81 FR 66513 - Airworthiness Directives; Saab AB, Saab Aeronautics (Formerly Known as Saab AB, Saab Aerosystems) Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 188 (September 28, 2016)

Page Range		66513-66516
FR Document		2016-23081

We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD requires an inspection to identify the type of fasteners installed on the upper longerons and upper fittings of the engine mounting structure (EMS), an inspection for discrepancies of certain fasteners, and corrective action if necessary. This AD was prompted by the discovery of blind fasteners installed in EMS upper fittings that do not meet the type design. We are issuing this AD to detect and correct discrepancies of blind fasteners that could cause crack development and vibration in the engine mount structure, which could lead to failure of the affected engine-mount-to-airplane structural connection and resultant detachment of an engine from the airplane when both sides of a nacelle are affected.

Federal Register, Volume 81 Issue 188 (Wednesday, September 28, 2016)

[Federal Register Volume 81, Number 188 (Wednesday, September 28, 2016)]
[Rules and Regulations]
[Pages 66513-66516]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-23081]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9114; Directorate Identifier 2016-NM-146-AD; 
Amendment 39-18671; AD 2016-20-05]
RIN 2120-AA64


Airworthiness Directives; Saab AB, Saab Aeronautics (Formerly 
Known as Saab AB, Saab Aerosystems) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD requires 
an inspection to identify the type of fasteners installed on the upper 
longerons and upper fittings of the engine mounting structure (EMS), an 
inspection for discrepancies of certain fasteners, and corrective 
action if necessary. This AD was prompted by the discovery of blind 
fasteners installed in EMS upper fittings that do not meet the type 
design. We are issuing this AD to detect and correct discrepancies of 
blind fasteners that could cause crack development and vibration in the 
engine mount structure, which could lead to failure of the affected 
engine-mount-to-airplane structural connection and resultant detachment 
of an engine from the airplane when both sides of a nacelle are 
affected.

DATES: This AD becomes effective October 13, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publications listed in this AD as of October 13, 
2016.
    We must receive comments on this AD by November 14, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 66514]]

     Federal eRulemaking Portal: Go to http://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 final rule, contact Saab 
AB, Saab Aeronautics, SE-581 88, Link[ouml]ping, Sweden; telephone +46 
13 18 5591; fax +46 13 18 4874; email 
[email protected]; Internet http://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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-9114.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9114; 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 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: 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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0171, dated August 22, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Saab AB, Saab 
Aeronautics Model SAAB 2000 airplanes. The MCAI states:

    During inspections, blind fasteners were found installed in 
engine mounting structure (EMS) upper fittings, frame NS204.7 and 
upper longerons. The type design specifies that the fasteners at 
this location must be Hi-Lok fasteners and two solid rivets (monel).
    This condition, if not detected and corrected, could cause 
cracks development, vibration in the engine mount structure, leading 
to failure of the affected engine mount-to-aeroplane structural 
connection, possibly resulting in detachment of an engine from the 
aeroplane when affecting both sides of a nacelle.
    To address this unsafe condition, SAAB issued Service Bulletin 
(SB) 2000-54-035 (hereafter referred to as `the SB' in this [EASA] 
AD) to provide inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time * * * [general] visual inspection of the affected areas to 
determine which type(s) of fasteners are installed, and, depending 
on findings, accomplishment of applicable corrective action(s) 
[repair or additional actions as applicable]. This [EASA] AD also 
requires reporting of all inspection results to SAAB.
    This [EASA] AD is considered an interim action and further AD 
action may follow.

    Required actions include a detailed inspection for discrepancies, 
including gaps between the fastener head and structure, traces of 
movement, and deformation of the structure. You may examine the MCAI on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-9114.

Related Service Information Under 1 CFR Part 51

    We reviewed SAAB 2000 Service Bulletin 2000-54-035, Revision 01, 
dated August 12, 2016. The service information describes procedures for 
an inspection to identify the type of fasteners installed on the upper 
longerons and upper fittings of the EMS, and a detailed inspection of 
incorrect (blind) fasteners to detect discrepancies, and corrective 
actions. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
discrepancies of blind fasteners could cause crack development and 
vibration in the engine mount structure, which could lead to failure of 
the affected engine-mount-to-airplane structural connection and 
resultant detachment of an engine from the airplane when both sides of 
a nacelle are affected. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-9114; Directorate 
Identifier 2016-NM-146-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 8 airplanes of U.S. registry.
    We also estimate that it will take about 4 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $2,720, or $340 per product.
    We have received no definitive data that would enable us to provide 
cost

[[Page 66515]]

estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-20-05 Saab AB, Saab Aeronautics (Formerly Known as Saab AB, 
Saab Aerosystems): Amendment 39-18671; Docket No. FAA-2016-9114; 
Directorate Identifier 2016-NM-146-AD.

(a) Effective Date

    This AD becomes effective October 13, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Saab AB, Saab Aeronautics (formerly known 
as Saab AB, Saab Aerosystems) Model SAAB 2000 airplanes, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by the discovery of blind fasteners 
installed in engine mounting structure (EMS) upper fittings that do 
not meet the type design. We are issuing this AD to detect and 
correct discrepancies of blind fasteners that could cause crack 
development and vibration in the engine mount structure, which could 
lead to failure of the affected engine-mount-to-airplane structural 
connection and resultant detachment of an engine from the airplane 
when both sides of a nacelle are affected.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Fastener Identification

    Within 30 days or 150 flight hours after the effective date of 
this AD, whichever occurs first, do a general visual inspection of 
the upper longerons and upper fittings of the EMS to identify the 
type of fasteners installed, in accordance with the Accomplishment 
Instructions of SAAB 2000 Service Bulletin 2000-54-035, Revision 01, 
dated August 12, 2016.

(h) Inspection for Discrepancies

    For any fastener other than the fasteners specified in SAAB 2000 
Service Bulletin 2000-54-035, Revision 01, dated August 12, 2016, 
found during the inspection required by paragraph (g) of this AD: 
Before further flight, do a detailed inspection for discrepancies of 
those fasteners, including gaps between the fastener heads and 
structure, traces of movement, and deformation of the structure, in 
accordance with the Accomplishment Instructions of SAAB 2000 Service 
Bulletin 2000-54-035, Revision 01, dated August 12, 2016.

(i) Corrective Action

    (1) If, during the inspection as required by paragraph (h) of 
this AD, any gap between the fastener heads and structure, traces of 
movement, or deformation of the structure is found: Before further 
flight obtain repair instructions from the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Saab AB, Saab 
Aeronautics' EASA Design Organization Approval (DOA); and before 
further flight accomplish those instructions accordingly.
    (2) If all fasteners inspected as required by paragraph (h) of 
this AD are firmly attached, and no deformation of the structure is 
found: Within 30 days or 150 flight hours after the effective date 
of the AD, whichever occurs first, obtain repair instructions from 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Saab AB, Saab Aeronautics' EASA DOA; 
and at the applicable time required in the repair instructions, 
accomplish the repair accordingly.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using SAAB 2000 Service 
Bulletin 2000-54-035, dated July 22, 2016.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: 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: [email protected]. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Saab AB, Saab Aeronautics' EASA DOA. If approved by the DOA, the 
approval must include the DOA-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0171, dated August 22, 
2016, for related information. You may examine the MCAI on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-9114.
    (2) Service information identified in this AD that is not 
incorporated by reference is

[[Page 66516]]

available at the addresses specified in paragraphs (m)(3) and (m)(4) 
of this AD.

(m) 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 2000 Service Bulletin 2000-54-035, Revision 01, dated 
August 12, 2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact Saab 
AB, Saab Aeronautics, SE-581 88, Link[ouml]ping, Sweden; telephone 
+46 13 18 5591; fax +46 13 18 4874; email 
[email protected]; Internet http://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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 14, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-23081 Filed 9-27-16; 8:45 am]
 BILLING CODE 4910-13-P

66514 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations

• Federal eRulemaking Portal: Go to an unsafe condition for all Saab AB, referenced above. We are issuing this
http://www.regulations.gov. Follow the Saab Aeronautics Model SAAB 2000 AD because we evaluated all pertinent
instructions for submitting comments. airplanes. The MCAI states: information and determined the unsafe
• Fax: 202–493–2251. During inspections, blind fasteners were condition exists and is likely to exist or
• Mail: U.S. Department of found installed in engine mounting structure develop on other products of the same
Transportation, Docket Operations, M– (EMS) upper fittings, frame NS204.7 and type design.
30, West Building Ground Floor, Room upper longerons. The type design specifies
that the fasteners at this location must be Hi- FAA’s Determination of the Effective
W12–140, 1200 New Jersey Avenue SE.,
Lok fasteners and two solid rivets (monel). Date
Washington, DC 20590.
• Hand Delivery: U.S. Department of This condition, if not detected and An unsafe condition exists that
corrected, could cause cracks development, requires the immediate adoption of this
Transportation, Docket Operations, M– vibration in the engine mount structure,
30, West Building Ground Floor, Room AD. The FAA has found that the risk to
leading to failure of the affected engine
W12–140, 1200 New Jersey Avenue SE., mount-to-aeroplane structural connection, the flying public justifies waiving notice
Washington, DC, between 9 a.m. and 5 possibly resulting in detachment of an engine and comment prior to adoption of this
p.m., Monday through Friday, except from the aeroplane when affecting both sides rule because discrepancies of blind
Federal holidays. of a nacelle. fasteners could cause crack
For service information identified in To address this unsafe condition, SAAB development and vibration in the
this final rule, contact Saab AB, Saab issued Service Bulletin (SB) 2000–54–035 engine mount structure, which could
(hereafter referred to as ‘the SB’ in this lead to failure of the affected engine-
Aeronautics, SE–581 88, Linköping, [EASA] AD) to provide inspection
Sweden; telephone +46 13 18 5591; fax mount-to-airplane structural connection
instructions.
+46 13 18 4874; email For the reasons described above, this
and resultant detachment of an engine
saab2000.techsupport@saabgroup.com; [EASA] AD requires a one-time * * * from the airplane when both sides of a
Internet http://www.saabgroup.com. [general] visual inspection of the affected nacelle are affected. Therefore, we
You may view this referenced service areas to determine which type(s) of fasteners determined that notice and opportunity
information at the FAA, Transport are installed, and, depending on findings, for public comment before issuing this
Airplane Directorate, 1601 Lind Avenue accomplishment of applicable corrective AD are impracticable and that good
SW., Renton, WA. For information on action(s) [repair or additional actions as cause exists for making this amendment
applicable]. This [EASA] AD also requires effective in fewer than 30 days.
the availability of this material at the reporting of all inspection results to SAAB.
FAA, call 425–227–1221. It is also This [EASA] AD is considered an interim Comments Invited
available on the Internet at http:// action and further AD action may follow.
www.regulations.gov by searching for This AD is a final rule that involves
and locating Docket No. FAA–2016– Required actions include a detailed requirements affecting flight safety, and
9114. inspection for discrepancies, including we did not precede it by notice and
gaps between the fastener head and opportunity for public comment. We
Examining the AD Docket structure, traces of movement, and invite you to send any written relevant
You may examine the AD docket on deformation of the structure. You may data, views, or arguments about this AD.
the Internet at http:// examine the MCAI on the Internet at Send your comments to an address
www.regulations.gov by searching for http://www.regulations.gov by searching listed under the ADDRESSES section.
and locating Docket No. FAA–2016– for and locating Docket No. FAA–2016– Include ‘‘Docket No. FAA–2016–9114;
9114; or in person at the Docket 9114. Directorate Identifier 2016–NM–146–
Operations office between 9 a.m. and 5 Related Service Information Under 1 AD’’ at the beginning of your comments.
p.m., Monday through Friday, except CFR Part 51 We specifically invite comments on the
Federal holidays. The AD docket overall regulatory, economic,
We reviewed SAAB 2000 Service environmental, and energy aspects of
contains this AD, the regulatory
Bulletin 2000–54–035, Revision 01, this AD. We will consider all comments
evaluation, any comments received, and
dated August 12, 2016. The service received by the closing date and may
other information. The street address for
information describes procedures for an amend this AD based on those
the Docket Operations office (telephone
inspection to identify the type of comments.
800–647–5527) is in the ADDRESSES
fasteners installed on the upper We will post all comments we
section. Comments will be available in
longerons and upper fittings of the EMS, receive, without change, to http://
the AD docket shortly after receipt.
and a detailed inspection of incorrect www.regulations.gov, including any
FOR FURTHER INFORMATION CONTACT: (blind) fasteners to detect discrepancies, personal information you provide. We
Shahram Daneshmandi, Aerospace and corrective actions. This service will also post a report summarizing each
Engineer, International Branch, ANM– information is reasonably available substantive verbal contact we receive
116, Transport Airplane Directorate, because the interested parties have about this AD.
FAA, 1601 Lind Avenue SW., Renton, access to it through their normal course
WA 98057–3356; telephone 425–227– of business or by the means identified Costs of Compliance
1112; fax 425–227–1149. in the ADDRESSES section. We estimate that this AD affects 8
SUPPLEMENTARY INFORMATION: airplanes of U.S. registry.
FAA’s Determination and Requirements We also estimate that it will take
Discussion of This AD about 4 work-hours per product to
The European Aviation Safety Agency This product has been approved by comply with the basic requirements of
sradovich on DSK3GMQ082PROD with RULES

(EASA), which is the Technical Agent the aviation authority of another this AD. The average labor rate is $85
for the Member States of the European country, and is approved for operation per work-hour. Based on these figures,
Union, has issued EASA Airworthiness in the United States. Pursuant to our we estimate the cost of this AD on U.S.
Directive 2016–0171, dated August 22, bilateral agreement with the State of operators to be $2,720, or $340 per
2016 (referred to after this as the Design Authority, we have been notified product.
Mandatory Continuing Airworthiness of the unsafe condition described in the We have received no definitive data
Information, or ‘‘the MCAI’’), to correct MCAI and service information that would enable us to provide cost

VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1

Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 66515

estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701. the fastener heads and structure, traces of
specified in this AD. movement, or deformation of the structure is
§ 39.13 [Amended] found: Before further flight obtain repair
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by adding instructions from the Manager, International
Title 49 of the United States Code the following new airworthiness Branch, ANM–116, Transport Airplane
directive (AD): Directorate, FAA; or the European Aviation
specifies the FAA’s authority to issue Safety Agency (EASA); or Saab AB, Saab
rules on aviation safety. Subtitle I, 2016–20–05 Saab AB, Saab Aeronautics Aeronautics’ EASA Design Organization
section 106, describes the authority of (Formerly Known as Saab AB, Saab Approval (DOA); and before further flight
the FAA Administrator. ‘‘Subtitle VII: Aerosystems): Amendment 39–18671; accomplish those instructions accordingly.
Aviation Programs,’’ describes in more Docket No. FAA–2016–9114; Directorate (2) If all fasteners inspected as required by
detail the scope of the Agency’s Identifier 2016–NM–146–AD. paragraph (h) of this AD are firmly attached,
authority. (a) Effective Date and no deformation of the structure is found:
We are issuing this rulemaking under Within 30 days or 150 flight hours after the
This AD becomes effective October 13,
the authority described in ‘‘Subtitle VII, effective date of the AD, whichever occurs
2016.
first, obtain repair instructions from the
Part A, Subpart III, Section 44701:
(b) Affected ADs Manager, International Branch, ANM–116,
General requirements.’’ Under that Transport Airplane Directorate, FAA; or
section, Congress charges the FAA with None.
EASA; or Saab AB, Saab Aeronautics’ EASA
promoting safe flight of civil aircraft in (c) Applicability DOA; and at the applicable time required in
air commerce by prescribing regulations This AD applies to all Saab AB, Saab the repair instructions, accomplish the repair
for practices, methods, and procedures Aeronautics (formerly known as Saab AB, accordingly.
the Administrator finds necessary for Saab Aerosystems) Model SAAB 2000 (j) Credit for Previous Actions
safety in air commerce. This regulation airplanes, certificated in any category.
This paragraph provides credit for actions
is within the scope of that authority (d) Subject required by paragraphs (g) and (h) of this AD,
because it addresses an unsafe condition if those actions were performed before the
Air Transport Association (ATA) of
that is likely to exist or develop on America Code 54, Nacelles/pylons. effective date of this AD using SAAB 2000
products identified in this rulemaking Service Bulletin 2000–54–035, dated July 22,
action. (e) Reason 2016.
This AD was prompted by the discovery of
Regulatory Findings blind fasteners installed in engine mounting (k) Other FAA AD Provisions
We determined that this AD will not structure (EMS) upper fittings that do not The following provisions also apply to this
have federalism implications under meet the type design. We are issuing this AD AD:
to detect and correct discrepancies of blind (1) Alternative Methods of Compliance
Executive Order 13132. This AD will fasteners that could cause crack development (AMOCs): The Manager, International
not have a substantial direct effect on and vibration in the engine mount structure, Branch, ANM–116, FAA, has the authority to
the States, on the relationship between which could lead to failure of the affected approve AMOCs for this AD, if requested
the national government and the States, engine-mount-to-airplane structural using the procedures found in 14 CFR 39.19.
or on the distribution of power and connection and resultant detachment of an In accordance with 14 CFR 39.19, send your
responsibilities among the various engine from the airplane when both sides of request to your principal inspector or local
levels of government. a nacelle are affected. Flight Standards District Office, as
For the reasons discussed above, I (f) Compliance appropriate. If sending information directly
certify that this AD: to the International Branch, send it to ATTN:
Comply with this AD within the Shahram Daneshmandi, Aerospace Engineer,
1. Is not a ‘‘significant regulatory compliance times specified, unless already International Branch, ANM–116, Transport
action’’ under Executive Order 12866; done. Airplane Directorate, FAA, 1601 Lind
2. Is not a ‘‘significant rule’’ under the (g) Fastener Identification Avenue SW., Renton, WA 98057–3356;
DOT Regulatory Policies and Procedures telephone 425–227–1112; fax 425–227–1149.
Within 30 days or 150 flight hours after the
(44 FR 11034, February 26, 1979); effective date of this AD, whichever occurs Information may be emailed to: 9-ANM-116-
3. Will not affect intrastate aviation in first, do a general visual inspection of the AMOC-REQUESTS@faa.gov. Before using
Alaska; and upper longerons and upper fittings of the any approved AMOC, notify your appropriate
4. Will not have a significant EMS to identify the type of fasteners principal inspector, or lacking a principal
economic impact, positive or negative, installed, in accordance with the inspector, the manager of the local flight
Accomplishment Instructions of SAAB 2000 standards district office/certificate holding
on a substantial number of small entities
Service Bulletin 2000–54–035, Revision 01, district office.
under the criteria of the Regulatory (2) Contacting the Manufacturer: For any
Flexibility Act. dated August 12, 2016.
requirement in this AD to obtain corrective
(h) Inspection for Discrepancies actions from a manufacturer, the action must
List of Subjects in 14 CFR Part 39
For any fastener other than the fasteners be accomplished using a method approved
Air transportation, Aircraft, Aviation specified in SAAB 2000 Service Bulletin by the Manager, International Branch, ANM–
safety, Incorporation by reference, 2000–54–035, Revision 01, dated August 12, 116, Transport Airplane Directorate, FAA; or
Safety. 2016, found during the inspection required EASA; or Saab AB, Saab Aeronautics’ EASA
by paragraph (g) of this AD: Before further DOA. If approved by the DOA, the approval
Adoption of the Amendment flight, do a detailed inspection for must include the DOA-authorized signature.
Accordingly, under the authority discrepancies of those fasteners, including
(l) Related Information
delegated to me by the Administrator, gaps between the fastener heads and
structure, traces of movement, and (1) Refer to Mandatory Continuing
the FAA amends 14 CFR part 39 as
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deformation of the structure, in accordance Airworthiness Information (MCAI) EASA
follows: with the Accomplishment Instructions of Airworthiness Directive 2016–0171, dated
SAAB 2000 Service Bulletin 2000–54–035, August 22, 2016, for related information. You
PART 39—AIRWORTHINESS Revision 01, dated August 12, 2016. may examine the MCAI on the Internet at
DIRECTIVES http://www.regulations.gov by searching for
(i) Corrective Action and locating Docket No. FAA–2016–9114.
■ 1. The authority citation for part 39 (1) If, during the inspection as required by (2) Service information identified in this
continues to read as follows: paragraph (h) of this AD, any gap between AD that is not incorporated by reference is

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66516 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations

available at the addresses specified in and fuselage skin surface, corrective part 39 by adding an AD that would
paragraphs (m)(3) and (m)(4) of this AD. actions if necessary, and relocating the apply to certain Bombardier, Inc. Model
(m) Material Incorporated by Reference existing thermostats. We are issuing this DHC–8–400 series airplanes. The NPRM
(1) The Director of the Federal Register AD to prevent corrosion within the published in the Federal Register on
approved the incorporation by reference thermostats that might cause the switch May 2, 2016 (81 FR 26176) (‘‘the
(IBR) of the service information listed in this mechanism to seize in the open position NPRM’’).
paragraph under 5 U.S.C. 552(a) and 1 CFR and prevent the activation of the Transport Canada Civil Aviation
part 51. associated engine air intake heater. An (TCCA), which is the aviation authority
(2) You must use this service information inactive engine air intake heater could for Canada, has issued Canadian
as applicable to do the actions required by lead to an engine failure. Airworthiness Directive CF–2015–24,
this AD, unless this AD specifies otherwise. dated August 24, 2015 (referred to after
(i) SAAB 2000 Service Bulletin 2000–54– DATES: This AD is effective November 2,
035, Revision 01, dated August 12, 2016. 2016. this as the Mandatory Continuing
(ii) Reserved. The Director of the Federal Register Airworthiness Information, or ‘‘the
(3) For service information identified in approved the incorporation by reference MCAI’’), to correct an unsafe condition
this AD, contact Saab AB, Saab Aeronautics, of a certain publication listed in this AD for certain Bombardier, Inc. Model
SE–581 88, Linköping, Sweden; telephone as of November 2, 2016. DHC–8–400 series airplanes. The MCAI
+46 13 18 5591; fax +46 13 18 4874; email ADDRESSES: For service information states:
saab2000.techsupport@saabgroup.com;
Internet http://www.saabgroup.com. identified in this final rule, contact A malfunctioning Engine Air Intake Heater
(4) You may view this service information Bombardier, Inc., Q-Series Technical has been discovered with corrosion on the
at the FAA, Transport Airplane Directorate, Help Desk, 123 Garratt Boulevard, thermostats and the aeroplane skin where the
1601 Lind Avenue SW., Renton, WA. For Toronto, Ontario M3K 1Y5, Canada; thermostats are installed. The two
information on the availability of this telephone: 416–375–4000; fax: 416– thermostats are installed directly under the
material at the FAA, call 425–227–1221. flight compartment floor along the aeroplane
375–4539; email: thd.qseries@ centre line where moisture accumulation
(5) You may view this service information aero.bombardier.com; Internet: http://
that is incorporated by reference at the and/or migration may occur, which can cause
www.bombardier.com. You may view corrosion of the thermostats. Corrosion
National Archives and Records
this referenced service information at within the thermostats may seize the switch
Administration (NARA). For information on
the availability of this material at NARA, call the FAA, Transport Airplane mechanism open, preventing the activation
202–741–6030, or go to: http:// Directorate, 1601 Lind Avenue SW., of the associated Engine Air Intake Heater.
www.archives.gov/federal-register/cfr/ibr- Renton, WA. For information on the Failure of the Engine Air Intake Heater to
locations.html. availability of this material at the FAA, activate may pose a safety risk to the
call 425–227–1221. It is also available aeroplane in icing conditions.
Issued in Renton, Washington, on Bombardier has issued Service Bulletin
September 14, 2016. on the Internet at http:// (SB) 84–30–10 to inspect, replace if required
Michael Kaszycki, www.regulations.gov by searching for and relocate the thermostat assembly to
and locating Docket No. FAA–2016– rectify this problem. [An inactive engine air
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. 6148. intake heater could lead to an engine failure.]
[FR Doc. 2016–23081 Filed 9–27–16; 8:45 am] Examining the AD Docket You may examine the MCAI in the
BILLING CODE 4910–13–P You may examine the AD docket on AD docket on the Internet at http://
the Internet at http:// www.regulations.gov by searching for
www.regulations.gov by searching for and locating Docket No. FAA–2016–
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2016– 6148.
Federal Aviation Administration 6148; or in person at the Docket Comments
Management Facility between 9 a.m.
We gave the public the opportunity to
14 CFR Part 39 and 5 p.m., Monday through Friday,
participate in developing this AD. We
except Federal holidays. The AD docket
[Docket No. FAA–2016–6148; Directorate received no comments on the NPRM or
contains this AD, the regulatory
Identifier 2015–NM–154–AD; Amendment on the determination of the cost to the
evaluation, any comments received, and
39–18660; AD 2016–19–11] public.
other information. The street address for
RIN 2120–AA64 the Docket Office (telephone 800–647– Conclusion
5527) is Docket Management Facility, We reviewed the relevant data and
Airworthiness Directives; Bombardier, U.S. Department of Transportation, determined that air safety and the
Inc. Airplanes Docket Operations, M–30, West public interest require adopting this AD
AGENCY: Federal Aviation Building Ground Floor, Room W12–140, as proposed except for minor editorial
Administration (FAA), Department of 1200 New Jersey Avenue SE., changes. We have determined that these
Transportation (DOT). Washington, DC 20590. minor changes:
ACTION: Final rule. FOR FURTHER INFORMATION CONTACT: • Are consistent with the intent that
Assata Dessaline, Aerospace Engineer, was proposed in the NPRM for
SUMMARY: We are adopting a new Avionics and Services Branch, ANE– correcting the unsafe condition; and
airworthiness directive (AD) for certain 172, FAA, New York Aircraft • Do not add any additional burden
Bombardier, Inc. Model DHC–8–400 Certification Office (ACO), 1600 Stewart upon the public than was already
series airplanes. This AD was prompted Avenue, Suite 410, Westbury, NY proposed in the NPRM.
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by a malfunctioning No. 2 engine intake 11590; telephone 516–228–7301; fax
heater with corrosion on the thermostats 516–794–5531. Related Service Information Under 1
and the fuselage skin where the CFR Part 51
SUPPLEMENTARY INFORMATION:
thermostats made contact with the Bombardier, Inc. has issued
aircraft fuselage skin. This AD requires Discussion Bombardier Service Bulletin 84–30–10,
a general visual inspection for corrosion We issued a notice of proposed Revision E, dated October 10, 2014. The
of the thermostats’ mounting surfaces rulemaking (NPRM) to amend 14 CFR service information describes

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Document Created: 2016-09-28 01:07:48
Document Modified: 2016-09-28 01:07:48

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule; request for comments.
Dates		This AD becomes effective October 13, 2016.
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.
FR Citation		81 FR 66513
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

81 FR 66513 - Airworthiness Directives; Saab AB, Saab Aeronautics (Formerly Known as Saab AB, Saab Aerosystems) Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 188 (September 28, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration