Airbus
Service Bulletin (SB) A310–53–2124 (Airbus
modification 13023), to increase the service
life of junctions of center box upper frame
bases to upper fuselage arches.
The threshold timescales for
accomplishment of the tasks as defined in SB
A310–53–2124 were refined and reduced.
Consequently, EASA issued AD 2007–0238
to require compliance with Revision 01 of SB
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A310–53–2124 at the reduced compliance
times, superseding (the requirements of)
DGAC France AD F–2005–078. Subsequently,
Airbus identified reference material that was
erroneously introduced into Airbus SB
A310–53–2124 Revision 01. As a result, the
SB instructions could not be accomplished
properly. Operators that tried to apply SB
A310–53–2124 at Revision 01 had to contact
Airbus; see also Airbus SBIT [service bulletin
information telex] ref. 914.0135/08, dated 03
March 2008.
Consequently, [EASA] AD 2007–0238 was
revised to exclude reference to Airbus SB
A310–53–2124 Revision 01 and to require
accomplishment of the task(s) as described in
the original SB A310–53–2124 instead,
although retaining the reduced compliance
times introduced by [EASA] AD 2007–0238
at original issue.
EASA AD 2008–0212, superseding [EASA]
AD 2007–0238R1, was published to refer to
Airbus SB A310 53–2124 Revision 02, the
corrected version that was used to meet the
requirements of this [EASA] AD.
Since [EASA] AD 2008–0212 was issued,
new investigations in the frame of the
Widespread Fatigue Damage campaign
induced thresholds reduction, and Airbus
issued SB A310–53–2124 Revision 03.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2008–0212, which is superseded, and
requires accomplishment of modification(s)
within reduced compliance time, as
published in Airbus SB A310–53–2124
Revision 03.
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Required actions include a high
frequency eddy current (HFEC) rotating
probe inspection for cracking of certain
fastener holes on certain frames, and
related investigative and corrective
actions if necessary; and modification of
certain fastener holes. Related
investigative actions include an
additional HFEC rotating probe
inspection for cracking of fastener holes
and a check to determine the edge
distance of certain holes. Corrective
actions include ream out of cracks and
repair. You may examine the MCAI in
the AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0695.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A310–53–2124, Revision 03,
dated December 22, 2014. The service
information describes procedures for a
rototest inspection for cracking between
FR 43 through FR 46 on the center box,
and the cold expansion (modification)
of the most fatigue sensitive fastener
holes. 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.
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FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Differences Between This NPRM and
the MCAI
There is a difference between this
NPRM and the MCAI regarding how the
compliance times are stated for the
accomplishment of the inspection and
modification specified in paragraph (j)
of this proposed AD. The MCAI states
that the accomplishment of the
inspection and modification specified in
Airbus Service Bulletin A310–53–2124
should be accomplished no later than 6
months (estimated by projection of
airplane usage) prior to the thresholds
specified in the MCAI. Paragraph (j) of
this proposed AD specifies that the
accomplishment of the inspection and
modification should be done ‘‘at the
applicable thresholds specified in table
3 to the introductory text of paragraph
(j) of this AD.’’ The compliance times
specified in table 3 to the introductory
text of paragraph (j) of this proposed AD
are based upon the average annual
utilization of the Airbus airplanes
identified in paragraph (c) of this
proposed AD. Based on this
information, we calculated that within 6
months an Airbus Model A310 series
airplane would have accumulated an
average of 300 flight cycles and 978
flight hours.
Costs of Compliance
We estimate that this proposed AD
affects 8 airplanes of U.S. registry.
We estimate that it would take about
41 work-hours per product to comply
with the basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Required parts
would cost about $20,180 per product.
Based on these figures, we estimate the
cost of this proposed AD on U.S.
operators to be $189,320, or $23,665 per
product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
(i.e., additional inspection and
modification for certain airplanes)
specified in this proposed AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2009–18–16, Amendment 39–16012 (74
FR 46342, September 9, 2009), and
adding the following new AD:
■
Airbus: Docket No. FAA–2017–0695;
Directorate Identifier 2016–NM–173–AD.
(a) Comments Due Date
We must receive comments by August 28,
2017.
(b) Affected ADs
(e) Reason
This AD was prompted by an evaluation by
the design approval holder indicating that
the junctions of center box upper frame bases
to the upper fuselage arches are subject to
widespread fatigue damage and that the
compliance threshold for the modification in
AD 2009–18–16 should be reduced. We are
issuing this AD to prevent fatigue cracking of
the frame foot run-outs, which could lead to
rupture of the frame foot and cracking in
adjacent frames and skin, and which could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
This AD replaces AD 2009–18–16,
Amendment 39–16012 (74 FR 46342,
September 9, 2009) (‘‘AD 2009–18–16’’).
(c) Applicability
This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324 and
–325 airplanes; certificated in any category;
all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(g) Inspections and Modification of Fastener
Holes
Except for airplanes modified before the
effective date of this AD using the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124: At the times
specified in paragraph (g)(1) of this AD but
no later than the times specified in paragraph
(g)(2) of this AD, do a high frequency eddy
current (HFEC) rotating probe inspection for
cracking of fastener holes H1 through H29 on
frames 43 through 46, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
53–2124, Revision 03, dated December 22,
2014, except as required by paragraph (h) of
this AD. If no cracking is found and the edge
distance of the fastener hole is equal to or
greater than the distance specified in the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124, Revision 03,
dated December 22, 2014, before further
flight, do the modification (cold expansion)
of the affected fastener holes, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–53–2124,
Revision 03, dated December 22, 2014. Do all
applicable related investigative and
corrective actions before further flight.
(1) Inspect at the applicable time specified
in table 1 to paragraph (g)(1) of this AD, or
within 24 months after the effective date of
this AD, whichever occurs later. To establish
the average flight time (AFT), take the
accumulated flight time (counted from the
take-off up to the landing) and divide by the
number of accumulated flight cycles. This
gives the AFT per flight cycle.
TABLE 1 TO PARAGRAPH (G)(1) OF THIS AD—NEW COMPLIANCE TIMES
Affected airplanes
Compliance time
Model A310–203, –204, –221, and –222 airplanes .................................
Model A310–304, –322, –324, and –325 airplanes with an AFT of less
than or equal to 3.16 flight hours.
Model A310–304, –322, –324, and –325 airplanes with an AFT greater
than 3.16 flight hours.
(2) Inspect at the later of the times
specified in paragraphs (g)(2)(i) and (g)(2)(ii)
of this AD.
(i) At the applicable time indicated in table
2 to paragraph (g)(2)(i) of this AD. Airbus
Model A310–304, –322, –324, and –325
Prior to accumulation of 19,600 flight cycles or
since first flight of the airplane, whichever occurs
Prior to accumulation of 22,400 flight cycles or
since first flight of the airplane, whichever occurs
Prior to accumulation of 19,800 flight cycles or
since first flight of the airplane, whichever occurs
airplanes with an AFT equal to or less than
3.17 flight hours are short range airplanes.
Airbus Model A310–304, –322, –324, and
–325 airplanes with an AFT exceeding 3.17
flight hours are long range airplanes. For this
paragraph, to establish the average flight
39,200 flight hours
first.
62,700 flight hours
first.
99,200 flight hours
first.
time, take the accumulated flight time
(counted from the take-off up to the landing)
and divide by the number of accumulated
flight cycles. This provides the AFT per flight
cycle.
TABLE 2 TO PARAGRAPH (G)(2)(I) OF THIS AD—RETAINED COMPLIANCE TIMES
Affected airplanes
Inspection/modification compliance time, whichever occurs later
Model A310–304, –322, –324 and –325 short range airplanes ..............
Prior to accumulation of 26,500 flight cycles or 74,300 flight hours
since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after October 14, 2009 (the effective date of
AD 2009–18–16), without exceeding 29,200 flight cycles or 81,800
flight hours since first flight, whichever occurs first
Prior to accumulation of 23,400 flight cycles or 117,100 flight hours
since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after October 14, 2009 (the effective date of
AD 2009–18–16), without exceeding 25,800 flight cycles or 129,000
flight hours since first flight, whichever occurs first
Prior to accumulation of 23,400 flight cycles or 46,800 flight hours
since first flight of the airplane, whichever occurs first
Within 3,000 flight cycles after October 14, 2009 (the effective date of
AD 2009–18–16), without exceeding 28,800 flight cycles or 57,700
flight hours since first flight, whichever occurs first
Model A310–304, –322, –324 and –325 long range airplanes ...............
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Model A310–203, –204, –221, and A310–222 ........................................
(ii) Within 500 flight cycles or 800 flight
hours after October 14, 2009 (the effective
date of AD 2009–18–16), whichever occurs
first.
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(h) Service Information Exception
Where Airbus Service Bulletin A310–53–
2124, Revision 03, dated December 22, 2014,
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specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
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accordance with the procedures specified in
paragraph (l)(2) of this AD.
(i) Airplanes Modified per Revision 01 of the
Service Information
For airplanes modified before the effective
date of this AD using Airbus Service Bulletin
A310–53–2124, Revision 01, dated May 3,
2007: Unless already accomplished, before
further flight, do applicable corrective
actions using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
(j) Additional Inspection and Modification
Except as provided by paragraphs (j)(1) and
(j)(2) of this AD, as applicable: At the
applicable thresholds specified in table 3 to
the introductory text of paragraph (j) of this
32507
AD, contact the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA for additional inspection and
modification instructions. Accomplish those
instructions within the compliance times
provided by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
TABLE 3 TO THE INTRODUCTORY TEXT OF PARAGRAPH (J) OF THIS AD—ADDITIONAL INSPECTION AND MODIFICATION
Thresholds
(Flight cycles or flight hours, whichever occurs first after accomplishment of the inspection and
modification specified in Airbus Service Bulletin A310–53–2124)
Affected airplanes
Inspection threshold
Modification threshold
Model A310–203, –204, –221, and –222 airplanes.
Model A310–304, –322, –324, and –325 airplanes.
30,200 flight cycles or 68,122 flight hours .......
45,500 flight cycles or 102,722 flight hours
37,000 flight cycles or 103,522 flight hours .....
55,700 flight cycles or 155,722 flight hours
(1) For Model A310–203, –204, –221, and
–222 airplanes: No additional inspection is
required if the inspection and modification
specified in Airbus Service Bulletin A310–
53–2124 was done after the accumulation of
29,500 flight cycles and 70,900 flight hours
since the first flight of the airplane.
(2) For Model A310–304, –322, –324, and
–325 airplanes: No additional inspection is
required if the inspection and modification
specified in Airbus Service Bulletin A310–
53–2124 was done after the accumulation of
22,600 flight cycles and 69,400 flight hours
since the first flight of the airplane.
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as provided by paragraph (h) 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.
information on the availability of this
material at the FAA, call 425–227–1221.
mstockstill on DSK30JT082PROD with PROPOSALS
(k) Credit for Previous Actions
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
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124, dated April
4, 2005; or Airbus Service Bulletin A310–53–
2124, Revision 02, dated May 22, 2008.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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-AMOCREQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
VerDate Sep<11>2014
17:18 Jul 13, 2017
Jkt 241001
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0197, dated October 5, 2016, for related
information. This MCAI may be found in the
AD docket on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0695.
(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: https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
Issued in Renton, Washington, on June 29,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14590 Filed 7–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0630; Directorate
Identifier 2017–NM–058–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–200,
–200LR, –300, and –300ER series
airplanes. This proposed AD was
prompted by reports of corrosion in the
aft fuselage. This proposed AD would
require a one-time review of the
operator’s maintenance procedures,
repetitive detailed internal and external
inspections for corrosion or cracking,
and applicable on-condition actions.
This proposed AD would also include
an optional terminating action for the
inspections. We are proposing this AD
to address the unsafe condition on these
products.
SUMMARY:
E:\FR\FM\14JYP1.SGM
14JYP1
Agencies
[Federal Register Volume 82, Number 134 (Friday, July 14, 2017)]
[Proposed Rules]
[Pages 32503-32507]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14590]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0695; Directorate Identifier 2016-NM-173-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) 2009-18-
16, for certain Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes. AD 2009-18-16 requires an inspection for
cracking of certain fastener holes on certain frames, and related
investigative and corrective actions if necessary; and modification of
certain fastener holes. Since we issued AD 2009-18-16, an evaluation by
the design approval holder (DAH) indicated that the compliance times
should be reduced. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by August 28, 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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-
[[Page 32504]]
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: https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0695; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0695;
Directorate Identifier 2016-NM-173-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 https://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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as widespread fatigue damage. It is
associated with general degradation of large areas of structure with
similar structural details and stress levels. As an airplane ages,
widespread fatigue damage (WFD) will likely occur, and will certainly
occur if the airplane is operated long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
On August 24, 2009, we issued AD 2009-18-16, Amendment 39-16012 (74
FR 46342, September 9, 2009) (``AD 2009-18-16''), for certain Airbus
Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
AD 2009-18-16 was prompted by an identification of a structural
modification that falls within the scope of the work related to the
extension of the service life of the affected airplanes and widespread
fatigue damage evaluations. AD 2009-18-16 requires inspecting by
rotating probe for cracking of fastener holes H1 through H29 on frames
(FRs) 43 through 46 inclusive, and inspecting fastener holes H1 through
H29 on FRs 43 through 46 inclusive, to determine the edge distance of
the fastener hole, and corrective actions if necessary. We issued AD
2009-18-16 to prevent fatigue cracking of the frame foot run-outs,
which could lead to rupture of the frame foot and cracking in adjacent
frames and skin, and which could result in reduced structural integrity
of the fuselage.
Since we issued AD 2009-18-16, the manufacturer has conducted a new
investigation as part of the WFD program and determined that the
compliance times 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 AD 2016-0197, dated October 5, 2016
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), for all Airbus Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes. EASA AD 2016-0197
supersedes EASA AD 2008-0212, dated December 4, 2008. EASA AD 2008-0212
was the MCAI referred to in FAA AD 2009-18-16. The new MCAI states:
Within the scope of work related to the extension of the service
life of A310 design and widespread fatigue damage evaluations, DGAC
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France
issued AD F-2005-078 (EASA approval 2005-3957) [which corresponds to
FAA AD 2006-02-06, Amendment 39-14458 (71 FR 3214, January 20,
2006)] to require a structural modification, as defined in Airbus
Service Bulletin (SB) A310-53-2124 (Airbus modification 13023), to
increase the service life of junctions of center box upper frame
bases to upper fuselage arches.
The threshold timescales for accomplishment of the tasks as
defined in SB A310-53-2124 were refined and reduced. Consequently,
EASA issued AD 2007-0238 to require compliance with Revision 01 of
SB
[[Page 32505]]
A310-53-2124 at the reduced compliance times, superseding (the
requirements of) DGAC France AD F-2005-078. Subsequently, Airbus
identified reference material that was erroneously introduced into
Airbus SB A310-53-2124 Revision 01. As a result, the SB instructions
could not be accomplished properly. Operators that tried to apply SB
A310-53-2124 at Revision 01 had to contact Airbus; see also Airbus
SBIT [service bulletin information telex] ref. 914.0135/08, dated 03
March 2008.
Consequently, [EASA] AD 2007-0238 was revised to exclude
reference to Airbus SB A310-53-2124 Revision 01 and to require
accomplishment of the task(s) as described in the original SB A310-
53-2124 instead, although retaining the reduced compliance times
introduced by [EASA] AD 2007-0238 at original issue.
EASA AD 2008-0212, superseding [EASA] AD 2007-0238R1, was
published to refer to Airbus SB A310 53-2124 Revision 02, the
corrected version that was used to meet the requirements of this
[EASA] AD.
Since [EASA] AD 2008-0212 was issued, new investigations in the
frame of the Widespread Fatigue Damage campaign induced thresholds
reduction, and Airbus issued SB A310-53-2124 Revision 03.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2008-0212, which is superseded, and requires
accomplishment of modification(s) within reduced compliance time, as
published in Airbus SB A310-53-2124 Revision 03.
Required actions include a high frequency eddy current (HFEC)
rotating probe inspection for cracking of certain fastener holes on
certain frames, and related investigative and corrective actions if
necessary; and modification of certain fastener holes. Related
investigative actions include an additional HFEC rotating probe
inspection for cracking of fastener holes and a check to determine the
edge distance of certain holes. Corrective actions include ream out of
cracks and repair. You may examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2017-0695.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A310-53-2124, Revision
03, dated December 22, 2014. The service information describes
procedures for a rototest inspection for cracking between FR 43 through
FR 46 on the center box, and the cold expansion (modification) of the
most fatigue sensitive fastener holes. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Differences Between This NPRM and the MCAI
There is a difference between this NPRM and the MCAI regarding how
the compliance times are stated for the accomplishment of the
inspection and modification specified in paragraph (j) of this proposed
AD. The MCAI states that the accomplishment of the inspection and
modification specified in Airbus Service Bulletin A310-53-2124 should
be accomplished no later than 6 months (estimated by projection of
airplane usage) prior to the thresholds specified in the MCAI.
Paragraph (j) of this proposed AD specifies that the accomplishment of
the inspection and modification should be done ``at the applicable
thresholds specified in table 3 to the introductory text of paragraph
(j) of this AD.'' The compliance times specified in table 3 to the
introductory text of paragraph (j) of this proposed AD are based upon
the average annual utilization of the Airbus airplanes identified in
paragraph (c) of this proposed AD. Based on this information, we
calculated that within 6 months an Airbus Model A310 series airplane
would have accumulated an average of 300 flight cycles and 978 flight
hours.
Costs of Compliance
We estimate that this proposed AD affects 8 airplanes of U.S.
registry.
We estimate that it would take about 41 work-hours per product to
comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about
$20,180 per product. Based on these figures, we estimate the cost of
this proposed AD on U.S. operators to be $189,320, or $23,665 per
product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions (i.e., additional
inspection and modification for certain airplanes) specified in this
proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 32506]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009), and
adding the following new AD:
Airbus: Docket No. FAA-2017-0695; Directorate Identifier 2016-NM-
173-AD.
(a) Comments Due Date
We must receive comments by August 28, 2017.
(b) Affected ADs
This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342,
September 9, 2009) (``AD 2009-18-16'').
(c) Applicability
This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324 and -325 airplanes; certificated in any category;
all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder indicating that the junctions of center box upper frame bases
to the upper fuselage arches are subject to widespread fatigue
damage and that the compliance threshold for the modification in AD
2009-18-16 should be reduced. We are issuing this AD to prevent
fatigue cracking of the frame foot run-outs, which could lead to
rupture of the frame foot and cracking in adjacent frames and skin,
and 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) Inspections and Modification of Fastener Holes
Except for airplanes modified before the effective date of this
AD using the Accomplishment Instructions of Airbus Service Bulletin
A310-53-2124: At the times specified in paragraph (g)(1) of this AD
but no later than the times specified in paragraph (g)(2) of this
AD, do a high frequency eddy current (HFEC) rotating probe
inspection for cracking of fastener holes H1 through H29 on frames
43 through 46, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310-53-2124, Revision 03,
dated December 22, 2014, except as required by paragraph (h) of this
AD. If no cracking is found and the edge distance of the fastener
hole is equal to or greater than the distance specified in the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2124,
Revision 03, dated December 22, 2014, before further flight, do the
modification (cold expansion) of the affected fastener holes, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all
applicable related investigative and corrective actions before
further flight.
(1) Inspect at the applicable time specified in table 1 to
paragraph (g)(1) of this AD, or within 24 months after the effective
date of this AD, whichever occurs later. To establish the average
flight time (AFT), take the accumulated flight time (counted from
the take-off up to the landing) and divide by the number of
accumulated flight cycles. This gives the AFT per flight cycle.
Table 1 to Paragraph (g)(1) of This AD--New Compliance Times
------------------------------------------------------------------------
Affected airplanes Compliance time
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222 Prior to accumulation of 19,600
airplanes. flight cycles or 39,200 flight
hours since first flight of
the airplane, whichever occurs
first.
Model A310-304, -322, -324, and -325 Prior to accumulation of 22,400
airplanes with an AFT of less than or flight cycles or 62,700 flight
equal to 3.16 flight hours. hours since first flight of
the airplane, whichever occurs
first.
Model A310-304, -322, -324, and -325 Prior to accumulation of 19,800
airplanes with an AFT greater than flight cycles or 99,200 flight
3.16 flight hours. hours since first flight of
the airplane, whichever occurs
first.
------------------------------------------------------------------------
(2) Inspect at the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) At the applicable time indicated in table 2 to paragraph
(g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325
airplanes with an AFT equal to or less than 3.17 flight hours are
short range airplanes. Airbus Model A310-304, -322, -324, and -325
airplanes with an AFT exceeding 3.17 flight hours are long range
airplanes. For this paragraph, to establish the average flight time,
take the accumulated flight time (counted from the take-off up to
the landing) and divide by the number of accumulated flight cycles.
This provides the AFT per flight cycle.
Table 2 to Paragraph (g)(2)(i) of This AD--Retained Compliance Times
------------------------------------------------------------------------
Inspection/modification
Affected airplanes compliance time, whichever
occurs later
------------------------------------------------------------------------
Model A310-304, -322, -324 and -325 Prior to accumulation of 26,500
short range airplanes. flight cycles or 74,300 flight
hours since first flight of
the airplane, whichever occurs
first
Within 3,000 flight cycles
after October 14, 2009 (the
effective date of AD 2009-18-
16), without exceeding 29,200
flight cycles or 81,800 flight
hours since first flight,
whichever occurs first
Model A310-304, -322, -324 and -325 Prior to accumulation of 23,400
long range airplanes. flight cycles or 117,100
flight hours since first
flight of the airplane,
whichever occurs first
Within 3,000 flight cycles
after October 14, 2009 (the
effective date of AD 2009-18-
16), without exceeding 25,800
flight cycles or 129,000
flight hours since first
flight, whichever occurs first
Model A310-203, -204, -221, and A310- Prior to accumulation of 23,400
222. flight cycles or 46,800 flight
hours since first flight of
the airplane, whichever occurs
first
Within 3,000 flight cycles
after October 14, 2009 (the
effective date of AD 2009-18-
16), without exceeding 28,800
flight cycles or 57,700 flight
hours since first flight,
whichever occurs first
------------------------------------------------------------------------
(ii) Within 500 flight cycles or 800 flight hours after October
14, 2009 (the effective date of AD 2009-18-16), whichever occurs
first.
(h) Service Information Exception
Where Airbus Service Bulletin A310-53-2124, Revision 03, dated
December 22, 2014, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
[[Page 32507]]
accordance with the procedures specified in paragraph (l)(2) of this
AD.
(i) Airplanes Modified per Revision 01 of the Service Information
For airplanes modified before the effective date of this AD
using Airbus Service Bulletin A310-53-2124, Revision 01, dated May
3, 2007: Unless already accomplished, before further flight, do
applicable corrective actions using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
(j) Additional Inspection and Modification
Except as provided by paragraphs (j)(1) and (j)(2) of this AD,
as applicable: At the applicable thresholds specified in table 3 to
the introductory text of paragraph (j) of this AD, contact the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA for additional
inspection and modification instructions. Accomplish those
instructions within the compliance times provided by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
Table 3 to the Introductory Text of Paragraph (j) of This AD--Additional
Inspection and Modification
------------------------------------------------------------------------
Thresholds (Flight cycles or flight
hours, whichever occurs first after
accomplishment of the inspection and
modification specified in Airbus
Affected airplanes Service Bulletin A310-53-2124)
---------------------------------------
Inspection Modification
threshold threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and - 30,200 flight 45,500 flight
222 airplanes. cycles or 68,122 cycles or 102,722
flight hours. flight hours
Model A310-304, -322, -324, and - 37,000 flight 55,700 flight
325 airplanes. cycles or 103,522 cycles or 155,722
flight hours. flight hours
------------------------------------------------------------------------
(1) For Model A310-203, -204, -221, and -222 airplanes: No
additional inspection is required if the inspection and modification
specified in Airbus Service Bulletin A310-53-2124 was done after the
accumulation of 29,500 flight cycles and 70,900 flight hours since
the first flight of the airplane.
(2) For Model A310-304, -322, -324, and -325 airplanes: No
additional inspection is required if the inspection and modification
specified in Airbus Service Bulletin A310-53-2124 was done after the
accumulation of 22,600 flight cycles and 69,400 flight hours since
the first flight of the airplane.
(k) Credit for Previous Actions
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 Accomplishment Instructions of
Airbus Service Bulletin A310-53-2124, dated April 4, 2005; or Airbus
Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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. 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.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(3) Required for Compliance (RC): Except as provided by
paragraph (h) 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0197, dated October 5, 2016, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0695.
(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: https://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 June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14590 Filed 7-13-17; 8:45 am]
BILLING CODE 4910-13-P