Airworthiness Directives; Dassault Aviation Airplanes, 40065-40069 [2013-15949]
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Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules
(a) Applicability
This AD applies to Erickson Air-Crane
Incorporated (Erickson) Model S–64E and S–
64F helicopters, with rotary wing blade
assembly (main rotor blade), part number (P/
N) 6415–20201–043, –045, –047, –048, –049,
–050, or –051; or 6415–20601–041, –042,
–043, –044, –045, –046, –047, –048, –049,
–050, –051, or –052, installed, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the main rotor blade (blade), which
could result in blade separation and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 90–26–12, Docket
No. 90–ASW–27, Amendment 39–6841 (55
FR 51406, December 14, 1990).
(d) Comments Due Date
We must receive comments by September
3, 2013.
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(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Before further flight, visually check the
Blade Inspection Method (BIM) pressure
indicators of the main rotor blades for a black
or red color indication.
(2) Before further flight, replace any blade
with a black or red color indication in a BIM
pressure indicator with an airworthy part of
the same part number unless the black or red
color indication is determined to be the
result of BIM system malfunction.
Note 1 to paragraph (f)(2) of this AD:
Paragraphs (f)(4)(i–iv) of this AD specify how
to determine if a BIM system is functioning
correctly.
(3) Repeat the visual BIM pressure
indicator check required by paragraph (f)(1)
of this AD prior to the first flight of each day
and thereafter at intervals not to exceed:
(i) Three hours time-in-service (TIS) from
the last check for helicopters engaged in
seven or more external lifts per hour; or
(ii) Five hours TIS from the last check for
helicopters engaged in either less than seven
external lifts per hour or operation without
external cargo.
(4) Prior to the first flight of each day,
check the BIM pressure indicator for proper
function as follows:
(i) Press in and hold the manual test lever
(grenade-type handle) on the raised area of
the handle over the pin-type actuation
plunger. Do not handle the indicator glass
bulb since the heat of the hand may change
the internal reference pressure and result in
an erroneous indicator reading.
(ii) Depress the actuation plunger fully to
shut off the pressure completely from the
blade into the indicator. If necessary, press
with the thumbs of both hands to overcome
the plunger spring force.
Note 2 to paragraph (f)(4)(ii) of this AD: If
pressure is applied to the end of the lever on
the flat area, the actuation plunger will not
fully depress.
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(iii) Verify proper operation of the
indicator by observing that a full-black or
full-red (unsafe) indication appears in not
less than 10 or more than 30 seconds after
depressing the plunger for a temperature of
20 degrees F (¥6.7 degrees C) or above. At
lower temperatures, extend the upper limit to
the corresponding time as follows:
(A) 19 to 0 degrees F (¥7.2 to ¥17.8
degrees C); upper limit of 35 seconds.
(B) ¥1 to ¥20 degrees F (¥18.3 to ¥28.9
degrees C); upper limit of 40 seconds.
(C) ¥21 to ¥40 degrees F (¥29.4 to ¥40.0
degrees C); upper limit of 50 seconds.
(D) ¥41 to ¥60 degrees F (¥40.5 to ¥51.1
degrees C); upper limit of 60 seconds.
(iv) Release the lever and observe that the
black or red indication snaps back
immediately, leaving an all-white or allyellow (safe) indication.
(v) If the indicator does not meet the
specified requirements, then either identify
and correct the BIM indicator malfunction or
replace the suspect main rotor blade with an
airworthy blade of the same part number
prior to further flight.
(5) The checks required by paragraphs
(f)(1) and (f)(4)(i–iv) of this AD may be
performed by the owner/operator (pilot)
holding at least a private pilot certificate, and
must be entered into the aircraft records
showing compliance with this AD in
accordance with 14 CFR 43.9 (a)(1)–(4) and
14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439.
(g) Special Flight Permit
Special flight permits will not be issued.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: JC Lin, Aviation
Safety Engineer, Rotorcraft Certification
Office, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137;
telephone (817) 222–5170; email 7-AVSASW-170@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
Erickson Air-Crane Incorporated Service
Bulletins No. 64B15–4D, Revision D, dated
January 26, 2001 for the Model S–64E and
No. 64F15–2, Revision A, dated July 14, 1999
for the Model S–64F, which are not
incorporated by reference, contain additional
information about the subject of this AD. For
service information, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/
Compliance Officer, 3100 Willow Springs Rd,
PO Box 3247, Central Point, OR 97502;
telephone (541) 664–5544; fax (541) 664–
2312; email cerickson@ericksonaircrane.com.
You may review a copy of this information
at the FAA, Office of the Regional Counsel,
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Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on June 18,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–15954 Filed 7–2–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0464; Directorate
Identifier 2012–NM–010–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all Dassault Aviation
Model FALCON 7X airplanes. The
existing AD currently requires adding
an automatic reversion logic and a
means for the pilot to override pitch
trim control normal modes, and
installing placards in the cockpit;
replacing the frame of the emergency
switch box; replacing certain horizontal
stabilizer electronic control units
(HSECU); operating the airplane
according to the limitations and
procedures in the airplane flight manual
(AFM); revising the Limitations section
of the AFM; and revising the
maintenance program to incorporate a
certain maintenance planning document
(MPD) task. Since we issued that AD,
Dassault Aviation has developed a
modification of the fly-by-wire (FBW)
standard; changed the AFM to
incorporate changes resulting from the
FBW modification; and revised the
airplane maintenance manual (AMM) to
incorporate repetitive operational tests
of the electric motors reversion relays
and trim emergency command of the
horizontal stabilizer trim system
(HSTS). Once incorporated, these
actions allow restoration of the
originally certified minimum equipment
list items. This proposed AD would
retain certain requirements of the
previous AD; would require modifying
the FBW standard; operating the
SUMMARY:
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Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules
airplane according to the limitations
and procedures in an approved AFM;
and operational testing of the electric
motors reversion relays and trim
emergency command of the HSTS, and
repairs if necessary. We are proposing
this AD to prevent an uncontrolled
pitch trim runaway, which could result
in loss of control of the airplane.
DATES: We must receive comments on
this proposed AD by August 19, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Dassault
Falcon Jet, P.O. Box 2000, South
Hackensack, New Jersey 07606;
telephone 201–440–6700; Internet
https://www.dassaultfalcon.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0464; Directorate Identifier
2012–NM–010–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
On July 15, 2011, we issued AD 2011–
16–01, Amendment 39–16759 (76 FR
47424, August 5, 2011). That AD
requires actions intended to address an
unsafe condition on all Dassault
Aviation Model FALCON 7X airplanes.
Since we issued AD 2011–16–01,
Amendment 39–16759 (76 FR 47424,
August 5, 2011), the European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community, has issued
EASA Airworthiness Directive 2011–
0241, dated December 19, 2011 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
In May 2011, a Dassault Aviation Falcon
7X aeroplane experienced an uncontrolled
pitch trim runaway during descent. The crew
succeeded in recovering a stable situation
and performed an uneventful landing.
The results of the investigations showed
that there was a production defect in the
Horizontal Stabilizer Electronic Control Unit
(HSECU) which could have contributed to
the cause of the event.
This condition, if not corrected, could lead
to a loss of control of the aeroplane.
To address this unsafe condition, EASA
issued emergency AD 2011–0102–E which
prohibited further flights. Following further
technical investigations accomplished by
Dassault Aviation, EASA issued AD 2011–
0114, currently at revision 2, which
superseded EASA AD 2011–0102–E.
Following accomplishment of all the actions
as required by EASA AD 2011–0114R2, all
aeroplanes could resume flying with
operational limitations.
Since EASA AD 2011–0114R2 was issued,
Dassault Aviation have developed a
modification (M1245 to be embodied through
accomplishment of Dassault Aviation Service
Bulletin F7X–214) of the Fly-By-Wire (FBW)
current standard which improves the
monitoring and reversion logic of the
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Horizontal Stabilizer Trim System (HSTS).
This modification results in earlier failure
detection and quicker reversion.
Dassault Aviation have issued as well
Revision 13 of the Aircraft Flight Manual
(AFM) which incorporates the changes
introduced in EASA AD 2011–0114R2 (CP55
and 56) as well as the new changes resulting
from Dassault Aviation M1245 (CP58).
Dassault Aviation have introduced as well
operational tests of the HSTS electric motors
reversion relays and of the HSTS trim
emergency command into the Chapter 5.40 of
F7X Aircraft Maintenance Manual (CP010).
For the reasons described above, EASA
issued AD 2011–0169 to require:
1. accomplishing Dassault Aviation
modification M1245,
2. amending the AFM, and
3. implementing the operational tests of the
HSTS electric motors reversion relays and of
the HSTS trim emergency command.
Accomplishment of all the above actions
restored the full original certified flight
envelope of the aeroplane.
Since EASA AD 2011–0169 was issued,
further analyses have demonstrated that,
once Dassault Aviation modification M1245
is embodied, it is allowed to restore the
originally certified Minimum Equipment List
(MEL) items which were removed in
accordance with the requirement of
paragraph (4) of EASA AD 2011–0114R2.
For the reasons described above, this
[EASA] AD, which supersedes EASA AD
2011–0169, retaining its requirements, in
addition, extends the applicability of the AD
to all S/Ns and, for aeroplanes fitted with
FBW standard 2.1.7.3, allows the MEL
limitations imposed by EASA AD 2011–
0114R2 to be removed.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Dassault has issued the following
service information.
• Dassault Mandatory Service
Bulletin 7X–214, including New
Standard Installation Checklist, dated
August 30, 2011.
• Dassault Mandatory Service
Bulletin 7X–214, Revision Erratum,
dated January 26, 2012.
• Dassault Falcon 7X AFM, Revision
13, dated August 29, 2011.
• FCS Data Loading Procedure,
Reference DT EQUIP 43913, Issue D,
dated May 28, 2010.
• Chapter 5–40–00, Airworthiness
Limitations, of the Falcon 7X
Maintenance Manual DGT 107838,
Revision 2, dated August 25, 2011. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
Explanation of Changes Made to This
NPRM
We have revised the heading and
wording for paragraph (h) of this
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proposed AD; this change does not
affect the intent of that paragraph.
We have deleted note 2 to paragraph
(l) of AD 2011–16–01, Amendment 39–
16759 (76 FR 47424, August 5, 2011).
Instead, we have included that
information in paragraph (l)(2) of this
proposed AD.
We have deleted note 3 of AD 2011–
16–01, Amendment 39–16759 (76 FR
47424, August 5, 2011). Instead, we
have included that information in
paragraph (n) of this proposed AD.
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FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
This AD requires revisions to certain
operator maintenance documents to
include new inspections. Compliance
with these inspections is required by 14
CFR 91.403(c). For airplanes that have
been previously modified, altered, or
repaired in the areas addressed by these
inspections, the operator may not be
able to accomplish the inspections
described in the revisions. In this
situation, to comply with 14 CFR
91.403(c), the operator must request
approval for an alternative method of
compliance according to the procedures
specified in paragraph (s) of this
proposed AD. The request should
include a description of changes to the
required inspections that will ensure the
continued operational safety of the
airplane.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 30 products of U.S. registry.
The actions that are required by AD
2011–16–01, Amendment 39–16759 (76
FR 47424, August 5, 2011), and retained
in this proposed AD take about 340
work-hours per product, at an average
labor rate of $85 per work hour. Where
the service information lists required
parts costs that are covered under
warranty, we have assumed that there
will be no charge for these parts. As we
do not control warranty coverage for
affected parties, some parties may incur
costs higher than estimated here. Based
on these figures, the estimated cost of
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the currently required actions is $28,900
product.
We estimate that it would take about
11 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$28,050, or $935 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2011–16–01, Amendment 39–16759 (76
FR 47424, August 5, 2011), and adding
the following new AD:
■
Dassault Aviation: Docket No. FAA–2013–
0464; Directorate Identifier 2012–NM–
010–AD.
(a) Comments Due Date
We must receive comments by August 19,
2013.
(b) Affected ADs
This AD supersedes AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011).
(c) Applicability
This AD applies to all Dassault Aviation
Model FALCON 7X airplanes, certificated in
any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by an uncontrolled
pitch trim runaway during descent. We are
issuing this AD to prevent an uncontrolled
pitch trim runaway, which could result in
loss of control of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Modification
This paragraph restates the requirements of
paragraph (g) of AD 2011–16–01,
Amendment 39–16759 (76 FR47424, August
5, 2011). Before further flight, do the
applicable actions specified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD.
(1) For airplanes on which Dassault
Mandatory Service Bulletin 7X–211, Revision
1, dated June 14, 2011, has not been done as
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of August 22, 2011 (the effective date of AD
2011–16–01, Amendment 39–16759 (76 FR
47424, August 5, 2011)): Modify the airplane
by adding an automatic reversion logic and
a means for the pilot to override pitch trim
control normal modes, and install placards in
the cockpit in full view of the pilots, in
accordance with paragraph 2.,
‘‘Accomplishment Instructions for Aircraft
which have not Already Implemented the
Revision 1 of the Service Bulletin,’’ of
Dassault Mandatory Service Bulletin 7X–211,
Revision 2, including New Standard
Installation Checklist and Appendix A, dated
June 22, 2011, including FCS Data Loading
Procedure, Issue D, dated May 28, 2010.
(2) For airplanes on which Dassault
Mandatory Service Bulletin 7X–211, Revision
1, dated June 14, 2011, has been done as of
August 22, 2011 (the effective date of AD
2011–16–01, Amendment 39–16759 (76 FR
47424, August 5, 2011)): Replace the frame of
the emergency switch box, in accordance
with paragraph 3., ‘‘Accomplishment
Instructions for Aircraft which have Already
Implemented Revision 1 of this Service
Bulletin,’’ of Dassault Mandatory Service
Bulletin 7X–211, Revision 2, including New
Standard Installation Checklist and
Appendix A, dated June 22, 2011, including
FCS Data Loading Procedure, Issue D, dated
May 28, 2010.
(3) For airplanes equipped with any
horizontal stabilizer electronic control unit
(HSECU) P/N 051244–04, replace the HSECU
with any HSECU identified in paragraph
(g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD, in
accordance with the Accomplishment
Instructions of Dassault Mandatory Service
Bulletin 7X–212, Revision 2, dated July 7,
2011.
(i) HSECU P/N 051244–02.
(ii) Verified HSECU P/N 051244–04 having
a stamped ‘‘V.’’
(iii) HSECU P/N 051244–05.
(h) Retained Credit for Previous Actions
This paragraph restates the provisions
specified in paragraph (h) of AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011). This paragraph provides credit for
the HSECU replacement required by
paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if
those replacements were performed before
August 22, 2011 (the effective date of AD
2011–16–01), using Dassault Mandatory
Service Bulletin 7X–212, Revision 1, dated
June 23, 2011, which is not incorporated by
reference in this AD.
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(i) Retained Revision of Airplane Flight
Manual (AFM)
This paragraph restates the requirements of
paragraph (i) of AD 2011–16–01, Amendment
39–16759 (76 FR 47424, August 5, 2011). As
of August 22, 2011 (the effective date AD
2011–16–01), operate the airplane according
to the limitations and procedures in the
Dassault Falcon 7X AFM, Revision 12, dated
June 16, 2011, until the actions required by
paragraph (p) of this AD are accomplished.
Revision 12 introduces revised operational
speed limitations and revised procedures
accounting for the new TRIM EMERG button.
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(j) Retained Electronic Checklist Database
Installation
This paragraph restates the requirements of
paragraph (j) of AD 2011–16–01, Amendment
39–16759 (76 FR 47424, August 5, 2011).
Before further flight, install the electronic
checklist V0007 database, in accordance with
the Accomplishment Instructions of Dassault
Service Bulletin 7X–213, dated June 22,
2011. Accomplishment of the actions
required in paragraph (o) of this AD
terminates the actions required by paragraph
(j) of this AD.
(k) Retained Operating Restrictions
This paragraph restates the requirements of
paragraph (k) of AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011). Before further flight, revise the
Limitations section of the Dassault Falcon 7X
AFM to include the information provided in
Figure 1 to paragraph (k) of this AD. This
may be accomplished by inserting a copy of
Figure 1 to paragraph (k) of this AD into the
AFM. Accomplishment of the actions
required in paragraph (p) of this AD
terminates the actions required by paragraph
(k) of this AD.
Figure 1 to Paragraph (k) of This AD
Dispatch with any inoperative equipment
identified below is prohibited. This
prohibition takes precedence over the FAA
master minimum equipment list (MMEL) or
any operator’s MEL.
Air data systems (identified as MEL item 34–
9)
Multi functional probe (MFP) heating system
(identified as MMEL item 30–1)
ACMU3 and ACMU4 (identified as MMEL
item 27–3)
LH REAR POWER #3 (identified as MMEL
item 27–5–(–6)
Back-up mode (identified as MMEL item 27–
8)
(l) Retained Maintenance Program Revision
This paragraph restates the requirements of
paragraph (l) of AD 2011–16–01, Amendment
39–16759 (76 FR 47424, August 5, 2011).
(1) Within 30 days after August 22, 2011
(the effective date of AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011)), revise the maintenance program to
incorporate Maintenance Planning Document
(MPD) Task 27–40–00–710–801, as specified
in Dassault Aviation, Falcon 7X Maintenance
Manual (MM), Falcon 7X—Chapter 5–40–00
after Rev 01, dated June 10, 2011 (commonly
referred to as Dassault Change Proposal (CP)
CP009 to Chapter 5–40–00 of Dassault Falcon
7X MM). The initial compliance time for
doing the operational test of the HSTS
electric motors reversion relays is 1,850 flight
hours after accomplishment of the applicable
actions required by paragraph (g) of this AD.
Accomplishment of the actions required in
paragraph (q) of this AD terminates the
actions required by paragraph (l) of this AD.
(2) The MM revision required by paragraph
(l) of this AD may be done by inserting a
copy of Dassault CP CP009, dated June 10,
2011, to Chapter 5–40–00 of Dassault Falcon
7X MM into the MM. When Dassault CP
CP009 has been included in general revisions
of the MM, the general revisions may be
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
inserted into the MM, provided the relevant
information in the general revision is
identical to that in Dassault CP CP009, and
Dassault CP CP009 may be removed.
(m) Retained Limitations for Alternative
Procedures or Intervals
This paragraph restates the requirements of
paragraph (m) of AD 2011–16–01,
Amendment 39–16759 (76 FR47424, August
5, 2011). After the maintenance program has
been revised as required by paragraph (l) of
this AD, no alternative procedure or interval
for the operational test may be used unless
the procedure and/or interval is approved as
an alternative method of compliance (AMOC)
in accordance with the procedures specified
in paragraph (s) of this AD.
(n) Retained FAA AD Differences
This paragraph restates the AD differences
identified by Note 3 of AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011). This AD differs from the mandatory
continuing airworthiness information (MCAI)
and/or service information as follows:
(1) European Aviation Safety Agency
(EASA) AD 2011–0114R2 requires repetitive
operational tests of the HSTS electric motors
reversion relays, and specifies that the
aircraft maintenance program may be revised
in lieu of those repetitive tests. This FAA AD
mandates revising the maintenance program.
(2) EASA AD 2011–0114R2 does not
include any requirement to revise the
electronic checklist. Paragraph (j) of this FAA
AD requires this action.
(3) EASA AD 2011–0114R2 mandates
amending the minimum equipment list
(MEL) by removing certain items. This FAA
AD instead requires revising the AFM to
prohibit dispatch with those items
inoperative. The operational effect, however,
is the same.
(o) New Fly-By-Wire System Modification
Within 12 months after accomplishing the
actions required by paragraph (g) of this AD
or within 9 months after the effective date of
this AD, whichever is later: Modify the flyby-wire system installed in the airplane to
the 2.1.7.3 standard, in accordance with the
Accomplishment Instructions of Dassault
Mandatory Service Bulletin 7X–214, dated
August 30, 2011, as revised by Dassault
Mandatory Service Bulletin 7X–214, Revision
Erratum, dated January 26, 2012.
Accomplishment of the actions required in
paragraph (o) of this AD terminates the
actions required by paragraph (j) of this AD.
(p) New AFM Revision
After accomplishing the actions required
by paragraph (o) of this AD: Operate the
airplane thereafter according to the
limitations and procedures specified in
Dassault Falcon 7X AFM, Revision 13, dated
August 29, 2011. Accomplishment of the
actions required by this paragraph terminates
the requirements of paragraphs (i) and (k) of
this AD; thereafter, the AFM limitation
required by paragraph (k) of this AD may be
removed from the AFM.
(q) New Maintenance Program Revision
Within 30 days after the effective date of
this AD: Revise the maintenance program to
E:\FR\FM\03JYP1.SGM
03JYP1
Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules
incorporate Chapter 5–40–00, Airworthiness
Limitations, of the Dassault Falcon 7X MM
DGT 107838, Revision 2, dated August 25,
2011, into the MM.
(1) The initial compliance time for the
operational test of the HSTS trim emergency
command is within 650 flight hours after the
modification required by paragraph (o) of this
AD.
(2) The initial compliance time for the
operational test of the HSTS electric motors
reversion relays is within 5,050 flight hours
after the modification required by paragraph
(o) of this AD.
(3) Accomplishment of the actions required
in paragraph (q) of this AD terminates the
actions required by paragraph (l) of this AD.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(r) New Limitations for Alternative Actions
or Intervals
After accomplishing the revision required
by paragraph (q) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an AMOC in accordance with
the procedures specified in paragraph (s) of
this AD.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, Transport Airplane Directorate,
ANM–116, 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:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1137; fax (425) 227–
1149. Information may be emailed to: 9ANM-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. AMOCs approved previously in
accordance with AD 2011–16–01,
Amendment 39–16759 (76 FR 47424, August
5, 2011), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(t) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2011–0241, dated December 19,
2011, and the service information specified
in paragraphs (t)(1)(i) though (t)(1)(ix) of this
AD.
VerDate Mar<15>2010
16:18 Jul 02, 2013
Jkt 229001
(i) Chapter 5–40–00, Airworthiness
Limitations, of the Dassault Falcon 7X MM
DGT 107838, Revision 2, dated August 25,
2011.
(ii) Dassault Change Proposal CP009 to
Chapter 5–40- 00 of Dassault Falcon 7X
Maintenance Manual), dated June 10, 2011.
(iii) Dassault Falcon 7X Airplane Flight
Manual, Revision 12, dated June 16, 2011.
(iv) Dassault Falcon 7X Airplane Flight
Manual, Revision 13, dated August 29, 2011.
(v) Dassault Mandatory Service Bulletin
7X–211, Revision 2, including New Standard
Installation Checklist and Appendix A, dated
June 22, 2011, including FCS Data Loading
Procedure, Issue D, dated May 28, 2010.
(vi) Dassault Mandatory Service Bulletin
7X–212, Revision 2, dated July 7, 2011.
(vii) Dassault Mandatory Service Bulletin
7X–214, dated August 30, 2011.
(viii) Dassault Mandatory Service Bulletin
7X–214, Revision Erratum, dated January 26,
2012.
(ix) Dassault Service Bulletin 7X–213,
dated June 22, 2011.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.com. You may review
copies of the 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 14,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–15949 Filed 7–2–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0539; Directorate
Identifier 2012–NM–145–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of Proposed Rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2000–12–
11, that applies to certain Model A300
B4–600 and Model A300 B4–600R series
airplanes. That AD currently requires
repetitive inspections to detect cracks in
the bolt holes inboard and outboard of
rib 9 on the bottom booms of the front
and rear wing spars, and repair if
necessary. Since we issued that AD, we
have determined through a fleet survey
SUMMARY:
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
40069
and an updated fatigue and damage
tolerance analysis that the risk for
fatigue cracking on the front and rear
spar bottom booms is higher than was
initially determined. This proposed AD
would reduce the initial inspection
compliance time and repetitive
inspection interval. We are proposing
this AD to detect and correct fatigue
cracks in the bolt holes of the wing
spars, which could result in reduced
structural integrity of a wing spar.
DATES: We must receive comments on
this proposed AD by August 19, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
EAW (Airworthiness Office), 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the 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; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: (425) 227–2125;
fax: (425) 227–1149.
E:\FR\FM\03JYP1.SGM
03JYP1
]]>Agencies
[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40065-40069]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-15949]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0464; Directorate Identifier 2012-NM-010-AD]
RIN 2120-AA64
Airworthiness Directives; Dassault Aviation Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all Dassault Aviation Model FALCON 7X airplanes.
The existing AD currently requires adding an automatic reversion logic
and a means for the pilot to override pitch trim control normal modes,
and installing placards in the cockpit; replacing the frame of the
emergency switch box; replacing certain horizontal stabilizer
electronic control units (HSECU); operating the airplane according to
the limitations and procedures in the airplane flight manual (AFM);
revising the Limitations section of the AFM; and revising the
maintenance program to incorporate a certain maintenance planning
document (MPD) task. Since we issued that AD, Dassault Aviation has
developed a modification of the fly-by-wire (FBW) standard; changed the
AFM to incorporate changes resulting from the FBW modification; and
revised the airplane maintenance manual (AMM) to incorporate repetitive
operational tests of the electric motors reversion relays and trim
emergency command of the horizontal stabilizer trim system (HSTS). Once
incorporated, these actions allow restoration of the originally
certified minimum equipment list items. This proposed AD would retain
certain requirements of the previous AD; would require modifying the
FBW standard; operating the
[[Page 40066]]
airplane according to the limitations and procedures in an approved
AFM; and operational testing of the electric motors reversion relays
and trim emergency command of the HSTS, and repairs if necessary. We
are proposing this AD to prevent an uncontrolled pitch trim runaway,
which could result in loss of control of the airplane.
DATES: We must receive comments on this proposed AD by August 19, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606;
telephone 201-440-6700; Internet https://www.dassaultfalcon.com.
You may review copies of the 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; or in person at the Docket Operations office
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: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1137;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0464;
Directorate Identifier 2012-NM-010-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
On July 15, 2011, we issued AD 2011-16-01, Amendment 39-16759 (76
FR 47424, August 5, 2011). That AD requires actions intended to address
an unsafe condition on all Dassault Aviation Model FALCON 7X airplanes.
Since we issued AD 2011-16-01, Amendment 39-16759 (76 FR 47424,
August 5, 2011), the European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2011-0241, dated December 19,
2011 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
In May 2011, a Dassault Aviation Falcon 7X aeroplane experienced
an uncontrolled pitch trim runaway during descent. The crew
succeeded in recovering a stable situation and performed an
uneventful landing.
The results of the investigations showed that there was a
production defect in the Horizontal Stabilizer Electronic Control
Unit (HSECU) which could have contributed to the cause of the event.
This condition, if not corrected, could lead to a loss of
control of the aeroplane.
To address this unsafe condition, EASA issued emergency AD 2011-
0102-E which prohibited further flights. Following further technical
investigations accomplished by Dassault Aviation, EASA issued AD
2011-0114, currently at revision 2, which superseded EASA AD 2011-
0102-E. Following accomplishment of all the actions as required by
EASA AD 2011-0114R2, all aeroplanes could resume flying with
operational limitations.
Since EASA AD 2011-0114R2 was issued, Dassault Aviation have
developed a modification (M1245 to be embodied through
accomplishment of Dassault Aviation Service Bulletin F7X-214) of the
Fly-By-Wire (FBW) current standard which improves the monitoring and
reversion logic of the Horizontal Stabilizer Trim System (HSTS).
This modification results in earlier failure detection and quicker
reversion.
Dassault Aviation have issued as well Revision 13 of the
Aircraft Flight Manual (AFM) which incorporates the changes
introduced in EASA AD 2011-0114R2 (CP55 and 56) as well as the new
changes resulting from Dassault Aviation M1245 (CP58).
Dassault Aviation have introduced as well operational tests of
the HSTS electric motors reversion relays and of the HSTS trim
emergency command into the Chapter 5.40 of F7X Aircraft Maintenance
Manual (CP010).
For the reasons described above, EASA issued AD 2011-0169 to
require:
1. accomplishing Dassault Aviation modification M1245,
2. amending the AFM, and
3. implementing the operational tests of the HSTS electric
motors reversion relays and of the HSTS trim emergency command.
Accomplishment of all the above actions restored the full
original certified flight envelope of the aeroplane.
Since EASA AD 2011-0169 was issued, further analyses have
demonstrated that, once Dassault Aviation modification M1245 is
embodied, it is allowed to restore the originally certified Minimum
Equipment List (MEL) items which were removed in accordance with the
requirement of paragraph (4) of EASA AD 2011-0114R2.
For the reasons described above, this [EASA] AD, which
supersedes EASA AD 2011-0169, retaining its requirements, in
addition, extends the applicability of the AD to all S/Ns and, for
aeroplanes fitted with FBW standard 2.1.7.3, allows the MEL
limitations imposed by EASA AD 2011-0114R2 to be removed.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Dassault has issued the following service information.
Dassault Mandatory Service Bulletin 7X-214, including New
Standard Installation Checklist, dated August 30, 2011.
Dassault Mandatory Service Bulletin 7X-214, Revision
Erratum, dated January 26, 2012.
Dassault Falcon 7X AFM, Revision 13, dated August 29,
2011.
FCS Data Loading Procedure, Reference DT EQUIP 43913,
Issue D, dated May 28, 2010.
Chapter 5-40-00, Airworthiness Limitations, of the Falcon
7X Maintenance Manual DGT 107838, Revision 2, dated August 25, 2011.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
Explanation of Changes Made to This NPRM
We have revised the heading and wording for paragraph (h) of this
[[Page 40067]]
proposed AD; this change does not affect the intent of that paragraph.
We have deleted note 2 to paragraph (l) of AD 2011-16-01, Amendment
39-16759 (76 FR 47424, August 5, 2011). Instead, we have included that
information in paragraph (l)(2) of this proposed AD.
We have deleted note 3 of AD 2011-16-01, Amendment 39-16759 (76 FR
47424, August 5, 2011). Instead, we have included that information in
paragraph (n) of this proposed AD.
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 the same
type design.
This AD requires revisions to certain operator maintenance
documents to include new inspections. Compliance with these inspections
is required by 14 CFR 91.403(c). For airplanes that have been
previously modified, altered, or repaired in the areas addressed by
these inspections, the operator may not be able to accomplish the
inspections described in the revisions. In this situation, to comply
with 14 CFR 91.403(c), the operator must request approval for an
alternative method of compliance according to the procedures specified
in paragraph (s) of this proposed AD. The request should include a
description of changes to the required inspections that will ensure the
continued operational safety of the airplane.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 30 products of U.S. registry.
The actions that are required by AD 2011-16-01, Amendment 39-16759
(76 FR 47424, August 5, 2011), and retained in this proposed AD take
about 340 work-hours per product, at an average labor rate of $85 per
work hour. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, the estimated cost of the currently
required actions is $28,900 product.
We estimate that it would take about 11 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Where the service information lists
required parts costs that are covered under warranty, we have assumed
that there will be no charge for these parts. As we do not control
warranty coverage for affected parties, some parties may incur costs
higher than estimated here. Based on these figures, we estimate the
cost of the proposed AD on U.S. operators to be $28,050, or $935 per
product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011), and
adding the following new AD:
Dassault Aviation: Docket No. FAA-2013-0464; Directorate Identifier
2012-NM-010-AD.
(a) Comments Due Date
We must receive comments by August 19, 2013.
(b) Affected ADs
This AD supersedes AD 2011-16-01, Amendment 39-16759 (76 FR
47424, August 5, 2011).
(c) Applicability
This AD applies to all Dassault Aviation Model FALCON 7X
airplanes, certificated in any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by an uncontrolled pitch trim runaway
during descent. We are issuing this AD to prevent an uncontrolled
pitch trim runaway, which could result in loss of control of the
airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Modification
This paragraph restates the requirements of paragraph (g) of AD
2011-16-01, Amendment 39-16759 (76 FR47424, August 5, 2011). Before
further flight, do the applicable actions specified in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD.
(1) For airplanes on which Dassault Mandatory Service Bulletin
7X-211, Revision 1, dated June 14, 2011, has not been done as
[[Page 40068]]
of August 22, 2011 (the effective date of AD 2011-16-01, Amendment
39-16759 (76 FR 47424, August 5, 2011)): Modify the airplane by
adding an automatic reversion logic and a means for the pilot to
override pitch trim control normal modes, and install placards in
the cockpit in full view of the pilots, in accordance with paragraph
2., ``Accomplishment Instructions for Aircraft which have not
Already Implemented the Revision 1 of the Service Bulletin,'' of
Dassault Mandatory Service Bulletin 7X-211, Revision 2, including
New Standard Installation Checklist and Appendix A, dated June 22,
2011, including FCS Data Loading Procedure, Issue D, dated May 28,
2010.
(2) For airplanes on which Dassault Mandatory Service Bulletin
7X-211, Revision 1, dated June 14, 2011, has been done as of August
22, 2011 (the effective date of AD 2011-16-01, Amendment 39-16759
(76 FR 47424, August 5, 2011)): Replace the frame of the emergency
switch box, in accordance with paragraph 3., ``Accomplishment
Instructions for Aircraft which have Already Implemented Revision 1
of this Service Bulletin,'' of Dassault Mandatory Service Bulletin
7X-211, Revision 2, including New Standard Installation Checklist
and Appendix A, dated June 22, 2011, including FCS Data Loading
Procedure, Issue D, dated May 28, 2010.
(3) For airplanes equipped with any horizontal stabilizer
electronic control unit (HSECU) P/N 051244-04, replace the HSECU
with any HSECU identified in paragraph (g)(3)(i), (g)(3)(ii), or
(g)(3)(iii) of this AD, in accordance with the Accomplishment
Instructions of Dassault Mandatory Service Bulletin 7X-212, Revision
2, dated July 7, 2011.
(i) HSECU P/N 051244-02.
(ii) Verified HSECU P/N 051244-04 having a stamped ``V.''
(iii) HSECU P/N 051244-05.
(h) Retained Credit for Previous Actions
This paragraph restates the provisions specified in paragraph
(h) of AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5,
2011). This paragraph provides credit for the HSECU replacement
required by paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if those
replacements were performed before August 22, 2011 (the effective
date of AD 2011-16-01), using Dassault Mandatory Service Bulletin
7X-212, Revision 1, dated June 23, 2011, which is not incorporated
by reference in this AD.
(i) Retained Revision of Airplane Flight Manual (AFM)
This paragraph restates the requirements of paragraph (i) of AD
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). As of
August 22, 2011 (the effective date AD 2011-16-01), operate the
airplane according to the limitations and procedures in the Dassault
Falcon 7X AFM, Revision 12, dated June 16, 2011, until the actions
required by paragraph (p) of this AD are accomplished. Revision 12
introduces revised operational speed limitations and revised
procedures accounting for the new TRIM EMERG button.
(j) Retained Electronic Checklist Database Installation
This paragraph restates the requirements of paragraph (j) of AD
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). Before
further flight, install the electronic checklist V0007 database, in
accordance with the Accomplishment Instructions of Dassault Service
Bulletin 7X-213, dated June 22, 2011. Accomplishment of the actions
required in paragraph (o) of this AD terminates the actions required
by paragraph (j) of this AD.
(k) Retained Operating Restrictions
This paragraph restates the requirements of paragraph (k) of AD
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). Before
further flight, revise the Limitations section of the Dassault
Falcon 7X AFM to include the information provided in Figure 1 to
paragraph (k) of this AD. This may be accomplished by inserting a
copy of Figure 1 to paragraph (k) of this AD into the AFM.
Accomplishment of the actions required in paragraph (p) of this AD
terminates the actions required by paragraph (k) of this AD.
Figure 1 to Paragraph (k) of This AD
Dispatch with any inoperative equipment identified below is
prohibited. This prohibition takes precedence over the FAA master
minimum equipment list (MMEL) or any operator's MEL.
Air data systems (identified as MEL item 34-9)
Multi functional probe (MFP) heating system (identified as MMEL item
30-1)
ACMU3 and ACMU4 (identified as MMEL item 27-3)
LH REAR POWER 3 (identified as MMEL item 27-5-(-6)
Back-up mode (identified as MMEL item 27-8)
(l) Retained Maintenance Program Revision
This paragraph restates the requirements of paragraph (l) of AD
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011).
(1) Within 30 days after August 22, 2011 (the effective date of
AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011)),
revise the maintenance program to incorporate Maintenance Planning
Document (MPD) Task 27-40-00-710-801, as specified in Dassault
Aviation, Falcon 7X Maintenance Manual (MM), Falcon 7X--Chapter 5-
40-00 after Rev 01, dated June 10, 2011 (commonly referred to as
Dassault Change Proposal (CP) CP009 to Chapter 5-40-00 of Dassault
Falcon 7X MM). The initial compliance time for doing the operational
test of the HSTS electric motors reversion relays is 1,850 flight
hours after accomplishment of the applicable actions required by
paragraph (g) of this AD. Accomplishment of the actions required in
paragraph (q) of this AD terminates the actions required by
paragraph (l) of this AD.
(2) The MM revision required by paragraph (l) of this AD may be
done by inserting a copy of Dassault CP CP009, dated June 10, 2011,
to Chapter 5-40-00 of Dassault Falcon 7X MM into the MM. When
Dassault CP CP009 has been included in general revisions of the MM,
the general revisions may be inserted into the MM, provided the
relevant information in the general revision is identical to that in
Dassault CP CP009, and Dassault CP CP009 may be removed.
(m) Retained Limitations for Alternative Procedures or Intervals
This paragraph restates the requirements of paragraph (m) of AD
2011-16-01, Amendment 39-16759 (76 FR47424, August 5, 2011). After
the maintenance program has been revised as required by paragraph
(l) of this AD, no alternative procedure or interval for the
operational test may be used unless the procedure and/or interval is
approved as an alternative method of compliance (AMOC) in accordance
with the procedures specified in paragraph (s) of this AD.
(n) Retained FAA AD Differences
This paragraph restates the AD differences identified by Note 3
of AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011).
This AD differs from the mandatory continuing airworthiness
information (MCAI) and/or service information as follows:
(1) European Aviation Safety Agency (EASA) AD 2011-0114R2
requires repetitive operational tests of the HSTS electric motors
reversion relays, and specifies that the aircraft maintenance
program may be revised in lieu of those repetitive tests. This FAA
AD mandates revising the maintenance program.
(2) EASA AD 2011-0114R2 does not include any requirement to
revise the electronic checklist. Paragraph (j) of this FAA AD
requires this action.
(3) EASA AD 2011-0114R2 mandates amending the minimum equipment
list (MEL) by removing certain items. This FAA AD instead requires
revising the AFM to prohibit dispatch with those items inoperative.
The operational effect, however, is the same.
(o) New Fly-By-Wire System Modification
Within 12 months after accomplishing the actions required by
paragraph (g) of this AD or within 9 months after the effective date
of this AD, whichever is later: Modify the fly-by-wire system
installed in the airplane to the 2.1.7.3 standard, in accordance
with the Accomplishment Instructions of Dassault Mandatory Service
Bulletin 7X-214, dated August 30, 2011, as revised by Dassault
Mandatory Service Bulletin 7X-214, Revision Erratum, dated January
26, 2012. Accomplishment of the actions required in paragraph (o) of
this AD terminates the actions required by paragraph (j) of this AD.
(p) New AFM Revision
After accomplishing the actions required by paragraph (o) of
this AD: Operate the airplane thereafter according to the
limitations and procedures specified in Dassault Falcon 7X AFM,
Revision 13, dated August 29, 2011. Accomplishment of the actions
required by this paragraph terminates the requirements of paragraphs
(i) and (k) of this AD; thereafter, the AFM limitation required by
paragraph (k) of this AD may be removed from the AFM.
(q) New Maintenance Program Revision
Within 30 days after the effective date of this AD: Revise the
maintenance program to
[[Page 40069]]
incorporate Chapter 5-40-00, Airworthiness Limitations, of the
Dassault Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011,
into the MM.
(1) The initial compliance time for the operational test of the
HSTS trim emergency command is within 650 flight hours after the
modification required by paragraph (o) of this AD.
(2) The initial compliance time for the operational test of the
HSTS electric motors reversion relays is within 5,050 flight hours
after the modification required by paragraph (o) of this AD.
(3) Accomplishment of the actions required in paragraph (q) of
this AD terminates the actions required by paragraph (l) of this AD.
(r) New Limitations for Alternative Actions or Intervals
After accomplishing the revision required by paragraph (q) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used unless the actions or intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (s) of this
AD.
(s) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, Transport Airplane Directorate, ANM-116, 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: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone (425) 227-1137; 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. AMOCs approved previously in accordance with AD 2011-16-01,
Amendment 39-16759 (76 FR 47424, August 5, 2011), are approved as
AMOCs for the corresponding provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(t) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0241, dated
December 19, 2011, and the service information specified in
paragraphs (t)(1)(i) though (t)(1)(ix) of this AD.
(i) Chapter 5-40-00, Airworthiness Limitations, of the Dassault
Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011.
(ii) Dassault Change Proposal CP009 to Chapter 5-40- 00 of
Dassault Falcon 7X Maintenance Manual), dated June 10, 2011.
(iii) Dassault Falcon 7X Airplane Flight Manual, Revision 12,
dated June 16, 2011.
(iv) Dassault Falcon 7X Airplane Flight Manual, Revision 13,
dated August 29, 2011.
(v) Dassault Mandatory Service Bulletin 7X-211, Revision 2,
including New Standard Installation Checklist and Appendix A, dated
June 22, 2011, including FCS Data Loading Procedure, Issue D, dated
May 28, 2010.
(vi) Dassault Mandatory Service Bulletin 7X-212, Revision 2,
dated July 7, 2011.
(vii) Dassault Mandatory Service Bulletin 7X-214, dated August
30, 2011.
(viii) Dassault Mandatory Service Bulletin 7X-214, Revision
Erratum, dated January 26, 2012.
(ix) Dassault Service Bulletin 7X-213, dated June 22, 2011.
(2) For service information identified in this AD, contact
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey
07606; telephone 201-440-6700; Internet https://www.dassaultfalcon.com. You may review copies of the 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 14, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15949 Filed 7-2-13; 8:45 am]
BILLING CODE 4910-13-P
