Airworthiness Directives; Airbus Airplanes, 29440-29445 [2017-13406]
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29440
Proposed Rules
Federal Register
Vol. 82, No. 124
Thursday, June 29, 2017
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0624; Directorate
Identifier 2016–NM–135–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A319 series airplanes,
Model A320–211, –212, –214, –231,
–232, and –233 airplanes, and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. This
proposed AD was prompted by a
runway excursion due to an unexpected
thrust increase leading to an unstable
approach performed using the current
flight management and guidance
computer (FMGC) standard. This
proposed AD would require
identification of potentially affected
FMGCs, replacement of any affected
FMGC, and applicable concurrent
actions. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by August 14, 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–
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
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SUMMARY:
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p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
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.
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0624; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
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–2017–0624; Directorate Identifier
2016–NM–135–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
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will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0122, dated June 21,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A319 series airplanes, Model
A320–211, –212, –214, –231, –232, and
–233 airplanes, and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. The MCAI states:
Following an instrument landing system
(ILS) approach, during night, in rainy
condition, an A321 aeroplane experienced a
longitudinal runway excursion. Investigation
revealed that the approach was not stabilized
with an overspeed of 19 knots (kts) over the
runway threshold, followed by a long flare
(18 seconds) with touchdown far behind the
touchdown zone. The aeroplane exited the
runway at 75 kts and came to rest around 300
meters beyond the end of the runway. During
the final approach, at 150 feet Radio
Altimeter (RA) altitude, the corrected
airspeed of the aeroplane was 165 kts (24 kts
overspeed). Auto thrust (ATHR) commanded
a transient N1 increase up to 70% due to the
ATHR speed Mach control law.
The ATHR system on A320 family
aeroplane was designed to maintain
accurately the aircraft speed/Mach to speed/
Mach target by commanding the thrust,
featuring also a trade-off at low altitude
between thrust corrections to maintain speed
equal to speed target and too large thrust
corrections destabilizing the aircraft
trajectory near the ground. The conclusions
of the investigations were that the main
contributor to this runway excursion was a
non-stabilized approach not followed by a
go-around. ATHR misbehaviour in case of
large overspeed led to an unexpected thrust
increase, which is considered as a
contributor to the long flare.
This ATHR characteristic, reported as
‘‘Spurious thrust increase during approach,’’
was initially found in 1996 and a
modification was developed and introduced
in Flight Guidance (FG) 2G standard ‘‘C8 or
I8’’ (C for CFM engines and I for IAE engines)
in 2001.
Prompted by these findings, Airbus
introduced a programme to encourage
operators to replace the FMGC Legacy with
the FMGC equipped with Flight Management
System type 2 (FMS2) and FG standard,
which introduces additional operational
capabilities, including Runway Overrun
Protection System/Runway Overrun Warning
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(ROPS/ROW) and Autopilot/Traffic Collision
Avoidance System (AP/TCAS). It was
determined that the ROPS, in a scenario
similar to the one described above, would
have triggered a ‘‘RUNWAY TOO SHORT’’
aural alert before touchdown. Information
was made available through Airbus Service
Information Letter (SIL) 22–039 (later
superseded by Word In Service Experience
(WISE) In Service Information 22.83.00003),
and EASA published Safety Information
Bulletin (SIB) 2013–19, recommending the
FMGC upgrade.
Since EASA SIB was published, it was
determined that many operators have chosen
not to implement the optional upgrade that
improves the ATHR behaviour.
More recently, prompted by a
recommendation from the BEA (Bureau
ˆ
´
´
d’Enquetes et d’Analyses pour la securite de
l’aviation civile) of France, to reduce the risk
of further runway excursions due to
uninterrupted unstable approaches
performed with the legacy FMGC standard,
EASA decided to require installation of at
least the first version of the FMS2 and
associated FG for legacy aeroplanes.
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD 1999–411–140(B)R1
[which corresponds to FAA AD 2000–12–13,
Amendment 39–11791 (65 FR 37845, June
19, 2000) (‘‘AD 2000–12–13’’)] and AD 1998–
226–119(B)R1 [which corresponds to FAA
AD 98–19–08, Amendment 39–10750 (63 FR
50503, September 22, 1998)] to address
different unsafe conditions, requiring to
install a certain previous FMGC standard that
may be susceptible to the ‘‘Spurious thrust
increase during approach’’.
For the reasons described above, this
[EASA] AD * * * requires replacement of
the affected FMGC units with upgraded units
[and applicable concurrent actions].
Concurrent actions include the
installation of certain FMGCs, wiring,
display management computers, wiring
associated with pin programming, and
applicable operational program
configuration disks. 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–2017–0624.
Other Related Rulemaking
On September 2, 1998, we issued AD
98–19–08, Amendment 39–10750 (63
FR 50503, September 22, 1998) (‘‘AD
98–19–08’’), for certain Airbus Model
A321 series airplanes. AD 98–19–08 was
prompted by issuance of mandatory
continuing airworthiness information by
a foreign civil airworthiness authority.
AD 98–19–08 requires revising the
airplane flight manual to prohibit
automatic landings and Category III
operations on runways with a magnetic
orientation of 170 through 190 degrees
inclusive. We issued AD 98–19–08 to
prevent the use of erroneous automatic
roll-out guidance generated by the
FMGC, which could result in the
airplane departing the runway upon
landing.
On June 9, 2000, we issued AD 2000–
12–13, Amendment 39–11791 (65 FR
37845, June 19, 2000) (‘‘AD 2000–12–
13’’), for certain Airbus Model A319,
A320, and A321 series airplanes. AD
2000–12–13 was prompted by issuance
of mandatory continuing airworthiness
information by a foreign civil
airworthiness authority. AD 2000–12–13
requires modification or replacement of
all existing FMGC’s, as applicable. We
issued AD 2000–12–13 to prevent
erroneous navigational calculations,
which could result in an increased risk
of collision with terrain or other
airplanes.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information, which describes
procedures for replacement of any
affected FMGC with a serviceable
FMGC. These documents are distinct
since they apply to different airplane
configurations.
• Airbus Service Bulletin A320–22–
1090, Revision 11, dated July 20, 2004.
• Airbus Service Bulletin A320–22–
1103, Revision 04, dated March 12,
2004.
• Airbus Service Bulletin A320–22–
1116, Revision 04, dated March 29,
2004.
• Airbus Service Bulletin A320–22–
1152, Revision 03, dated February 18,
2005.
• Airbus Service Bulletin A320–22–
1243, Revision 05, dated May 31, 2010.
• Airbus Service Bulletin A320–22–
1519, Revision 02, dated December 21,
2015.
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 Proposed AD
and the MCAI
The MCAI supersedes two DGAC
ADs, which correspond to FAA AD 98–
19–08 and AD 2000–12–13. The MCAI
does not retain the requirements of the
DGAC ADs. This proposed AD is a
stand-alone AD that specifies
accomplishing the actions required by
this proposed AD would terminate all
requirements of AD 2000–12–13. We
have determined that the actions
specified in AD 2000–12–13 must
continue to be required until the actions
of the proposed AD are accomplished.
This proposed AD does not terminate
the actions specified in AD 98–19–08
because it addresses a different unsafe
condition relative to installing a certain
previous FMGC standard, as stated in
EASA AD 2016–0122.
Costs of Compliance
We estimate that this proposed AD
affects 1,032 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
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Action
Labor cost
Inspection ...................
1 work-hour × $85 per hour = $85 .....................................................
We estimate the following costs to do
any necessary replacements that would
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be required based on the results of the
proposed inspection. We have no way of
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Cost per
product
Parts cost
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$0
$85
Cost on
U.S. operators
$87,720
determining the number of aircraft that
might need these replacements.
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ON-CONDITION COSTS
Action
Labor cost
Replacement .....................
9 work-hours × $85 per hour = $765 .......................................................................
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.
sradovich on DSK3GMQ082PROD with PROPOSALS
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.
$30,000
$30,765
(f) Compliance
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.
§ 39.13
Cost per
product
Parts cost
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2017–0624;
Directorate Identifier 2016–NM–135–AD.
(a) Comments Due Date
We must receive comments by August 14,
2017.
(b) Affected ADs
This AD affects AD 2000–12–13,
Amendment 39–11791 (65 FR 37845, June
19, 2000) (‘‘AD 2000–12–13’’).
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) through (c)(3) of this AD, all
manufacturer serial numbers.
(1) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(2) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(3) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 22, Auto Flight.
(e) Reason
This AD was prompted by a report of a
runway excursion due to an unexpected
thrust increase leading to an unstable
approach performed using the current flight
management and guidance computer (FMGC)
standard. We are issuing this AD to prevent
unstable approaches due to an unexpected
thrust increase, which could result in
reduced controllability of the airplane and
runway excursions.
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Replacement of Affected
FMGC
(1) Within 36 months after the effective
date of this AD: Inspect the FMGC to
determine if any FMGC with an affected part
number identified in Figure 1 to paragraphs
(g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD
is installed. A review of airplane
maintenance records is acceptable in lieu of
inspecting the FMGC, provided those records
can be relied upon for that purpose and the
part number of the FMGC can be
conclusively identified from that review.
(2) If any affected FMGC with an affected
part number identified in Figure 1 to
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j)
of this AD is found during any inspection or
review required by paragraph (g)(1) of this
AD: Within 36 months after the effective date
of this AD, replace the FMGC with a
serviceable FMGC having a part number that
is not identified in Figure 1 to paragraphs
(g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD,
in accordance with the Accomplishment
Instructions and paragraph 1.B. (concurrent
actions) of the applicable service information
specified in paragraphs (g)(2)(i) through
(g)(2)(vi) of this AD, or 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). Refer
to Figure 2 to paragraph (g)(2) of this AD and
Figure 3 to paragraph (g)(2) of this AD for the
lists of approved eligible FMGCs certified as
of the effective date of this AD.
(i) Airbus Service Bulletin A320–22–1090,
Revision 11, dated July 20, 2004 (installation
of FMGC part number (P/N) C13042BA01).
(ii) Airbus Service Bulletin A320–22–1103,
Revision 04, dated March 12, 2004
(installation of FMGC P/N C13043AA01).
(iii) Airbus Service Bulletin A320–22–
1116, Revision 04, dated March 29, 2004
(installation of FMGC P/N C13043BA01).
(iv) Airbus Service Bulletin A320–22–
1152, Revision 03, dated February 18, 2005
(installation of FMGC P/N C13043AA02).
(v) Airbus Service Bulletin A320–22–1243,
Revision 05, dated May 31, 2010 (installation
of FMGC P/N C13043BA04).
(vi) Airbus Service Bulletin A320–22–
1519, Revision 02, dated December 21, 2015
(installation of FMGC P/N C13207CA00).
FIGURE 1 TO PARAGRAPHS (g)(1), (g)(2), (h)(1), (h)(2), AND (j) OF THIS AD—AFFECTED FMGCS
Airplanes
FMGC No.
A319–111 ...........................................................................
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FIGURE 1 TO PARAGRAPHS (g)(1), (g)(2), (h)(1), (h)(2), AND (j) OF THIS AD—AFFECTED FMGCS—Continued
Airplanes
A319–112 ...........................................................................
A319–113 ...........................................................................
A319–114 ...........................................................................
A319–115 ...........................................................................
A320–211 ...........................................................................
A320–212 ...........................................................................
A320–214 ...........................................................................
A321–111.
A321–112.
A321–211.
A321–212 and A321–213 (all CFM56).
A319–131 ...........................................................................
A319–132 ...........................................................................
A319–133 ...........................................................................
A320–231 ...........................................................................
A320–232 ...........................................................................
A320–233.
A321–131.
A321–231 and A321–232 (all V2500).
B398AAM0407
B398AAM0411
B398BAM0203
B398BAM0207
B546BAM0202
B546BAM0206
B546CAM0104
B398AAM0408
B398AAM0412
B398BAM0204
B398BAM0208
B546BAM0203
B546CAM0101
B398AAM0409
B398BAM0101
B398BAM0205
B398BAM0209
B546BAM0204
B546CAM0102
B398AAM0410
B398BAM0202
B398BAM0206
B546BAM0101
B546BAM0205
B546CAM0103
B398BCM0101
B398BCM0105
B398BCM0109
B546BCM0204
B546CCM0103
B398BCM0102
B398BCM0106
B546BCM0101
B546BCM0205
B546CCM0104
B398BCM0103
B398BCM0107
B546BCM0102
B546CCM0101
B546CCM0105
B398BCM0104
B398BCM0108
B546BCM0203
B546CCM0102
B546CCM0106
FIGURE 2 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE
DATE OF THIS AD
Airplanes
A319–111
A319–112
A319–113
A319–114
A319–115
A320–211
A320–212
A320–214
A321–111
A321–112
A321–211
A321–212
A321–213
FMGC part No.
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
and ..........................................................................................................................................
(all CFM56) .............................................................................................................................
C13042AA01
C13042AA02
C13042AA03
C13042AA04
C13042AA05
C13042AA06
C13042AA07
C13043AA01
C13043AA02
C13043AA03
C13043AA04
C13043AA05
C13043AA06
FMGC hardware
C13207AA00
C13207CA00
C13207CA00
C13208AA00
C13208AA00
C13208AA00
Flight Guidance
(FG) software
G2858AAA01
G2858AAA02
G2858AAA03
G2858AAA01
G2858AAA02
G2858AAA03
FIGURE 3 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE
DATE OF THIS AD
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Airplanes
A319–131
A319–132
A319–133
A320–231
A320–232
A320–233
A321–131
A321–231
A321–232
FMGC part No.
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
..................................................................................................................................................
and ..........................................................................................................................................
(all V2500) ...............................................................................................................................
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C13042BA01
C13042BA02
C13042BA03
C13042BA04
C13042BA05
C13042BA06
C13042BA07
C13042BA08
C13043BA01
C13043BA02
C13043BA03
C13043BA04
C13043BA05
C13043BA06
C13043BA07
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FIGURE 3 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE
DATE OF THIS AD—Continued
Airplanes
C13043BA08
FMGC hardware
C13207BA00
C13207DA00
C13207DA00
C13207DA00
C13208BA00
C13208BA00
C13208BA00
C13208BA00
(h) Unaffected Airplanes
(1) An airplane on which Airbus
Modification 31896 or Airbus Modification
31897 has been embodied in production is
not affected by the requirements of paragraph
(g) of this AD, provided it is conclusively
determined that no FMGC with an affected
part number identified in Figure 1 to
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j)
of this AD has been installed on that airplane
since the date of issuance of the original
certificate of airworthiness or the original
export certificate of airworthiness. A review
of airplane maintenance records is acceptable
to make this determination provided those
records can be relied upon for that purpose
and the part number of the FMGC can be
conclusively identified from that review.
(2) An airplane on which the actions
specified in paragraph (g)(2) have been done
before the effective date of this AD is not
affected by the requirements in paragraph (g)
of this AD, provided it is conclusively
determined that no FMGC with an affected
part number identified in Figure 1 to
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j)
of this AD has been installed on that airplane
since accomplishing the actions specified in
paragraph (g)(2) of this AD. A review of
airplane maintenance records is acceptable to
make this determination provided those
records can be relied upon for that purpose
and the part number of the FMGC can be
conclusively identified from that review.
(i) Parts Installation Limitation
Installation of an FMGC standard approved
after the effective date of this AD on any
airplane, is acceptable for compliance with
the actions required by paragraph (g)(2) of
this AD, provided the conditions specified in
paragraphs (i)(1) and (i)(2) of this AD are
accomplished.
(1) The software and hardware standard, as
applicable, must be approved by the
Manager, International Branch, ANM–116,
(FG) software
G2859AAA01
G2859AAA02
G2859AAA03
G2859AAA04
G2859AAA01
G2859AAA02
G2859AAA03
G2859AAA04
Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA.
(2) The installation must be accomplished
using airplane modification instructions
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install on any airplane an FMGC
with an affected part number identified in
Figure 1 to paragraphs (g)(1), (g)(2), (h)(1),
(h)(2), and (j) of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g)(2) of this AD, if
those actions were performed before the
effective date of this AD using the applicable
service information identified in Figure 4 to
paragraph (k) of this AD.
FIGURE 4 TO PARAGRAPH (k) OF THIS AD—SERVICE INFORMATION ACCEPTABLE FOR CREDIT FOR ACTIONS IN
PARAGRAPH (g)(2) OF THIS AD
Airbus service bulletin
C13042BA01 .......................................................
A320–22–1090 ...................................................
C13043AA01 .......................................................
A320–22–1103 ...................................................
C13043BA01 .......................................................
sradovich on DSK3GMQ082PROD with PROPOSALS
FMGC/FG install
A320–22–1116 ...................................................
C13043AA02 .......................................................
A320–22–1152 ...................................................
C13043BA04 .......................................................
A320–22–1243 ...................................................
VerDate Sep<11>2014
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Jkt 241001
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29JNP1
March 5, 2002.
April 15, 2002.
June 14, 2002.
October 1, 2002.
November 26, 2002.
January 13, 2003.
March 3, 2003.
June 26, 2003.
October 15, 2003.
November 7, 2003.
January 22, 2004.
October 8, 2002.
April 1, 2003.
August 28, 2003.
October 15, 2003.
January 31, 2003.
August 4, 2003.
October 17, 2003.
February 25, 2004.
May 5, 2004.
July 6, 2004.
October 15, 2004.
October 16, 2007.
April 1, 2008.
September 10, 2008.
February 17, 2009.
March 3, 2010.
29445
Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules
FIGURE 4 TO PARAGRAPH (k) OF THIS AD—SERVICE INFORMATION ACCEPTABLE FOR CREDIT FOR ACTIONS IN
PARAGRAPH (g)(2) OF THIS AD—Continued
FMGC/FG install
Airbus service bulletin
C13207CA00 ......................................................
A320–22–1519 ...................................................
Issued in Renton, Washington, on June 16,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(m) 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 (n)(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: 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.
sradovich on DSK3GMQ082PROD with PROPOSALS
(l) Terminating Action for Other ADs
Accomplishing the actions required by
paragraph (g)(1) of this AD, and, as
applicable, paragraph (g)(2) of this AD,
terminates all requirements of AD 2000–12–
13.
BILLING CODE 4910–13–P
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0122, dated
June 21, 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–
2017–0624.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM 116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227 1405; fax 425–227 1149.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email 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.
VerDate Sep<11>2014
16:13 Jun 28, 2017
Jkt 241001
[FR Doc. 2017–13406 Filed 6–28–17; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0648; Directorate
Identifier 2017–CE–012–AD]
RIN 2120–AA64
Airworthiness Directives; Piaggio Aero
Industries S.p.A. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Piaggio
Aero Industries S.p.A. Model P–180
airplanes. This proposed AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as disbonding of the upper
and lower metal skin from the
honeycomb core on the elevator
assembly and other flight control
surfaces. We are issuing this proposed
AD to require actions to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by August 14, 2017.
ADDRESSES: You may send comments 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–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
SUMMARY:
PO 00000
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Fmt 4702
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Date
00
01
June 26, 2015.
August 26, 2015.
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Piaggio Aero
Industries S.p.A—Continued
Airworthiness, Via Pionieri e Aviatori
d’Italia snc—16154 Genova, Italy;
Telephone: +39 010 0998046; Fax:
None; email: airworthiness@
piaggioaerospace.it; Internet:
www.piaggioaerospace.it/en/customersupport#care. You may review this
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
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–
0648; 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 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:
Mike Kiesov, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816)
329–4090; email: mike.kiesov@faa.gov.
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–2017–0648; Directorate Identifier
2017–CE–012–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
E:\FR\FM\29JNP1.SGM
29JNP1
]]>Agencies
[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)]
[Proposed Rules]
[Pages 29440-29445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13406]
========================================================================
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. 124 / Thursday, June 29, 2017 /
Proposed Rules
[[Page 29440]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0624; Directorate Identifier 2016-NM-135-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, -
232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. This proposed AD was prompted by a
runway excursion due to an unexpected thrust increase leading to an
unstable approach performed using the current flight management and
guidance computer (FMGC) standard. This proposed AD would require
identification of potentially affected FMGCs, replacement of any
affected FMGC, and applicable concurrent actions. We are proposing this
AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 14, 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-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email 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-
0624; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
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-2017-0624;
Directorate Identifier 2016-NM-135-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0122, dated June 21, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A319
series airplanes, Model A320-211, -212, -214, -231, -232, and -233
airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. The MCAI states:
Following an instrument landing system (ILS) approach, during
night, in rainy condition, an A321 aeroplane experienced a
longitudinal runway excursion. Investigation revealed that the
approach was not stabilized with an overspeed of 19 knots (kts) over
the runway threshold, followed by a long flare (18 seconds) with
touchdown far behind the touchdown zone. The aeroplane exited the
runway at 75 kts and came to rest around 300 meters beyond the end
of the runway. During the final approach, at 150 feet Radio
Altimeter (RA) altitude, the corrected airspeed of the aeroplane was
165 kts (24 kts overspeed). Auto thrust (ATHR) commanded a transient
N1 increase up to 70% due to the ATHR speed Mach control law.
The ATHR system on A320 family aeroplane was designed to
maintain accurately the aircraft speed/Mach to speed/Mach target by
commanding the thrust, featuring also a trade-off at low altitude
between thrust corrections to maintain speed equal to speed target
and too large thrust corrections destabilizing the aircraft
trajectory near the ground. The conclusions of the investigations
were that the main contributor to this runway excursion was a non-
stabilized approach not followed by a go-around. ATHR misbehaviour
in case of large overspeed led to an unexpected thrust increase,
which is considered as a contributor to the long flare.
This ATHR characteristic, reported as ``Spurious thrust increase
during approach,'' was initially found in 1996 and a modification
was developed and introduced in Flight Guidance (FG) 2G standard
``C8 or I8'' (C for CFM engines and I for IAE engines) in 2001.
Prompted by these findings, Airbus introduced a programme to
encourage operators to replace the FMGC Legacy with the FMGC
equipped with Flight Management System type 2 (FMS2) and FG
standard, which introduces additional operational capabilities,
including Runway Overrun Protection System/Runway Overrun Warning
[[Page 29441]]
(ROPS/ROW) and Autopilot/Traffic Collision Avoidance System (AP/
TCAS). It was determined that the ROPS, in a scenario similar to the
one described above, would have triggered a ``RUNWAY TOO SHORT''
aural alert before touchdown. Information was made available through
Airbus Service Information Letter (SIL) 22-039 (later superseded by
Word In Service Experience (WISE) In Service Information
22.83.00003), and EASA published Safety Information Bulletin (SIB)
2013-19, recommending the FMGC upgrade.
Since EASA SIB was published, it was determined that many
operators have chosen not to implement the optional upgrade that
improves the ATHR behaviour.
More recently, prompted by a recommendation from the BEA (Bureau
d'Enqu[ecirc]tes et d'Analyses pour la s[eacute]curit[eacute] de
l'aviation civile) of France, to reduce the risk of further runway
excursions due to uninterrupted unstable approaches performed with
the legacy FMGC standard, EASA decided to require installation of at
least the first version of the FMS2 and associated FG for legacy
aeroplanes.
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD 1999-411-140(B)R1 [which corresponds to FAA AD
2000-12-13, Amendment 39-11791 (65 FR 37845, June 19, 2000) (``AD
2000-12-13'')] and AD 1998-226-119(B)R1 [which corresponds to FAA AD
98-19-08, Amendment 39-10750 (63 FR 50503, September 22, 1998)] to
address different unsafe conditions, requiring to install a certain
previous FMGC standard that may be susceptible to the ``Spurious
thrust increase during approach''.
For the reasons described above, this [EASA] AD * * * requires
replacement of the affected FMGC units with upgraded units [and
applicable concurrent actions].
Concurrent actions include the installation of certain FMGCs,
wiring, display management computers, wiring associated with pin
programming, and applicable operational program configuration disks.
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-
0624.
Other Related Rulemaking
On September 2, 1998, we issued AD 98-19-08, Amendment 39-10750 (63
FR 50503, September 22, 1998) (``AD 98-19-08''), for certain Airbus
Model A321 series airplanes. AD 98-19-08 was prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. AD 98-19-08 requires revising the airplane
flight manual to prohibit automatic landings and Category III
operations on runways with a magnetic orientation of 170 through 190
degrees inclusive. We issued AD 98-19-08 to prevent the use of
erroneous automatic roll-out guidance generated by the FMGC, which
could result in the airplane departing the runway upon landing.
On June 9, 2000, we issued AD 2000-12-13, Amendment 39-11791 (65 FR
37845, June 19, 2000) (``AD 2000-12-13''), for certain Airbus Model
A319, A320, and A321 series airplanes. AD 2000-12-13 was prompted by
issuance of mandatory continuing airworthiness information by a foreign
civil airworthiness authority. AD 2000-12-13 requires modification or
replacement of all existing FMGC's, as applicable. We issued AD 2000-
12-13 to prevent erroneous navigational calculations, which could
result in an increased risk of collision with terrain or other
airplanes.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information, which
describes procedures for replacement of any affected FMGC with a
serviceable FMGC. These documents are distinct since they apply to
different airplane configurations.
Airbus Service Bulletin A320-22-1090, Revision 11, dated
July 20, 2004.
Airbus Service Bulletin A320-22-1103, Revision 04, dated
March 12, 2004.
Airbus Service Bulletin A320-22-1116, Revision 04, dated
March 29, 2004.
Airbus Service Bulletin A320-22-1152, Revision 03, dated
February 18, 2005.
Airbus Service Bulletin A320-22-1243, Revision 05, dated
May 31, 2010.
Airbus Service Bulletin A320-22-1519, Revision 02, dated
December 21, 2015.
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 Proposed AD and the MCAI
The MCAI supersedes two DGAC ADs, which correspond to FAA AD 98-19-
08 and AD 2000-12-13. The MCAI does not retain the requirements of the
DGAC ADs. This proposed AD is a stand-alone AD that specifies
accomplishing the actions required by this proposed AD would terminate
all requirements of AD 2000-12-13. We have determined that the actions
specified in AD 2000-12-13 must continue to be required until the
actions of the proposed AD are accomplished.
This proposed AD does not terminate the actions specified in AD 98-
19-08 because it addresses a different unsafe condition relative to
installing a certain previous FMGC standard, as stated in EASA AD 2016-
0122.
Costs of Compliance
We estimate that this proposed AD affects 1,032 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection.................... 1 work-hour x $85 per hour = $85 $0 $85 $87,720
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements.
[[Page 29442]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement........................... 9 work-hours x $85 per hour = $765...... $30,000 $30,765
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2017-0624; Directorate Identifier 2016-NM-
135-AD.
(a) Comments Due Date
We must receive comments by August 14, 2017.
(b) Affected ADs
This AD affects AD 2000-12-13, Amendment 39-11791 (65 FR 37845,
June 19, 2000) (``AD 2000-12-13'').
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) through (c)(3) of this AD,
all manufacturer serial numbers.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 22, Auto Flight.
(e) Reason
This AD was prompted by a report of a runway excursion due to an
unexpected thrust increase leading to an unstable approach performed
using the current flight management and guidance computer (FMGC)
standard. We are issuing this AD to prevent unstable approaches due
to an unexpected thrust increase, which could result in reduced
controllability of the airplane and runway excursions.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Replacement of Affected FMGC
(1) Within 36 months after the effective date of this AD:
Inspect the FMGC to determine if any FMGC with an affected part
number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1),
(h)(2), and (j) of this AD is installed. A review of airplane
maintenance records is acceptable in lieu of inspecting the FMGC,
provided those records can be relied upon for that purpose and the
part number of the FMGC can be conclusively identified from that
review.
(2) If any affected FMGC with an affected part number identified
in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of
this AD is found during any inspection or review required by
paragraph (g)(1) of this AD: Within 36 months after the effective
date of this AD, replace the FMGC with a serviceable FMGC having a
part number that is not identified in Figure 1 to paragraphs (g)(1),
(g)(2), (h)(1), (h)(2), and (j) of this AD, in accordance with the
Accomplishment Instructions and paragraph 1.B. (concurrent actions)
of the applicable service information specified in paragraphs
(g)(2)(i) through (g)(2)(vi) of this AD, or 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). Refer to Figure 2
to paragraph (g)(2) of this AD and Figure 3 to paragraph (g)(2) of
this AD for the lists of approved eligible FMGCs certified as of the
effective date of this AD.
(i) Airbus Service Bulletin A320-22-1090, Revision 11, dated
July 20, 2004 (installation of FMGC part number (P/N) C13042BA01).
(ii) Airbus Service Bulletin A320-22-1103, Revision 04, dated
March 12, 2004 (installation of FMGC P/N C13043AA01).
(iii) Airbus Service Bulletin A320-22-1116, Revision 04, dated
March 29, 2004 (installation of FMGC P/N C13043BA01).
(iv) Airbus Service Bulletin A320-22-1152, Revision 03, dated
February 18, 2005 (installation of FMGC P/N C13043AA02).
(v) Airbus Service Bulletin A320-22-1243, Revision 05, dated May
31, 2010 (installation of FMGC P/N C13043BA04).
(vi) Airbus Service Bulletin A320-22-1519, Revision 02, dated
December 21, 2015 (installation of FMGC P/N C13207CA00).
Figure 1 to Paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of This AD--Affected FMGCs
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
Airplanes FMGC No.
--------------------------------------------------------------------------------------------------------------------------------------------------------
A319-111......................... B398AAM0303 B398AAM0304 B398AAM0405 B398AAM0406
[[Page 29443]]
A319-112......................... B398AAM0407 B398AAM0408 B398AAM0409 B398AAM0410
A319-113......................... B398AAM0411 B398AAM0412 B398BAM0101 B398BAM0202
A319-114......................... B398BAM0203 B398BAM0204 B398BAM0205 B398BAM0206
A319-115......................... B398BAM0207 B398BAM0208 B398BAM0209 B546BAM0101
A320-211......................... B546BAM0202 B546BAM0203 B546BAM0204 B546BAM0205
A320-212......................... B546BAM0206 B546CAM0101 B546CAM0102 B546CAM0103
A320-214......................... B546CAM0104
A321-111.........................
A321-112.........................
A321-211.........................
A321-212 and A321-213 (all CFM56)
A319-131......................... B398BCM0101 B398BCM0102 B398BCM0103 B398BCM0104
A319-132......................... B398BCM0105 B398BCM0106 B398BCM0107 B398BCM0108
A319-133......................... B398BCM0109 B546BCM0101 B546BCM0102 B546BCM0203
A320-231......................... B546BCM0204 B546BCM0205 B546CCM0101 B546CCM0102
A320-232......................... B546CCM0103 B546CCM0104 B546CCM0105 B546CCM0106
A320-233.........................
A321-131.........................
A321-231 and A321-232 (all V2500)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Figure 2 to Paragraph (g)(2) of This AD--List of Approved Eligible FMGCs Certified as of the Effective Date of
This AD
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes FMGC part No.
----------------------------------------------------------------------------------------------------------------
A319-111................................ C13042AA01
A319-112................................ C13042AA02
A319-113................................ C13042AA03
A319-114................................ C13042AA04
A319-115................................ C13042AA05
A320-211................................ C13042AA06
A320-212................................ C13042AA07
A320-214................................ C13043AA01
A321-111................................ C13043AA02
A321-112................................ C13043AA03
A321-211................................ C13043AA04
A321-212 and............................ C13043AA05
A321-213 (all CFM56).................... C13043AA06
-----------------------------------------------------------------------
FMGC hardware Flight Guidance
(FG) software
-----------------------------------------------------------------------
C13207AA00 G2858AAA01
C13207CA00 G2858AAA02
C13207CA00 G2858AAA03
C13208AA00 G2858AAA01
C13208AA00 G2858AAA02
C13208AA00 G2858AAA03
----------------------------------------------------------------------------------------------------------------
Figure 3 to Paragraph (g)(2) of This AD--List of Approved Eligible FMGCs Certified as of the Effective Date of
This AD
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes FMGC part No.
----------------------------------------------------------------------------------------------------------------
A319-131................................ C13042BA01
A319-132................................ C13042BA02
A319-133................................ C13042BA03
A320-231................................ C13042BA04
A320-232................................ C13042BA05
A320-233................................ C13042BA06
A321-131................................ C13042BA07
A321-231 and............................ C13042BA08
A321-232 (all V2500).................... C13043BA01
C13043BA02
C13043BA03
C13043BA04
C13043BA05
C13043BA06
C13043BA07
[[Page 29444]]
C13043BA08
-----------------------------------------------------------------------
FMGC hardware (FG) software
-----------------------------------------------------------------------
C13207BA00 G2859AAA01
C13207DA00 G2859AAA02
C13207DA00 G2859AAA03
C13207DA00 G2859AAA04
C13208BA00 G2859AAA01
C13208BA00 G2859AAA02
C13208BA00 G2859AAA03
C13208BA00 G2859AAA04
----------------------------------------------------------------------------------------------------------------
(h) Unaffected Airplanes
(1) An airplane on which Airbus Modification 31896 or Airbus
Modification 31897 has been embodied in production is not affected
by the requirements of paragraph (g) of this AD, provided it is
conclusively determined that no FMGC with an affected part number
identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2),
and (j) of this AD has been installed on that airplane since the
date of issuance of the original certificate of airworthiness or the
original export certificate of airworthiness. A review of airplane
maintenance records is acceptable to make this determination
provided those records can be relied upon for that purpose and the
part number of the FMGC can be conclusively identified from that
review.
(2) An airplane on which the actions specified in paragraph
(g)(2) have been done before the effective date of this AD is not
affected by the requirements in paragraph (g) of this AD, provided
it is conclusively determined that no FMGC with an affected part
number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1),
(h)(2), and (j) of this AD has been installed on that airplane since
accomplishing the actions specified in paragraph (g)(2) of this AD.
A review of airplane maintenance records is acceptable to make this
determination provided those records can be relied upon for that
purpose and the part number of the FMGC can be conclusively
identified from that review.
(i) Parts Installation Limitation
Installation of an FMGC standard approved after the effective
date of this AD on any airplane, is acceptable for compliance with
the actions required by paragraph (g)(2) of this AD, provided the
conditions specified in paragraphs (i)(1) and (i)(2) of this AD are
accomplished.
(1) The software and hardware standard, as applicable, must be
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(2) The installation must be accomplished using airplane
modification instructions approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA.
(j) Parts Installation Prohibition
As of the effective date of this AD, no person may install on
any airplane an FMGC with an affected part number identified in
Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of
this AD.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g)(2) of this AD, if those actions were performed before the
effective date of this AD using the applicable service information
identified in Figure 4 to paragraph (k) of this AD.
Figure 4 to Paragraph (k) of this AD--Service Information Acceptable for Credit for Actions in Paragraph (g)(2)
of This AD
----------------------------------------------------------------------------------------------------------------
FMGC/FG install Airbus service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
C13042BA01...................... A320-22-1090............ 00 March 5, 2002.
01 April 15, 2002.
02 June 14, 2002.
03 October 1, 2002.
04 November 26, 2002.
05 January 13, 2003.
06 March 3, 2003.
07 June 26, 2003.
08 October 15, 2003.
09 November 7, 2003.
10 January 22, 2004.
C13043AA01...................... A320-22-1103............ 00 October 8, 2002.
01 April 1, 2003.
02 August 28, 2003.
03 October 15, 2003.
C13043BA01...................... A320-22-1116............ 00 January 31, 2003.
01 August 4, 2003.
02 October 17, 2003.
03 February 25, 2004.
C13043AA02...................... A320-22-1152............ 00 May 5, 2004.
01 July 6, 2004.
02 October 15, 2004.
C13043BA04...................... A320-22-1243............ 00 October 16, 2007.
01 April 1, 2008.
02 September 10, 2008.
03 February 17, 2009.
04 March 3, 2010.
[[Page 29445]]
C13207CA00...................... A320-22-1519............ 00 June 26, 2015.
01 August 26, 2015.
----------------------------------------------------------------------------------------------------------------
(l) Terminating Action for Other ADs
Accomplishing the actions required by paragraph (g)(1) of this
AD, and, as applicable, paragraph (g)(2) of this AD, terminates all
requirements of AD 2000-12-13.
(m) 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 (n)(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: 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0122, dated June 21, 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-2017-0624.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Branch, ANM 116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227 1405; fax 425-227 1149.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email 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 16, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13406 Filed 6-28-17; 8:45 am]
BILLING CODE 4910-13-P
