Airworthiness Directives; Airbus Airplanes, 31844-31848 [2016-11575]
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31844
Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations
Where:
E24 = 24-hour energy as determined in
section 5.10 of this appendix,
Ebatt = Measured battery energy as determined
in section 5.8 of this appendix,
Pm = Maintenance mode power as
determined in section 5.9 of this
appendix,
Psb = Standby mode power as determined in
section 5.11 of this appendix,
Poff = Off mode power as determined in
section 5.12 of this appendix,
tcd = Charge test duration as determined in
section 5.2 of this appendix, and
ta&m, n, tsb, and toff, are constants used
depending upon a device’s product class
and found in the following table:
TABLE 5.3—BATTERY CHARGER USAGE PROFILES
Product class
No.
Hours per day ***
Active +
maintenance
(ta&m)
Charges
(n)
Threshold
charge
time *
Number per
day
Hours
Rated battery
energy
(Ebatt) **
Description
Special
characteristic
or battery voltage
20.66
0.10
0.00
0.15
137.73
7.82
5.29
0.00
0.54
14.48
Standby
(tsb)
Off
(toff)
1 ...
Low-Energy ...........
≤5 Wh ....................
2 ...
Low-Energy, LowVoltage.
Low-Energy, Medium-Voltage.
Low-Energy, HighVoltage.
Medium-Energy,
Low-Voltage.
Medium-Energy,
High-Voltage.
High-Energy ..........
<100 Wh ................
Inductive Connection ****.
<4 V .......................
................................
4–10 V ...................
6.42
0.30
0.00
0.10
64.20
................................
>10 V .....................
16.84
0.91
0.00
0.50
33.68
100–3000 Wh ........
<20 V .....................
6.52
1.16
0.00
0.11
59.27
................................
≥20 V .....................
17.15
6.85
0.00
0.34
50.44
>3000 Wh ..............
................................
8.14
7.30
0.00
0.32
25.44
3 ...
4 ...
5 ...
6 ...
7 ...
* If the duration of the charge test (minus 5 hours) as determined in section 5.2 of appendix Y to subpart B of this part exceeds the threshold
charge time, use equation (ii) to calculate UEC otherwise use equation (i).
** Ebatt = Rated battery energy as determined in 10 CFR part 429.39(a).
*** If the total time does not sum to 24 hours per day, the remaining time is allocated to unplugged time, which means there is 0 power consumption and no changes to the UEC calculation needed.
**** Inductive connection and designed for use in a wet environment (e.g. electric toothbrushes).
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0006; Directorate
Identifier 2013–NM–147–AD; Amendment
39–18519; AD 2016–10–08]
RIN 2120–AA64
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Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
SUMMARY:
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22:59 May 19, 2016
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Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, A340–
300, A340–500, and A340–600 series
airplanes. This AD was prompted by the
results of endurance qualification tests
on the trimmable horizontal stabilizer
actuator (THSA), which revealed a
partial loss of the no-back brake (NBB)
efficiency in specific load conditions.
This AD requires inspecting certain
THSAs to determine the number of total
flight cycles the THSA has accumulated,
and replacing the THSA if necessary.
We are issuing this AD to detect and
correct premature wear of the carbon
friction disks on the NBB of the THSA.
Such a condition could lead to reduced
braking efficiency in certain load
conditions and, in conjunction with the
inability of the power gear train to keep
the ball screw in its last commanded
position, could result in uncommanded
movements of the trimmable horizontal
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stabilizer (THS) and loss of control of
the airplane.
This AD is effective June 24,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 24, 2016.
DATES:
For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330-A340@
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. It is also available on the Internet
ADDRESSES:
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[FR Doc. 2016–11486 Filed 5–19–16; 8:45 a.m.]
Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2014–0006.
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–2014–
0006; 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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to all Airbus Model
A330–200 Freighter, A330–200, A330–
300, A340–200, A340–300, A340–500,
and A340–600 series airplanes. The
SNPRM published in the Federal
Register on December 23, 2015 (80 FR
79738) (‘‘the SNPRM’’). We preceded
the SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on February 3,
2014 (79 FR 6104) (‘‘the NPRM’’). The
NPRM proposed to require inspecting
certain THSAs to determine the number
of total flight cycles the THSA has
accumulated, and replacing the THSA if
necessary. The NPRM was prompted by
the results of endurance qualification
tests on the THSA, which revealed a
partial loss of the NBB efficiency in
specific load conditions. The SNPRM
proposed to revise the NPRM by adding
airplanes to the proposed applicability,
reducing the proposed compliance
times for replacing affected TSHAs, and
revising the definition of a serviceable
THSA. We are issuing this AD to detect
and correct premature wear of the
carbon friction disks on the NBB of the
THSA. Such a condition could lead to
reduced braking efficiency in certain
load conditions and, in conjunction
with the inability of the power gear train
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to keep the ball screw in its last
commanded position, could result in
uncommanded movements of the THS
and loss of control of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0257R1, dated May 29,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Airbus Model
A330–200, A330–200 Freighter, A330–
300, A340–200, and A340–300 series
airplanes; and Model A340–500 and
A340–600 series airplanes. The MCAI
states:
During endurance qualification tests on
Trimmable Horizontal Stabilizer Actuator
(THSA) of another Airbus aeroplane type, a
partial loss of the no-back brake (NBB)
efficiency was experienced. Due to THSA
design similarity on the A330/A340 fleet, a
similar partial loss of the NBB efficiency was
identified on THSA Part Number (P/N) 47147
as installed on A330–300 and A340–200/–
300 aeroplanes, on THSA P/N 47172 as
installed on A330–200/–300 and A340–200/
–300 aeroplanes, and on THSA P/N 47175 as
installed on A340–500/600 aeroplanes.
Investigation results concluded that this
partial loss of braking efficiency in some
specific aerodynamic load conditions was
due to polishing and auto-contamination of
the NBB carbon friction disks.
This condition, if not detected and
corrected and in conjunction with the power
gear train not able to keep the ball screw in
its last commanded position, could lead to
uncommanded movements of the THS,
possibly resulting in loss of control of the
aeroplane.
To address this potential unsafe condition,
EASA issued AD 2013–0144 [https://
ad.easa.europa.eu/blob/easa_ad_2013_
0144.zip/AD_2013-0144R1_2] to require
replacement of each THSA that has exceeded
16,000 flight cycles (FC) in service, to be sent
in shop for NBB carbon disk replacement.
Since that AD was issued, a need for
clarification has been demonstrated,
regarding the identification of the THSA
‘affected’ by this requirement.
For this reason, EASA AD 2013–0144
[https://ad.easa.europa.eu/blob/easa_ad_
2013_0144.zip/AD_2013-0144R1_2] was
revised, confirming that this AD only affected
those THSA identified by Part Number (P/N)
in Airbus Alert Operator Transmission (AOT)
A27L005–13. In addition, a note was added
to make clear that the life limits as specified
in the current revision of ALS Part 4 are still
relevant for the affected THSA, as applicable
to aeroplane model and THSA P/N.
Since EASA AD 2013–0144R1 [https://
ad.easa.europa.eu/ad/2013-0144R1] was
issued, further assessment of the ageing/
endurance issue has resulted in the
conclusion that there is a need to replace the
NBB installed on the THSA.
Consequently, EASA issued AD 2014–0257
[https://ad.easa.europa.eu/blob/EASA_AD_
2014_0257_R1.pdf/AD_2014-0257R1_1]
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31845
which retained the requirements of EASA AD
2013–0144R1, which was superseded, and
required removal from service of affected
THSA. THSA should be sent in shop for NBB
carbon disk replacement. This [EASA] AD
affected additional THSA P/Ns when
compared to EASA AD 2013–0144R1 and
Airbus AOT A27L005–13.
Since that [EASA] AD was issued, it was
determined that it is necessary to consider
that the THSA removal for NBB disks
replacement could also be calculated since
last NBB disk replacement which was done
in-shop.
This AD also adds Model A340–541 and
A340–642 airplanes to the applicability.
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–2014–
0006.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information, all dated July 15,
2014.
• Service Bulletin A330–27–3199 (for
Model A330 series airplanes);
• Service Bulletin A340–27–4190 (for
Model A340–200 and –300 series
airplanes); and
• Service Bulletin A340–27–5062 (for
Model A340–500 and –600 series
airplanes).
The service information describes
procedures for inspecting the THSA to
determine the part number and
replacing THSAs having certain part
numbers with a new or serviceable part.
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.
Costs of Compliance
We estimate that this AD affects 94
airplanes of U.S. registry.
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Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Cost on U.S.
operators
Inspection ........................................................
3 work-hours × $85 per hour = $255 .............
$0
$255
$23,970
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
required inspection. We have no way of
determining the number of airplanes
that might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replacement .................................................................
23 work-hour × $85 per hour = $1,955 ........................
$722,556
$724,511
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.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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 that this AD:
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
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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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–10–08 Airbus: Amendment 39–18519.
Docket No. FAA–2014–0006; Directorate
Identifier 2013–NM–147–AD.
(a) Effective Date
This AD is effective June 24, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) through (c)(7) of this AD, all
manufacturer serial numbers.
(1) Model A330–201, –202, –203, –223, and
–243 airplanes.
(2) Model A330–223F and –243F airplanes.
(3) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(4) Model A340–211, –212, and –213
airplanes.
(5) Model A340–311, –312, and –313
airplanes.
(6) Model A340–541 airplanes.
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(7) Model A340–642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by the results of
endurance qualification tests on the
trimmable horizontal stabilizer actuator
(THSA), which revealed a partial loss of the
no-back brake (NBB) efficiency in specific
load conditions. We are issuing this AD to
detect and correct premature wear of the
carbon friction disks on the NBB of the
THSA. Such a condition could lead to
reduced braking efficiency in certain load
conditions and, in conjunction with the
inability of the power gear train to keep the
ball screw in its last commanded position,
could result in uncommanded movements of
the trimmable horizontal stabilizer and loss
of control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection To Determine THSA Part
Number and Accumulated Total Flight
Cycles
Within 90 days after the effective date of
this AD: Inspect the THSA to determine if it
has a part number that is specified in
paragraph (g)(1) or (g)(2) of this AD, and to
determine the total number of flight cycles
accumulated since the THSA’s first
installation on an airplane, or since the most
recent NBB replacement. A review of
airplane delivery or maintenance records is
acceptable in lieu of this inspection if the
part number of the THSA can be conclusively
determined from that review.
(1) For Model A330–200 Freighter, A330–
200, A330–300, A340–200 and A340–300
series airplanes: Part number (P/N) 47147–
500, 47147–700, 47172–300, 47172–500,
47172–510, or 47172–520.
(2) For Model A340–500 and –600 series
airplanes: P/N 47175–200, 47175–300,
47175–500, or 47175–520.
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(h) THSA Replacement for Airbus Model
A330–200 Freighter, A330–200, A330–300,
A340–200, and A340–300 Series Airplanes
For Airbus Model A330–200 Freighter,
A330–200, A330–300, A340–200, and A340–
300 series airplanes having a THSA with a
part number specified in paragraph (g)(1) of
this AD: At the applicable time specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD,
replace each affected THSA with a
serviceable THSA, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3199, dated July
15, 2014; or Airbus Service Bulletin A340–
27–4190, dated July 15, 2014; as applicable.
Note 1 to paragraphs (h), (i), and (j) of this
AD: The THSA life limits specified in Part
4—Aging System Maintenance of the Airbus
A330 and A340 Airworthiness Limitations
Sections are still relevant, as applicable to
airplane model and THSA part number.
(1) For a THSA that has accumulated or
exceeded 20,000 total flight cycles since the
THSA’s first installation on an airplane, or
since the most recent NBB replacement,
whichever is later, as of the effective date of
this AD: Within 6 months after the effective
date of this AD.
(2) For a THSA that has accumulated or
exceeded 16,000 total flight cycles, but less
than 20,000 total flight cycles since the
THSA’s first installation on an airplane, or
since the most recent NBB replacement,
whichever is later, as of the effective date of
this AD: At the applicable time specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) For Model A330–200 Freighter, A330–
200, and A330–300 series airplanes: Within
12 months after the effective date of this AD
but without exceeding 20,000 total flight
cycles.
(ii) For Model A340–200, and A340–300
series airplanes: Within 12 months after the
effective date of this AD but without
exceeding 20,000 total flight cycles.
(3) For a THSA that has accumulated less
than 16,000 total flight cycles since first
installation on an airplane, or since the most
recent NBB replacement, whichever is later,
as of the effective date of this AD: At the
applicable time specified in paragraph (i) of
this AD.
(i) Replacement Times for Airbus Model
A330–200 Freighter, A330–200, A330–300,
A340–200, and A340–300 Series Airplanes
With THSAs Having Less Than 16,000 Total
Flight Cycles as of the Effective Date of This
AD
The requirements of this paragraph apply
to Airbus Model A330–200 Freighter, A330–
200, A330–300, A340–200, and A340–300
series airplanes having a THSA with a part
number specified in paragraph (g)(1) of this
AD that has accumulated less than 16,000
total flight cycles since first installation on an
airplane, or since the most recent NBB
replacement, whichever is later, as of the
effective date of this AD. Not later than the
date specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD, as applicable: For any THSA
having reached or exceeded on that date the
corresponding number of total flight cycles as
specified in paragraphs (i)(1), (i)(2), and (i)(3)
of this AD, as applicable, replace the THSA
with a serviceable unit, in accordance with
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the Accomplishment Instructions of Airbus
Service Bulletin A330–27–3199, dated July
15, 2014; or Airbus Service Bulletin A340–
27–4190, dated July 15, 2014; as applicable.
(1) As of 12 months after the effective date
of this AD: The THSA flight-cycle limit
(since first installation on an airplane, or
since last NBB replacement, whichever
occurs later) is 16,000 total flight cycles.
(2) As of July 31, 2017: The THSA flightcycle limit (since first installation on an
airplane, or since last NBB replacement,
whichever occurs later) is 14,000 total flight
cycles.
(3) As of July 31, 2018: The THSA flightcycle limit (since first installation on an
airplane, or since last NBB replacement,
whichever occurs later) is 12,000 total flight
cycles.
(j) THSA Replacement for Airbus Model
A340–500 and –600 Series Airplanes
For Airbus Model A340–500 and A340–
600 series airplanes having a THSA with a
part number specified in paragraph (g)(2) of
this AD: Not later than the date specified in
paragraphs (j)(1), (j)(2), (j)(3), and (j)(4) of this
AD, as applicable, for any THSA having
reached or exceeded on that date the
corresponding number of total flight cycles as
specified in paragraphs (j)(1), (j)(2), (j)(3), and
(j)(4) of this AD, as applicable, replace each
affected THSA with a serviceable THSA, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A340–
27–5062, dated July 15, 2014.
(1) As of the effective date of this AD: The
THSA flight-cycle limit (since first
installation on an airplane, or since last NBB
replacement, whichever occurs later) is 6,000
total flight cycles.
(2) As of April 30, 2017: The THSA flightcycle limit (since first installation on an
airplane, or since last NBB replacement,
whichever occurs later) is 5,200 total flight
cycles.
(3) As of April 30, 2018: The THSA flightcycle limit (since first installation on an
airplane, or since last NBB replacement,
whichever occurs later) is 4,400 total flight
cycles.
(4) As of April 30, 2019: The THSA flightcycle limit (since first installation on an
airplane, or since last NBB replacement,
whichever occurs later) is 3,500 total flight
cycles.
(k) THSA Replacement Intervals for All
Airbus Airplanes Identified in Paragraph (c)
of This AD
For any part installed, as required by this
AD, having a part number identified in
paragraph (g)(1) or (g)(2) of this AD: From the
dates specified in paragraphs (i) and (j) of
this AD, as applicable, and prior to exceeding
the accumulated number of total flight cycles
corresponding to each time, replace each
affected THSA with a serviceable part, in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraphs (k)(1),
(k)(2), and (k)(3) of this AD.
(1) Airbus Service Bulletin A330–27–3199,
dated July 15, 2014.
(2) Airbus Service Bulletin A340–27–4190,
dated July 15, 2014.
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31847
(3) Airbus Service Bulletin A340–27–5062,
dated July 15, 2014.
(l) Definition of Serviceable THSA
For the purposes of this AD, a serviceable
THSA is a THSA:
(1) Having a part number identified in
paragraph (g)(1) or (g)(2) of this AD that has
not exceeded any of the total accumulated
flight cycles identified in paragraphs (i)(1)
through (i)(3) of this AD, or paragraphs (j)(1)
through (j)(4) of this AD, as applicable; or
(2) Having a part number that is not
identified in paragraph (g)(1) or (g)(2) of this
AD.
(m) Parts Installation Limitation
From each date specified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD, and
paragraphs (j)(1) through (j)(4) of this AD, as
applicable, a THSA having a part number
identified in paragraph (g)(1) or (g)(2) of this
AD may be installed on any airplane,
provided the THSA has not exceeded the
corresponding number of accumulated total
flight cycles.
(n) 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 ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425-227-1149.
Information may be emailed to: 9-ANM-116AMOC-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. The AMOC approval letter
must specifically reference this AD.
(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
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): 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
E:\FR\FM\20MYR1.SGM
20MYR1
31848
Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations
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.
(o) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0257R1, dated
May 29, 2015, 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–
2014–0006.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-27–3199,
dated July 15, 2014.
(ii) Airbus Service Bulletin A340–27–4190,
dated July 15, 2014.
(iii) Airbus Service Bulletin A340–27–
5062, dated July 15, 2014.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 9,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–11575 Filed 5–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
mstockstill on DSK5VPTVN1PROD with RULES
14 CFR Part 39
[Docket No. FAA–2015–6548; Directorate
Identifier 2015–NM–114–AD; Amendment
39–18520; AD 2016–10–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Sep<11>2014
22:59 May 19, 2016
Jkt 238001
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8 and
787–9 airplanes equipped with General
Electric engines. This AD was prompted
by reports of cracking in barrel nuts on
a forward engine mount of Model 747–
8 airplanes, which shares a similar
design to the forward engine mount of
Model 787–8 and 787–9 airplanes. This
AD requires, for certain airplanes,
replacement of the four barrel nuts of
the forward engine mount on each
engine. For certain other airplanes, this
AD requires an inspection to determine
if any forward engine mount barrel nut
having a certain part number is
installed; and related investigative and
corrective actions if necessary. We are
issuing this AD to detect and correct
cracking of the forward engine mount
barrel nuts. Such cracking could result
in reduced load capacity of the forward
engine mount and could result in
separation of an engine from the
airplane and consequent loss of control
of the airplane.
DATES: This AD is effective June 24,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 24, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone: 206–544–5000,
extension 1; fax: 206–766–5680; Internet
https://www.myboeingfleet.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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
6548.
SUMMARY:
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–2015–
6548; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM–120S,
Seattle Aircraft Certification Office,
FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6487;
fax: 425–917–6590; email:
allen.rauschendorfer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 and 787–9 airplanes
equipped with General Electric engines.
The NPRM published in the Federal
Register on December 11, 2015 (80 FR
76878) (‘‘the NPRM’’). The NPRM was
prompted by reports of cracking in
barrel nuts on a forward engine mount
of Model 747–8 airplanes, which shares
a similar design to the forward engine
mount of Model 787–8 and 787–9
airplanes. The NPRM proposed to
require, for certain airplanes,
replacement of the four barrel nuts of
the forward engine mount on each
engine. For certain other airplanes, the
NPRM proposed to require an
inspection to determine if any forward
engine mount barrel nut having a
certain part number is installed; and
related investigative and corrective
actions if necessary. We are issuing this
AD to detect and correct cracking of the
forward engine mount barrel nuts. Such
cracking could result in reduced load
capacity of the forward engine mount
and could result in separation of an
engine from the airplane and
consequent loss of control of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response to the comment.
Request To Revise the Compliance
Time
United Airlines requested that the
compliance time in the NPRM for Group
1 airplanes be changed from 2 years to
‘‘at next engine change.’’ United
considered the proposed compliance
time to be ‘‘expedited’’ because it took
Boeing 7 months to publish the service
information operators would be
required to use to comply with the
requirements in the NPRM, and it took
E:\FR\FM\20MYR1.SGM
20MYR1
]]>Agencies
[Federal Register Volume 81, Number 98 (Friday, May 20, 2016)]
[Rules and Regulations]
[Pages 31844-31848]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11575]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0006; Directorate Identifier 2013-NM-147-AD;
Amendment 39-18519; AD 2016-10-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. This AD was prompted by
the results of endurance qualification tests on the trimmable
horizontal stabilizer actuator (THSA), which revealed a partial loss of
the no-back brake (NBB) efficiency in specific load conditions. This AD
requires inspecting certain THSAs to determine the number of total
flight cycles the THSA has accumulated, and replacing the THSA if
necessary. We are issuing this AD to detect and correct premature wear
of the carbon friction disks on the NBB of the THSA. Such a condition
could lead to reduced braking efficiency in certain load conditions
and, in conjunction with the inability of the power gear train to keep
the ball screw in its last commanded position, could result in
uncommanded movements of the trimmable horizontal stabilizer (THS) and
loss of control of the airplane.
DATES: This AD is effective June 24, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 24,
2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email airworthiness.A330-A340@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. It is also available on the Internet
[[Page 31845]]
at https://www.regulations.gov by searching for and locating Docket No.
FAA-2014-0006.
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-2014-
0006; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to all Airbus
Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-
500, and A340-600 series airplanes. The SNPRM published in the Federal
Register on December 23, 2015 (80 FR 79738) (``the SNPRM''). We
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on February 3, 2014 (79 FR 6104)
(``the NPRM''). The NPRM proposed to require inspecting certain THSAs
to determine the number of total flight cycles the THSA has
accumulated, and replacing the THSA if necessary. The NPRM was prompted
by the results of endurance qualification tests on the THSA, which
revealed a partial loss of the NBB efficiency in specific load
conditions. The SNPRM proposed to revise the NPRM by adding airplanes
to the proposed applicability, reducing the proposed compliance times
for replacing affected TSHAs, and revising the definition of a
serviceable THSA. We are issuing this AD to detect and correct
premature wear of the carbon friction disks on the NBB of the THSA.
Such a condition could lead to reduced braking efficiency in certain
load conditions and, in conjunction with the inability of the power
gear train to keep the ball screw in its last commanded position, could
result in uncommanded movements of the THS and loss of control of the
airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0257R1, dated May 29, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on all Airbus Model A330-
200, A330-200 Freighter, A330-300, A340-200, and A340-300 series
airplanes; and Model A340-500 and A340-600 series airplanes. The MCAI
states:
During endurance qualification tests on Trimmable Horizontal
Stabilizer Actuator (THSA) of another Airbus aeroplane type, a
partial loss of the no-back brake (NBB) efficiency was experienced.
Due to THSA design similarity on the A330/A340 fleet, a similar
partial loss of the NBB efficiency was identified on THSA Part
Number (P/N) 47147 as installed on A330-300 and A340-200/-300
aeroplanes, on THSA P/N 47172 as installed on A330-200/-300 and
A340-200/-300 aeroplanes, and on THSA P/N 47175 as installed on
A340-500/600 aeroplanes.
Investigation results concluded that this partial loss of
braking efficiency in some specific aerodynamic load conditions was
due to polishing and auto-contamination of the NBB carbon friction
disks.
This condition, if not detected and corrected and in conjunction
with the power gear train not able to keep the ball screw in its
last commanded position, could lead to uncommanded movements of the
THS, possibly resulting in loss of control of the aeroplane.
To address this potential unsafe condition, EASA issued AD 2013-
0144 [https://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] to require replacement of each THSA that has exceeded
16,000 flight cycles (FC) in service, to be sent in shop for NBB
carbon disk replacement.
Since that AD was issued, a need for clarification has been
demonstrated, regarding the identification of the THSA `affected' by
this requirement.
For this reason, EASA AD 2013-0144 [https://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] was revised, confirming
that this AD only affected those THSA identified by Part Number (P/
N) in Airbus Alert Operator Transmission (AOT) A27L005-13. In
addition, a note was added to make clear that the life limits as
specified in the current revision of ALS Part 4 are still relevant
for the affected THSA, as applicable to aeroplane model and THSA P/
N.
Since EASA AD 2013-0144R1 [https://ad.easa.europa.eu/ad/2013-0144R1] was issued, further assessment of the ageing/endurance issue
has resulted in the conclusion that there is a need to replace the
NBB installed on the THSA.
Consequently, EASA issued AD 2014-0257 [https://ad.easa.europa.eu/blob/EASA_AD_2014_0257_R1.pdf/AD_2014-0257R1_1]
which retained the requirements of EASA AD 2013-0144R1, which was
superseded, and required removal from service of affected THSA. THSA
should be sent in shop for NBB carbon disk replacement. This [EASA]
AD affected additional THSA P/Ns when compared to EASA AD 2013-
0144R1 and Airbus AOT A27L005-13.
Since that [EASA] AD was issued, it was determined that it is
necessary to consider that the THSA removal for NBB disks
replacement could also be calculated since last NBB disk replacement
which was done in-shop.
This AD also adds Model A340-541 and A340-642 airplanes to the
applicability. 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-2014-0006.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM or on the determination
of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information, all dated July
15, 2014.
Service Bulletin A330-27-3199 (for Model A330 series
airplanes);
Service Bulletin A340-27-4190 (for Model A340-200 and -300
series airplanes); and
Service Bulletin A340-27-5062 (for Model A340-500 and -600
series airplanes).
The service information describes procedures for inspecting the
THSA to determine the part number and replacing THSAs having certain
part numbers with a new or serviceable part. 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.
Costs of Compliance
We estimate that this AD affects 94 airplanes of U.S. registry.
[[Page 31846]]
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................... 3 work-hours x $85 per $0 $255 $23,970
hour = $255.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the required inspection.
We have no way of determining the number of airplanes that might need
these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement.................................. 23 work-hour x $85 per hour = $722,556 $724,511
$1,955.
----------------------------------------------------------------------------------------------------------------
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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2016-10-08 Airbus: Amendment 39-18519. Docket No. FAA-2014-0006;
Directorate Identifier 2013-NM-147-AD.
(a) Effective Date
This AD is effective June 24, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) through (c)(7) of this AD,
all manufacturer serial numbers.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(6) Model A340-541 airplanes.
(7) Model A340-642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by the results of endurance qualification
tests on the trimmable horizontal stabilizer actuator (THSA), which
revealed a partial loss of the no-back brake (NBB) efficiency in
specific load conditions. We are issuing this AD to detect and
correct premature wear of the carbon friction disks on the NBB of
the THSA. Such a condition could lead to reduced braking efficiency
in certain load conditions and, in conjunction with the inability of
the power gear train to keep the ball screw in its last commanded
position, could result in uncommanded movements of the trimmable
horizontal stabilizer and loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection To Determine THSA Part Number and Accumulated Total
Flight Cycles
Within 90 days after the effective date of this AD: Inspect the
THSA to determine if it has a part number that is specified in
paragraph (g)(1) or (g)(2) of this AD, and to determine the total
number of flight cycles accumulated since the THSA's first
installation on an airplane, or since the most recent NBB
replacement. A review of airplane delivery or maintenance records is
acceptable in lieu of this inspection if the part number of the THSA
can be conclusively determined from that review.
(1) For Model A330-200 Freighter, A330-200, A330-300, A340-200
and A340-300 series airplanes: Part number (P/N) 47147-500, 47147-
700, 47172-300, 47172-500, 47172-510, or 47172-520.
(2) For Model A340-500 and -600 series airplanes: P/N 47175-200,
47175-300, 47175-500, or 47175-520.
[[Page 31847]]
(h) THSA Replacement for Airbus Model A330-200 Freighter, A330-200,
A330-300, A340-200, and A340-300 Series Airplanes
For Airbus Model A330-200 Freighter, A330-200, A330-300, A340-
200, and A340-300 series airplanes having a THSA with a part number
specified in paragraph (g)(1) of this AD: At the applicable time
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, replace
each affected THSA with a serviceable THSA, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3199,
dated July 15, 2014; or Airbus Service Bulletin A340-27-4190, dated
July 15, 2014; as applicable.
Note 1 to paragraphs (h), (i), and (j) of this AD: The THSA
life limits specified in Part 4--Aging System Maintenance of the
Airbus A330 and A340 Airworthiness Limitations Sections are still
relevant, as applicable to airplane model and THSA part number.
(1) For a THSA that has accumulated or exceeded 20,000 total
flight cycles since the THSA's first installation on an airplane, or
since the most recent NBB replacement, whichever is later, as of the
effective date of this AD: Within 6 months after the effective date
of this AD.
(2) For a THSA that has accumulated or exceeded 16,000 total
flight cycles, but less than 20,000 total flight cycles since the
THSA's first installation on an airplane, or since the most recent
NBB replacement, whichever is later, as of the effective date of
this AD: At the applicable time specified in paragraphs (h)(2)(i)
and (h)(2)(ii) of this AD.
(i) For Model A330-200 Freighter, A330-200, and A330-300 series
airplanes: Within 12 months after the effective date of this AD but
without exceeding 20,000 total flight cycles.
(ii) For Model A340-200, and A340-300 series airplanes: Within
12 months after the effective date of this AD but without exceeding
20,000 total flight cycles.
(3) For a THSA that has accumulated less than 16,000 total
flight cycles since first installation on an airplane, or since the
most recent NBB replacement, whichever is later, as of the effective
date of this AD: At the applicable time specified in paragraph (i)
of this AD.
(i) Replacement Times for Airbus Model A330-200 Freighter, A330-200,
A330-300, A340-200, and A340-300 Series Airplanes With THSAs Having
Less Than 16,000 Total Flight Cycles as of the Effective Date of This
AD
The requirements of this paragraph apply to Airbus Model A330-
200 Freighter, A330-200, A330-300, A340-200, and A340-300 series
airplanes having a THSA with a part number specified in paragraph
(g)(1) of this AD that has accumulated less than 16,000 total flight
cycles since first installation on an airplane, or since the most
recent NBB replacement, whichever is later, as of the effective date
of this AD. Not later than the date specified in paragraphs (i)(1),
(i)(2), and (i)(3) of this AD, as applicable: For any THSA having
reached or exceeded on that date the corresponding number of total
flight cycles as specified in paragraphs (i)(1), (i)(2), and (i)(3)
of this AD, as applicable, replace the THSA with a serviceable unit,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3199, dated July 15, 2014; or Airbus Service
Bulletin A340-27-4190, dated July 15, 2014; as applicable.
(1) As of 12 months after the effective date of this AD: The
THSA flight-cycle limit (since first installation on an airplane, or
since last NBB replacement, whichever occurs later) is 16,000 total
flight cycles.
(2) As of July 31, 2017: The THSA flight-cycle limit (since
first installation on an airplane, or since last NBB replacement,
whichever occurs later) is 14,000 total flight cycles.
(3) As of July 31, 2018: The THSA flight-cycle limit (since
first installation on an airplane, or since last NBB replacement,
whichever occurs later) is 12,000 total flight cycles.
(j) THSA Replacement for Airbus Model A340-500 and -600 Series
Airplanes
For Airbus Model A340-500 and A340-600 series airplanes having a
THSA with a part number specified in paragraph (g)(2) of this AD:
Not later than the date specified in paragraphs (j)(1), (j)(2),
(j)(3), and (j)(4) of this AD, as applicable, for any THSA having
reached or exceeded on that date the corresponding number of total
flight cycles as specified in paragraphs (j)(1), (j)(2), (j)(3), and
(j)(4) of this AD, as applicable, replace each affected THSA with a
serviceable THSA, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A340-27-5062, dated July 15, 2014.
(1) As of the effective date of this AD: The THSA flight-cycle
limit (since first installation on an airplane, or since last NBB
replacement, whichever occurs later) is 6,000 total flight cycles.
(2) As of April 30, 2017: The THSA flight-cycle limit (since
first installation on an airplane, or since last NBB replacement,
whichever occurs later) is 5,200 total flight cycles.
(3) As of April 30, 2018: The THSA flight-cycle limit (since
first installation on an airplane, or since last NBB replacement,
whichever occurs later) is 4,400 total flight cycles.
(4) As of April 30, 2019: The THSA flight-cycle limit (since
first installation on an airplane, or since last NBB replacement,
whichever occurs later) is 3,500 total flight cycles.
(k) THSA Replacement Intervals for All Airbus Airplanes Identified in
Paragraph (c) of This AD
For any part installed, as required by this AD, having a part
number identified in paragraph (g)(1) or (g)(2) of this AD: From the
dates specified in paragraphs (i) and (j) of this AD, as applicable,
and prior to exceeding the accumulated number of total flight cycles
corresponding to each time, replace each affected THSA with a
serviceable part, in accordance with the Accomplishment Instructions
of the applicable service information identified in paragraphs
(k)(1), (k)(2), and (k)(3) of this AD.
(1) Airbus Service Bulletin A330-27-3199, dated July 15, 2014.
(2) Airbus Service Bulletin A340-27-4190, dated July 15, 2014.
(3) Airbus Service Bulletin A340-27-5062, dated July 15, 2014.
(l) Definition of Serviceable THSA
For the purposes of this AD, a serviceable THSA is a THSA:
(1) Having a part number identified in paragraph (g)(1) or
(g)(2) of this AD that has not exceeded any of the total accumulated
flight cycles identified in paragraphs (i)(1) through (i)(3) of this
AD, or paragraphs (j)(1) through (j)(4) of this AD, as applicable;
or
(2) Having a part number that is not identified in paragraph
(g)(1) or (g)(2) of this AD.
(m) Parts Installation Limitation
From each date specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD, and paragraphs (j)(1) through (j)(4) of this AD,
as applicable, a THSA having a part number identified in paragraph
(g)(1) or (g)(2) of this AD may be installed on any airplane,
provided the THSA has not exceeded the corresponding number of
accumulated total flight cycles.
(n) 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 ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. 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. The
AMOC approval letter must specifically reference this AD.
(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 the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Required for Compliance (RC): 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
[[Page 31848]]
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.
(o) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2014-0257R1, dated May 29, 2015, 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-2014-0006.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-27-3199, dated July 15, 2014.
(ii) Airbus Service Bulletin A340-27-4190, dated July 15, 2014.
(iii) Airbus Service Bulletin A340-27-5062, dated July 15, 2014.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-11575 Filed 5-19-16; 8:45 am]
BILLING CODE 4910-13-P
