Airworthiness Directives; Airbus Airplanes, 29795-29798 [2017-13780]
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Federal Register / Vol. 82, No. 125 / Friday, June 30, 2017 / Proposed Rules
in the modified chord, in accordance with
Part 8 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1166,
Revision 2, dated May 25, 2006. If any crack
is found, before further flight, repair in
accordance with Part 3 or Part 4, as
applicable, of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006; except, if the repairs cannot be
installed using the identified procedures,
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (l) of this AD.
(j) Follow-On Inspection for Interim
Modification and Repair
For airplanes having line numbers 1
through 3132 inclusive, on which an interim
modification of the BS 727 outboard chord as
defined in Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006, has been accomplished: Within 60,000
flight cycles after accomplishment of the
interim modification of the outboard chord of
the frame at BS 727 at S–18A, but no earlier
than 50,000 flight cycles after
accomplishment of the modification, do a
one-time follow-on open-hole eddy current
inspection to detect cracks in the modified
chord, in accordance with Part 8 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1166, Revision 2,
dated May 25, 2006. If any crack is found
during the inspection required by this
paragraph, before further flight, repair in
accordance with Part 3 or Part 4, as
applicable, of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006; except, where the repairs cannot be
installed using the procedures identified in
this service bulletin, repair before further
flight using a method approved in
accordance with the procedures specified in
paragraph (l) of this AD.
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(k) Exception to the Service Information
Access and restoration procedures
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1166, Revision 2, dated May 25,
2006, are not required by this AD. Operators
may do those actions following their
approved maintenance procedures.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
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(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(m) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6450; fax: (425) 917–
6590; email: alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; 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.
Issued in Renton, Washington, on June 22,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13773 Filed 6–29–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0627; Directorate
Identifier 2017–NM–037–AD]
RIN 2120–AA64
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 A330–200 Freighter,
–200, and –300 series airplanes; and
Airbus Model A340–200, –300, –500,
and –600 series airplanes. This
proposed AD was prompted by a report
that the trimmable horizontal stabilizer
actuator (THSA) might not function as
intended after failure of the primary
load path. This proposed AD would
require repetitive detailed visual
inspections for discrepancies of the
SUMMARY:
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29795
THSA upper attachments and no-back
housing. 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 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.
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–
0627; 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:
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
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to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0627; Directorate Identifier
2017–NM–037–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.
without stalling [i.e., the THSA might not
function as intended after failure of the
primary load path]. The partial engagement
of the SLP at upper attachment level does not
trigger any indication to the flight crew.
This condition, if not detected and
corrected, could lead to THSA upper
attachment failure and consequent
disconnection of the THSA from the
aeroplane structure, possibly resulting in loss
of control of the aeroplane.
For the reasons described above, this
[EASA] AD requires repetitive detailed
[visual] inspections (DET) of the upper THSA
attachments parts and the PLP and SLP
fuselage attachment points, and, depending
on findings (which include, but are not
limited to, failure of the primary load path),
accomplishment of applicable [additional
inspections for discrepancies and] corrective
action(s).
Discussion
The additional inspections include a
detailed visual inspection for
discrepancies of the upper attachment
fitting of the airplane and a detailed
visual inspection for discrepancies of
the removed THSA. Corrective actions
include repair and replacement of the
THSA. 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–
0627.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0044, dated March 9,
2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200 Freighter, –200 and
–300 series airplanes; and Airbus Model
A340–200, –300, –500, and –600 series
airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer
Actuator (THSA), as installed on A330 and
A340 aeroplanes, was initially designed to
stall when engaging on the upper secondary
load path (SLP) after primary load path (PLP)
failure. Such stall triggers system monitoring
detection. New mission profile analysis
revealed that in some cases, the THSA could
be operated while engaged on the upper SLP
Related Service Information Under 1
CFR Part 51
We reviewed the following Airbus
service information:
• Airbus Service Bulletin A330–27–
3218, Revision 01, dated December 5,
2016.
• Airbus Service Bulletin A340–27–
4203, Revision 01 dated December 5,
2016.
• Airbus Service Bulletin A340–27–
5067, Revision 01 dated December 5,
2016.
The service information describes
procedures for detailed visual
inspections for discrepancies of the
THSA upper attachments and no-back
housing, additional inspections for
discrepancies, and corrective actions.
These documents are distinct since they
apply to different airplane models. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 102 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ..........................
3 work-hours × $85 per hour = $255 per inspection
cycle.
We estimate the following costs to do
any necessary replacements that would
Parts cost
Cost per product
$0
be required based on the results of the
proposed inspection. We have no way of
$255 per inspection cycle
Cost on U.S.
operators
$26,010
determining the number of aircraft that
might need this replacement.
ON-CONDITION COSTS
Labor cost
Replacement ....................................
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Action
20 work-hours × $85 per hour = $1,700 ...................................................
We have received no definitive data
that would enable us to provide cost
estimates for other on-condition actions
specified in this proposed AD.
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Parts cost
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:
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$734,661
Cost per
product
$736,361
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
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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
failure of the primary load path. We are
issuing this AD to detect and correct
discrepancies of the THSA upper
attachments and no-back housing, which
could lead to THSA upper attachment failure
and consequent disconnection of the THSA
from the airplane structure, possibly
resulting in loss of control of the airplane.
(f) Compliance
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
29797
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Detailed Visual Inspections
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2017–0627;
Directorate Identifier 2017–NM–037–AD.
(a) Comments Due Date
We must receive comments by August 14,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –223, –223F, –243, –243F,
–301, –302, –303, –321, –322, –323, –341,
–342 and –343 airplanes; and Airbus Model
A340–211, –212, –213, –311, –312, –313,
–541, and –642 airplanes; certificated in any
category, all manufacturer’s serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by a report that the
trimmable horizontal stabilizer actuator
(THSA) might not function as intended after
Before exceeding the Threshold in Table 1
to paragraph (g) of this AD, as applicable, or
within 3 months after the effective date of
this AD, whichever occurs later; and
thereafter at intervals not to exceed the
inspection interval values defined in Table 1
to paragraph (g) of this AD; accomplish a
detailed visual inspection for discrepancies
of the trimmable horizontal stabilizer
actuator (THSA) upper attachments and noback housing, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable. Where the ‘‘Threshold’’
column of table 1 to paragraph (g) of this AD
specifies compliance times in ‘‘FH’’ (flight
hours) or ‘‘FC’’ (flight cycles), those
compliance times are flight hours or flight
cycles since the first flight of the airplane, or
since the last accomplishment of Airbus
Model A330 or A340 Maintenance Review
Board Report task 27.40.00/07, or since the
last detailed visual inspection of the THSA
done in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, A340–27–
4203, or A340–27–5067, all dated July 1,
2016, as applicable.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—THSA UPPER ATTACHMENTS/NO-BACK HOUSING INSPECTIONS
Compliance times
(whichever occurs first, flight hours (FH) or
flight cycles (FC))
Affected airplanes
Inspection interval
(not to exceed)
Threshold
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A330, A340–200 and A340–300 ........................
A340–500 and A340–600 ..................................
(h) Additional Inspections and Corrective
Actions
(1) If, during any inspection required by
paragraph (g) of this AD, any discrepancy
identified in the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3218, Revision 01, A340–27–4203,
Revision 01, or A340–27–5067, Revision 01,
all dated December 5, 2016, as applicable, is
detected, before further flight, remove the
THSA, and accomplish a detailed visual
inspection for discrepancies of the upper
attachment fitting of the airplane and a
detailed visual inspection for discrepancies
of the removed THSA, in accordance with
the Accomplishment Instructions of Airbus
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Before 4,000 FH or 1,000 FC ..........................
Before 4,000 FH or 800 FC .............................
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable. As an alternative to the
removed THSA inspections required by this
paragraph, before further flight, replace the
THSA with a serviceable part (as defined in
paragraph (i) of this AD).
(2) If, during any inspection of the upper
attachment fitting of the airplane required by
paragraph (h)(1) of this AD, any discrepancy
identified in the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3218, Revision 01, A340–27–4203,
Revision 01, or A340–27–5067, Revision 01,
all dated December 5, 2016, as applicable, is
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4,000 FH or 1,000 FC.
4,000 FH or 800 FC.
detected, before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (k)(2) of
this AD.
(3) If, during any inspection of the removed
THSA required by paragraph (h)(1) of this
AD, no discrepancy specified in the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable, is detected, before
further flight, reinstall the THSA, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3218, Revision 01, A340–27–4203,
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Revision 01, or A340–27–5067, Revision 01,
all dated December 5, 2016, as applicable.
(4) If, during any inspection of the removed
THSA required by paragraph (h)(1) of this
AD, any discrepancy specified in the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable, is detected, before
further flight, replace the THSA with a
serviceable part (as defined in paragraph (i)
of this AD), in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable.
(i) Definition of Serviceable THSA
For the purpose of this AD, a serviceable
THSA is a part that has accumulated less
than 4,000 FH or 1,000 FC (for Airbus Model
A330, A340–200, or A340–300 airplanes) or
4,000 FH or 800 FC (for Airbus Model A340–
500 or A340–600 airplanes), whichever
occurs first since the first flight of the
airplane, or since the last overhaul of the
THSA, or since the last detailed visual
inspection of the THSA in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A330–27–3218, Revision 01,
A340–27–4203, Revision 01, or A340–27–
5067, Revision 01, all dated December 5,
2016, as applicable.
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(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g), (h)(1), (h)(3), and
(h)(4) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Airbus Service Bulletin A330–27–3218,
Revision 00, dated July 1, 2016.
(2) Airbus Service Bulletin A340–27–4203,
Revision 00, dated July 1, 2016.
(3) Airbus Service Bulletin A340–27–5067,
Revision 00, dated July, 1 2016.
(k) 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 manager of the International Branch,
send it to attention of the person identified
in paragraph (l)(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
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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): Except
as required by paragraph (h)(2) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–044, dated March 9, 2017, 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–2017–0627.
(2) For more information about this AD,
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.
(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. 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 22,
2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–13780 Filed 6–29–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 417
Waiver of Flight Termination Receiver
Qualification by Similarity Deficiencies
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of waiver.
AGENCY:
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This notice concerns three
petitions for waiver submitted to the
FAA by Rocket Lab USA Inc. (RL) for
the Flight Termination Receiver (FTR)
Qualification by Similarity (QBS): A
petition to waive the requirement that a
component may be qualified based on
similarity to a component that has
already been qualified for use only if the
environments encountered by the
previously qualified component during
its qualification or flight history were
equal or more severe than the Rocket
Lab qualification environments; a
petition to waive the Electromagnetic
Interference and Compatibility (EMI/
EMC) on the same units; and a petition
to waive the requirement that the same
manufacturer must produce the
qualified and the unqualified
component in the same location using
identical tools and manufacturing
processes. The FAA grants these three
petitions.
DATES: Issued in Washington, DC, on
May 15, 2017.
FOR FURTHER INFORMATION CONTACT: For
technical questions concerning this
waiver, contact Michael Wiktowy,
Licensing Program Lead, Commercial
Space Transportation—Licensing and
Evaluation Division, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–7287; email:
Michael.Wiktowy@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Background
RL submitted a petition to the FAA’s
Office of Commercial Space
Transportation (AST) requesting relief
from regulatory requirements for a
launch license for flight of Electron test
flight missions from Mahia, New
Zealand. Specifically, RL requested
relief from 14 CFR E417.7(f)(2) and (5),
Qualification Testing and Analysis by
Similarity for the Flight Termination
Receiver. For Qualification, the Flight
Termination Receiver is required to
meet Table E417.19–2, which states
with note (5): ‘‘The same three sample
components must undergo each test
designated with an X. For a test
designated with a quantity of less than
three, each sample component tested
must be one of the original three sample
components.’’ For Qualification Testing
and Analysis by Similarity, Part 417
Appendix E section 417.7(f) provides
the requirements a launch operator must
satisfy in order to qualify or re-qualify
a flight termination system component’s
design through qualification by
similarity to tests performed on
identical or similar hardware. Section
E417.7(f)(2) states that to qualify
component ‘‘A’’ based on similarity to
E:\FR\FM\30JNP1.SGM
30JNP1
]]>Agencies
[Federal Register Volume 82, Number 125 (Friday, June 30, 2017)]
[Proposed Rules]
[Pages 29795-29798]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13780]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0627; Directorate Identifier 2017-NM-037-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 A330-200 Freighter, -200, and -300 series airplanes; and
Airbus Model A340-200, -300, -500, and -600 series airplanes. This
proposed AD was prompted by a report that the trimmable horizontal
stabilizer actuator (THSA) might not function as intended after failure
of the primary load path. This proposed AD would require repetitive
detailed visual inspections for discrepancies of the THSA upper
attachments and no-back housing. 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
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.
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-
0627; 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: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments
[[Page 29796]]
to an address listed under the ADDRESSES section. Include ``Docket No.
FAA-2017-0627; Directorate Identifier 2017-NM-037-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 2017-0044, dated March 9, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, -200 and -300 series airplanes; and Airbus Model
A340-200, -300, -500, and -600 series airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer Actuator (THSA), as
installed on A330 and A340 aeroplanes, was initially designed to
stall when engaging on the upper secondary load path (SLP) after
primary load path (PLP) failure. Such stall triggers system
monitoring detection. New mission profile analysis revealed that in
some cases, the THSA could be operated while engaged on the upper
SLP without stalling [i.e., the THSA might not function as intended
after failure of the primary load path]. The partial engagement of
the SLP at upper attachment level does not trigger any indication to
the flight crew.
This condition, if not detected and corrected, could lead to
THSA upper attachment failure and consequent disconnection of the
THSA from the aeroplane structure, possibly resulting in loss of
control of the aeroplane.
For the reasons described above, this [EASA] AD requires
repetitive detailed [visual] inspections (DET) of the upper THSA
attachments parts and the PLP and SLP fuselage attachment points,
and, depending on findings (which include, but are not limited to,
failure of the primary load path), accomplishment of applicable
[additional inspections for discrepancies and] corrective action(s).
The additional inspections include a detailed visual inspection for
discrepancies of the upper attachment fitting of the airplane and a
detailed visual inspection for discrepancies of the removed THSA.
Corrective actions include repair and replacement of the THSA. 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-
0627.
Related Service Information Under 1 CFR Part 51
We reviewed the following Airbus service information:
Airbus Service Bulletin A330-27-3218, Revision 01, dated
December 5, 2016.
Airbus Service Bulletin A340-27-4203, Revision 01 dated
December 5, 2016.
Airbus Service Bulletin A340-27-5067, Revision 01 dated
December 5, 2016.
The service information describes procedures for detailed visual
inspections for discrepancies of the THSA upper attachments and no-back
housing, additional inspections for discrepancies, and corrective
actions. These documents are distinct since they apply to different
airplane models. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 102 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection....................... 3 work-hours x $85 per $0 $255 per inspection $26,010
hour = $255 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
this replacement.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................ 20 work-hours x $85 per hour = $734,661 $736,361
$1,700.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for other on-condition actions specified in this
proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that
[[Page 29797]]
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-2017-0627; Directorate Identifier 2017-NM-
037-AD.
(a) Comments Due Date
We must receive comments by August 14, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342
and -343 airplanes; and Airbus Model A340-211, -212, -213, -311, -
312, -313, -541, and -642 airplanes; certificated in any category,
all manufacturer's serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a report that the trimmable horizontal
stabilizer actuator (THSA) might not function as intended after
failure of the primary load path. We are issuing this AD to detect
and correct discrepancies of the THSA upper attachments and no-back
housing, which could lead to THSA upper attachment failure and
consequent disconnection of the THSA from the airplane structure,
possibly resulting in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Detailed Visual Inspections
Before exceeding the Threshold in Table 1 to paragraph (g) of
this AD, as applicable, or within 3 months after the effective date
of this AD, whichever occurs later; and thereafter at intervals not
to exceed the inspection interval values defined in Table 1 to
paragraph (g) of this AD; accomplish a detailed visual inspection
for discrepancies of the trimmable horizontal stabilizer actuator
(THSA) upper attachments and no-back housing, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable. Where the
``Threshold'' column of table 1 to paragraph (g) of this AD
specifies compliance times in ``FH'' (flight hours) or ``FC''
(flight cycles), those compliance times are flight hours or flight
cycles since the first flight of the airplane, or since the last
accomplishment of Airbus Model A330 or A340 Maintenance Review Board
Report task 27.40.00/07, or since the last detailed visual
inspection of the THSA done in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3218, A340-27-4203,
or A340-27-5067, all dated July 1, 2016, as applicable.
Table 1 to Paragraph (g) of This AD--THSA Upper Attachments/No-Back
Housing Inspections
------------------------------------------------------------------------
Compliance times (whichever occurs first,
flight hours (FH) or flight cycles (FC))
Affected airplanes -------------------------------------------
Inspection interval
Threshold (not to exceed)
------------------------------------------------------------------------
A330, A340-200 and A340-300. Before 4,000 FH or 4,000 FH or 1,000
1,000 FC. FC.
A340-500 and A340-600....... Before 4,000 FH or 4,000 FH or 800 FC.
800 FC.
------------------------------------------------------------------------
(h) Additional Inspections and Corrective Actions
(1) If, during any inspection required by paragraph (g) of this
AD, any discrepancy identified in the Accomplishment Instructions of
Airbus Service Bulletin A330-27-3218, Revision 01, A340-27-4203,
Revision 01, or A340-27-5067, Revision 01, all dated December 5,
2016, as applicable, is detected, before further flight, remove the
THSA, and accomplish a detailed visual inspection for discrepancies
of the upper attachment fitting of the airplane and a detailed
visual inspection for discrepancies of the removed THSA, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision 01, or
A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable. As an alternative to the removed THSA inspections
required by this paragraph, before further flight, replace the THSA
with a serviceable part (as defined in paragraph (i) of this AD).
(2) If, during any inspection of the upper attachment fitting of
the airplane required by paragraph (h)(1) of this AD, any
discrepancy identified in the Accomplishment Instructions of Airbus
Service Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision
01, or A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable, is detected, before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (k)(2) of this AD.
(3) If, during any inspection of the removed THSA required by
paragraph (h)(1) of this AD, no discrepancy specified in the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable, is detected, before
further flight, reinstall the THSA, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203,
[[Page 29798]]
Revision 01, or A340-27-5067, Revision 01, all dated December 5,
2016, as applicable.
(4) If, during any inspection of the removed THSA required by
paragraph (h)(1) of this AD, any discrepancy specified in the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable, is detected, before
further flight, replace the THSA with a serviceable part (as defined
in paragraph (i) of this AD), in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3218, Revision 01,
A340-27-4203, Revision 01, or A340-27-5067, Revision 01, all dated
December 5, 2016, as applicable.
(i) Definition of Serviceable THSA
For the purpose of this AD, a serviceable THSA is a part that
has accumulated less than 4,000 FH or 1,000 FC (for Airbus Model
A330, A340-200, or A340-300 airplanes) or 4,000 FH or 800 FC (for
Airbus Model A340-500 or A340-600 airplanes), whichever occurs first
since the first flight of the airplane, or since the last overhaul
of the THSA, or since the last detailed visual inspection of the
THSA in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision
01, or A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g), (h)(1), (h)(3), and (h)(4) of this AD, if those
actions were performed before the effective date of this AD using
the service information specified in paragraph (j)(1), (j)(2), or
(j)(3) of this AD.
(1) Airbus Service Bulletin A330-27-3218, Revision 00, dated
July 1, 2016.
(2) Airbus Service Bulletin A340-27-4203, Revision 00, dated
July 1, 2016.
(3) Airbus Service Bulletin A340-27-5067, Revision 00, dated
July, 1 2016.
(k) 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 manager of the International Branch, send it to
attention of the person identified in paragraph (l)(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 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): Except as required by
paragraph (h)(2) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-044, dated March 9, 2017, 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-2017-0627.
(2) For more information about this AD, 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.
(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. 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 22, 2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13780 Filed 6-29-17; 8:45 am]
BILLING CODE 4910-13-P
