Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes, 45337-45340 [2014-17315]
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Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations
(c) Effective Date
This AD becomes effective August 20, 2014
to all persons except those persons to whom
it was made immediately effective by
Emergency AD 2014–12–51, issued on June
10, 2014, which contained the requirements
of this AD.
(d) 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.
(e) Required Actions
(1) Within 10 hours TIS, remove the
horizontal stabilizer, clean the junction
frame, and dye-penetrant inspect around the
circumference of the junction frame for a
crack in the areas shown in Figure 1 of
Airbus Helicopters EC130 Emergency Alert
Service Bulletin No. 05A017, Revision 0,
dated June 6, 2014 (EASB 05A017). Pay
particular attention to the area around the 4
spars (item b) of Figure 1 of EASB 05A017.
An example of a crack is shown in Figure 3
of EASB 05A017.
(2) Within 25 hours TIS of the inspection
required by paragraph (e)(1) of this AD, and
thereafter at intervals not exceeding 25 hours
TIS, either perform the actions of paragraph
(e)(1) of this AD or, if the area is clean, using
a borescope, inspect around the
circumference of the junction frame for a
crack in the areas shown in Figure 2 of EASB
05A017. Pay particular attention to the area
around the 4 spars (item b) of Figure 2 of
EASB 05A017. An example of a crack is
shown in Figure 3 of EASB 05A017.
(3) If there is a crack, before further flight,
replace the junction frame.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Helicopters Emergency Alert
Service Bulletin No. 05A017, Revision 0,
dated June 6, 2014.
(ii) [Reserved]
(3) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://www.air
bushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may also view this service
information that is incorporated by reference
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://www.
archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on July 24,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–18247 Filed 8–4–14; 8:45 am]
BILLING CODE 4910–13–P
(f) Special Flight Permits
Special flight permits are prohibited.
DEPARTMENT OF TRANSPORTATION
(g) Alternative Methods of Compliance
(AMOCs)
Federal Aviation Administration
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5110; email robert.grant@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.
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(h) Additional Information
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5302: Rotorcraft Tailboom.
16:53 Aug 04, 2014
[Docket No. FAA–2014–0056; Directorate
Identifier 2013–NM–160–AD; Amendment
39–17906; AD 2014–15–04]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Saab AB, Saab Aerosystems Model
SAAB 2000 airplanes. This AD was
prompted by a report of rudder pedal
restriction which was the result of water
leakage at the inlet tubing of an in-line
heater in the lower part of the forward
fuselage. This AD requires deactivating
the potable water system, or
SUMMARY:
The subject of this AD is addressed in
European Aviation Safety Agency EAD No.
2014–0145–E, dated June 6, 2014. You may
view the EASA AD on the Internet at https://
www.regulations.gov in Docket No. FAA–
2014–0515.
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45337
alternatively filling and activating the
potable water system. We are issuing
this AD to prevent rudder pedal
restriction due to the pitch control
mechanism becoming frozen as the
result of water spray, which could
prevent disconnection and normal pitch
control, and consequently result in
reduced controllability of the airplane.
DATES: This AD becomes effective
September 9, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 9, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://www.
regulations.gov/#!docketDetail;D=FAA2014-0056; or in person at the Docket
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC.
For service information identified in
this AD, contact Saab AB, Saab
¨
Aerosystems, SE–581 88, Linkoping,
Sweden; telephone +46 13 18 5591; fax
+46 13 18 4874; email saab2000.tech
support@saabgroup.com; Internet
https://www.saabgroup.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.
FOR FURTHER INFORMATION CONTACT:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; telephone 425–227–
1112; fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Saab AB, Saab
Aerosystems Model SAAB 2000
airplanes. The NPRM published in the
Federal Register on February 25, 2014
(79 FR 10433). The NPRM was
prompted by a report of rudder pedal
restriction which was the result of water
leakage at the inlet tubing of an in-line
heater in the lower part of the forward
fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0172R1,
dated September 6, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
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Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations
MCAI’’), to correct an unsafe condition
for certain Saab AB, Saab Aerosystems
Model SAAB 2000 airplanes. The MCAI
states:
One occurrence of rudder pedal restriction
has been reported on a SAAB 2000
aeroplane. Subsequent investigation showed
that this was the result of water leakage at the
inlet tubing for the in-line heater (25HY) in
the lower part of the forward fuselage (Zone
116). The in-line heater attachment was
found ruptured, which resulted in water
spraying in the area. Frozen water on the
rudder control mechanism in Zone 116 then
led to the rudder pedal restriction.
Analysis after the reported event indicates
that the pitch control mechanism (including
pitch disconnect/spring unit) may also be
frozen as a result of water spray, which
would prevent disconnection and normal
pitch control.
This condition, if not corrected, could
result in further occurrences of reduced
control of an aeroplane.
Prompted by these findings, as a temporary
action to avoid this potential unsafe
condition, SAAB determined that the potable
water system should be deactivated. SAAB is
working on a solution that is expected to
eliminate the consequences of water spraying
in the area.
To address this unsafe condition, EASA
issued [an] Emergency AD * * * to require
deactivation of the Potable Water System.
Since that [EASA] AD was issued, SAAB
developed a temporary alternative procedure
for filling, reactivation and continued
operation of the potable water system. This
procedure includes a visual inspection to
make sure that there is no water spray in the
lower part of the forward fuselage (Zone 116)
during refilling of the potable water.
For the reasons described above, this
[EASA] AD is revised to allow application of
the alternative filling procedure of the
Potable Water System.
This [EASA] AD is still considered to be
an interim action and further [EASA] AD
action may follow.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/#!documentDetail;
D=FAA-2014-0056-0002.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 10433, February 25, 2014) or on the
determination of the cost to the public.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
The MCAI or referenced service
information in an FAA AD often directs
the owner/operator to contact the
manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
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Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 10433, February
25, 2014), we proposed to prevent the
use of repairs that were not specifically
developed to correct the unsafe
condition, by requiring that the repair
approval provided by the State of
Design Authority or its delegated agent
specifically refer to this FAA AD. This
change was intended to clarify the
method of compliance and to provide
operators with better visibility of repairs
that are specifically developed and
approved to correct the unsafe
condition. In addition, we proposed to
change the phrase ‘‘its delegated agent’’
to include a design approval holder
(DAH) with State of Design Authority
design organization approval (DOA), as
applicable, to refer to a DAH authorized
to approve required repairs for the
proposed AD.
No comments were provided to the
NPRM (79 FR 10433, February 25, 2014)
about these proposed changes. However,
a comment was provided for another
NPRM, Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013), in which the commenter stated
the following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of an AD
mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
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To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed
that paragraph and retitled it
‘‘Contacting the Manufacturer.’’ This
paragraph now clarifies that for any
requirement in this AD to obtain
corrective actions from a manufacturer,
the action must be accomplished using
a method approved by the FAA, the
European Aviation Safety Agency
(EASA), or Saab AB, Saab Aerosystems’
EASA DOA.
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that does not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
Other commenters to the NPRM
discussed previously, Directorate
Identifier 2012–NM–101–AD (78 FR
78285, December 26, 2013), pointed out
that in many cases the foreign
manufacturer’s service bulletin and the
foreign authority’s MCAI might have
been issued some time before the FAA
AD. Therefore, the DOA might have
provided U.S. operators with an
approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
approval document, adding time and
expense to the compliance process with
no safety benefit.
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Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations
Based on these comments, we
removed the requirement that the DAHprovided repair specifically refer to this
AD. Before adopting such a
requirement, the FAA will coordinate
with affected DAHs and verify they are
prepared to implement means to ensure
that their repair approvals consider the
unsafe condition addressed in this AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate. We also
have decided not to include a generic
reference to either the ‘‘delegated agent’’
or ‘‘DAH with State of Design Authority
design organization approval,’’ but
instead we have provided the specific
delegation approval granted by the State
of Design Authority for the DAH in the
Contacting the Manufacturer paragraph
of this AD.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
10433, February 25, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 10433,
February 25, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
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Costs of Compliance
We estimate that this AD affects 1
airplane of U.S. registry.
We also estimate that it will take
about 1 work-hour per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
$0 per product. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $85, or $85 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
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promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
gov/#!docketDetail;D=FAA-2014-0056;
or in person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
45339
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–15–04 Saab AB, Saab Aerosystems:
Amendment 39–17906. Docket No.
FAA–2014–0056; Directorate Identifier
2013–NM–160–AD.
(a) Effective Date
This AD becomes effective September 9,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Saab AB, Saab
Aerosystems Model SAAB 2000 airplanes,
certificated in any category, serial numbers
004 through 016 inclusive, 018, 022, 023,
024, 026, 029, 031, 032, 033, 035 through 039
inclusive, 041 through 044 inclusive, 046,
047, 048, 051, and 053 through 063 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 38, Water/Waste.
(e) Reason
This AD was prompted by a report of
rudder pedal restriction which was the result
of water leakage at the inlet tubing for an inline heater in the lower part of the forward
fuselage. We are issuing this AD to prevent
rudder pedal restriction due to the pitch
control mechanism becoming frozen as the
result of water spray, which could prevent
disconnection and normal pitch control, and
consequently result in reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Deactivation of Potable Water System
Within 30 days after the effective date of
this AD, deactivate the potable water system,
in accordance with the Accomplishment
Instructions of Saab Service Bulletin 2000–
38–010, dated July 12, 2013.
(h) Alternative to Deactivation of Potable
Water System
As an alternative, or subsequent, to the
action required by paragraph (g) of this AD,
during each filling of the potable water
system after the effective date of this AD,
accomplish the temporary filling procedure,
in accordance with the instructions in Saab
Service Newsletter SN 2000–1304, Revision
01, dated September 10, 2013, including
Attachment 1 Engineering Statement to
Operator 2000PBS034334, Issue A, dated
September 9, 2013.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
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Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations
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:
Shahram Daneshmandi, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1112; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Saab AB, Saab Aerosystems’
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
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(j) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2013–0172R1, dated September 6,
2013, for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov/#
!documentDetail;D=FAA-2014-0056-0002.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Saab Service Bulletin 2000–38–010,
dated July 12, 2013.
(ii) Saab Service Newsletter SN 2000–1304,
Revision 01, dated September 10, 2013,
including Attachment 1 Engineering
Statement to Operator 2000PBS034334 Issue
A, dated September 9, 2013.
(3) For service information identified in
this AD, contact Saab AB, Saab Aerosystems,
¨
SE–581 88, Linkoping, Sweden; telephone
+46 13 18 5591; fax +46 13 18 4874; email
saab2000.techsupport@saabgroup.com;
Internet https://www.saabgroup.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Issued in Renton, Washington, on July 13,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–17315 Filed 8–4–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0268; Directorate
Identifier 2011–NM–129–AD; Amendment
39–17914; AD 2014–15–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 737–600, –700,
–700C, –800, –900 and –900ER series
airplanes. This AD was prompted by
reports of incorrectly installed bolts
common to the rear spar termination
fitting on the horizontal stabilizer. This
AD requires inspecting for a serial
number that starts with the letters
‘‘SAIC’’ on the left- and right-side
horizontal stabilizer identification plate;
inspecting for correct bolt protrusion
and chamfer of the bolts of the rear spar
termination fitting of the horizontal
stabilizer, if necessary; inspecting to
determine if certain bolts are installed,
if necessary; and doing related
investigative and corrective actions if
necessary. We are issuing this AD to
prevent loss of structural integrity of the
horizontal stabilizer attachment and loss
of control of the airplane.
DATES: This AD is effective September 9,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 9, 2014.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
SUMMARY:
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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–2012–
0268; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6440;
fax: 425–917–6590; email:
nancy.marsh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a second supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900 and –900ER series airplanes.
The second SNPRM published in the
Federal Register on December 9, 2013
(78 FR 73744). We preceded the second
SNPRM with a first SNPRM that
published in the Federal Register on
March 7, 2013 (78 FR 14734). We
preceded the first SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
March 20, 2012 (77 FR 16188).
The NPRM proposed to require
inspecting for a serial number that starts
with the letters ‘‘SAIC’’ on the left- and
right-side horizontal stabilizer
identification plate; a detailed
inspection for correct bolt protrusion
and chamfer of the termination fitting
bolts of the horizontal stabilizer rear
spar, if necessary; inspecting to
determine if certain bolts are installed,
if necessary, and related investigative
and corrective actions if necessary. The
NPRM also proposed to require
repetitive inspections for cracking of the
termination fitting at certain bolt
locations, and repair if necessary. The
NPRM was prompted by reports of
incorrectly installed bolts common to
the rear spar termination fitting on the
horizontal stabilizer. The first SNPRM
revised the NPRM by adding airplanes
to the applicability. The second SNPRM
E:\FR\FM\05AUR1.SGM
05AUR1
]]>Agencies
[Federal Register Volume 79, Number 150 (Tuesday, August 5, 2014)]
[Rules and Regulations]
[Pages 45337-45340]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-17315]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0056; Directorate Identifier 2013-NM-160-AD;
Amendment 39-17906; AD 2014-15-04]
RIN 2120-AA64
Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was
prompted by a report of rudder pedal restriction which was the result
of water leakage at the inlet tubing of an in-line heater in the lower
part of the forward fuselage. This AD requires deactivating the potable
water system, or alternatively filling and activating the potable water
system. We are issuing this AD to prevent rudder pedal restriction due
to the pitch control mechanism becoming frozen as the result of water
spray, which could prevent disconnection and normal pitch control, and
consequently result in reduced controllability of the airplane.
DATES: This AD becomes effective September 9, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 9,
2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0056; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Saab AB,
Saab Aerosystems, SE-581 88, Link[ouml]ping, Sweden; telephone +46 13
18 5591; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com;
Internet https://www.saabgroup.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.
FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM-116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356;
telephone 425-227-1112; fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Saab AB, Saab
Aerosystems Model SAAB 2000 airplanes. The NPRM published in the
Federal Register on February 25, 2014 (79 FR 10433). The NPRM was
prompted by a report of rudder pedal restriction which was the result
of water leakage at the inlet tubing of an in-line heater in the lower
part of the forward fuselage.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0172R1, dated September 6, 2013 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the
[[Page 45338]]
MCAI''), to correct an unsafe condition for certain Saab AB, Saab
Aerosystems Model SAAB 2000 airplanes. The MCAI states:
One occurrence of rudder pedal restriction has been reported on
a SAAB 2000 aeroplane. Subsequent investigation showed that this was
the result of water leakage at the inlet tubing for the in-line
heater (25HY) in the lower part of the forward fuselage (Zone 116).
The in-line heater attachment was found ruptured, which resulted in
water spraying in the area. Frozen water on the rudder control
mechanism in Zone 116 then led to the rudder pedal restriction.
Analysis after the reported event indicates that the pitch
control mechanism (including pitch disconnect/spring unit) may also
be frozen as a result of water spray, which would prevent
disconnection and normal pitch control.
This condition, if not corrected, could result in further
occurrences of reduced control of an aeroplane.
Prompted by these findings, as a temporary action to avoid this
potential unsafe condition, SAAB determined that the potable water
system should be deactivated. SAAB is working on a solution that is
expected to eliminate the consequences of water spraying in the
area.
To address this unsafe condition, EASA issued [an] Emergency AD
* * * to require deactivation of the Potable Water System.
Since that [EASA] AD was issued, SAAB developed a temporary
alternative procedure for filling, reactivation and continued
operation of the potable water system. This procedure includes a
visual inspection to make sure that there is no water spray in the
lower part of the forward fuselage (Zone 116) during refilling of
the potable water.
For the reasons described above, this [EASA] AD is revised to
allow application of the alternative filling procedure of the
Potable Water System.
This [EASA] AD is still considered to be an interim action and
further [EASA] AD action may follow.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0056-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 10433, February 25,
2014) or on the determination of the cost to the public.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In the NPRM (79 FR 10433, February 25, 2014), we proposed to
prevent the use of repairs that were not specifically developed to
correct the unsafe condition, by requiring that the repair approval
provided by the State of Design Authority or its delegated agent
specifically refer to this FAA AD. This change was intended to clarify
the method of compliance and to provide operators with better
visibility of repairs that are specifically developed and approved to
correct the unsafe condition. In addition, we proposed to change the
phrase ``its delegated agent'' to include a design approval holder
(DAH) with State of Design Authority design organization approval
(DOA), as applicable, to refer to a DAH authorized to approve required
repairs for the proposed AD.
No comments were provided to the NPRM (79 FR 10433, February 25,
2014) about these proposed changes. However, a comment was provided for
another NPRM, Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013), in which the commenter stated the following: ``The
proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed that paragraph and
retitled it ``Contacting the Manufacturer.'' This paragraph now
clarifies that for any requirement in this AD to obtain corrective
actions from a manufacturer, the action must be accomplished using a
method approved by the FAA, the European Aviation Safety Agency (EASA),
or Saab AB, Saab Aerosystems' EASA DOA.
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that does not contain the DOA-authorized signature approval are not
EASA-approved, unless EASA directly approves the manufacturer's message
or other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM discussed previously, Directorate
Identifier 2012-NM-101-AD (78 FR 78285, December 26, 2013), pointed out
that in many cases the foreign manufacturer's service bulletin and the
foreign authority's MCAI might have been issued some time before the
FAA AD. Therefore, the DOA might have provided U.S. operators with an
approved repair, developed with full awareness of the unsafe condition,
before the FAA AD is issued. Under these circumstances, to comply with
the FAA AD, the operator would be required to go back to the
manufacturer's DOA and obtain a new approval document, adding time and
expense to the compliance process with no safety benefit.
[[Page 45339]]
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate. We also have
decided not to include a generic reference to either the ``delegated
agent'' or ``DAH with State of Design Authority design organization
approval,'' but instead we have provided the specific delegation
approval granted by the State of Design Authority for the DAH in the
Contacting the Manufacturer paragraph of this AD.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 10433, February 25, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 10433, February 25, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 1 airplane of U.S. registry.
We also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost $0 per product. Based on
these figures, we estimate the cost of this AD on U.S. operators to be
$85, or $85 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0056; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-15-04 Saab AB, Saab Aerosystems: Amendment 39-17906. Docket No.
FAA-2014-0056; Directorate Identifier 2013-NM-160-AD.
(a) Effective Date
This AD becomes effective September 9, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Saab AB, Saab Aerosystems Model SAAB 2000
airplanes, certificated in any category, serial numbers 004 through
016 inclusive, 018, 022, 023, 024, 026, 029, 031, 032, 033, 035
through 039 inclusive, 041 through 044 inclusive, 046, 047, 048,
051, and 053 through 063 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 38, Water/Waste.
(e) Reason
This AD was prompted by a report of rudder pedal restriction
which was the result of water leakage at the inlet tubing for an in-
line heater in the lower part of the forward fuselage. We are
issuing this AD to prevent rudder pedal restriction due to the pitch
control mechanism becoming frozen as the result of water spray,
which could prevent disconnection and normal pitch control, and
consequently result in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Deactivation of Potable Water System
Within 30 days after the effective date of this AD, deactivate
the potable water system, in accordance with the Accomplishment
Instructions of Saab Service Bulletin 2000-38-010, dated July 12,
2013.
(h) Alternative to Deactivation of Potable Water System
As an alternative, or subsequent, to the action required by
paragraph (g) of this AD, during each filling of the potable water
system after the effective date of this AD, accomplish the temporary
filling procedure, in accordance with the instructions in Saab
Service Newsletter SN 2000-1304, Revision 01, dated September 10,
2013, including Attachment 1 Engineering Statement to Operator
2000PBS034334, Issue A, dated September 9, 2013.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested
[[Page 45340]]
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:
Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; telephone 425-227-1112; fax 425-227-1149.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Saab AB, Saab
Aerosystems' EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
(j) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
European Aviation Safety Agency Airworthiness Directive 2013-0172R1,
dated September 6, 2013, for related information. This MCAI may be
found in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0056-0002.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Saab Service Bulletin 2000-38-010, dated July 12, 2013.
(ii) Saab Service Newsletter SN 2000-1304, Revision 01, dated
September 10, 2013, including Attachment 1 Engineering Statement to
Operator 2000PBS034334 Issue A, dated September 9, 2013.
(3) For service information identified in this AD, contact Saab
AB, Saab Aerosystems, SE-581 88, Link[ouml]ping, Sweden; telephone
+46 13 18 5591; fax +46 13 18 4874; email
saab2000.techsupport@saabgroup.com; Internet https://www.saabgroup.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 13, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-17315 Filed 8-4-14; 8:45 am]
BILLING CODE 4910-13-P
