(a) EFFECTIVE DATE
This airworthiness directive (AD) becomes effective October 22, 2014.
(b) AFFECTED ADS
This AD supersedes AD 2013-22-20, Amendment 39-17652 (78 FR 67018,
November 8, 2013).
(c) APPLICABILITY
This AD applies to Embraer S.A. Models EMB-505 airplanes, all serial
numbers, that are:
(1) Equipped with a part number (P/N) DAP00097-01 or P/N DAP00097-02 brake
assembly; and
(2) certificated in any category.
(d) SUBJECT
Air Transport Association of America (ATA) Code 32: Landing Gear.
(e) REASON
This AD was prompted by mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as cracks beyond acceptable limits
in the carbon discs of the left hand (LH) and right hand (RH) brake
assemblies. We are issuing this AD to detect and correct cracking of
the stator pressure plate and possible loss of brake parts on the
runway, which could result in reduced brake capability and a possible
runway excursion.
(f) ACTIONS AND COMPLIANCE
Unless already done, do the following actions in paragraphs (f)(1)
through (f)(14) of this AD, including all subparagraphs.
(1) If the number of flight cycles is unknown, calculate the compliance
times for flight cycles in this AD by multiplying the number of hours
time-in-service (TIS) on the brake assembly by .71 to come up with the
number of cycles. For the purposes of this AD, some examples are
below:
(i) 500 hours TIS equates to 355 flight cycles; and
(ii) 12 hours equates to 9 flight cycles.
(2) Do a general visual inspection (GVI) for cracks in the stator pressure
plate on both the LH and RH brake assemblies following Part 1 of the
Accomplishment Instructions in Embraer Phenom Service Bulletin No.
505-32-0011, Revision 01, dated March 31, 2014. Use the compliance
times in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD:
(i) For brake assemblies with 300 flight cycles or less since new or since
the last overhaul: Before or upon accumulating 150 flight cycles after
October 22, 2014 (the effective date of this AD) or within the next 30
flight cycles after October 22, 2014 (the effective date of this AD),
whichever occurs later, and repetitively thereafter at intervals not
to exceed 60 flight cycles or the next tire change, whichever occurs
first.
(ii) For brake assemblies with more than 300 flight cycles since new or
since the last overhaul: Within the next 10 flight cycles after
October 22, 2014 (the effective date of this AD), and repetitively
thereafter at intervals not to exceed 60 flight cycles or the next
tire change, whichever occurs first.
(3) If no cracks are found during any of the inspections required in para-
graph (f)(2) of this AD, continue the repetitive inspection intervals
required in paragraph (f)(2) of this AD, including all subparagraphs.
(4) If any crack is found in the stator pressure plate during any of the
inspections required in paragraph (f)(2) of this AD, before further
flight, do a detailed inspection (DET) following Part 1 of the
Accomplishment Instructions in Embraer Phenom Service Bulletin No.
505-32-0011, Revision 01, dated March 31, 2014.
(5) If no cracks beyond the acceptable limits are found during the DET
required in paragraph (f)(4) of this AD, continue the repetitive
inspection intervals required in paragraph (f)(2) of this AD, in-
cluding all subparagraphs.
(6) If cracks that exceed the acceptable limits are found during the DET
required in paragraph (f)(4) of this AD, before further flight, repair
the brake assembly following Appendix 2 of Embraer Phenom Service
Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014; or
replace the brake assembly with a brake assembly that has been
inspected and found free of cracks that exceed the acceptable limits
following the Accomplishment Instructions of Embraer Phenom Service
Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014.
Note 1 to paragraph (f)(6) of this AD: Appendix 2 of Embraer Phenom
Service Bulletin No. 505-32-0011, Revision 01, dated March 31, 2014,
consists of Meggitt Aircraft Braking System Service Bulletin No. SB-32
-1625, Revision A, dated October 17, 2013. This service bulletin is
incorporated as pages 27 through 40 of Embraer Phenom Service Bulletin No.
505-32-0011, Revision 01, dated March 31, 2014.
(7) At the next tire change or 30 days after October 22, 2014 (the effec-
tive date of this AD), whichever occurs later, do a DET for cracks on
the external visible surface of the thrust stator, double stator, and
rotors following Part 2 of the Accomplishment Instructions in Embraer
Phenom Service Bulletin No. 505-32-0011, Revision 01, dated March 31,
2014.
(8) If no crack is detected or if any crack within the acceptable limits
shown in Figure 4 Detail G of Embraer Phenom Service Bulletin No. 505
-32-0011, Revision 01, dated March 31, 2014, is detected in the
inspection required in paragraph (f)(7) of this AD, repeat the
inspection required by paragraph (f)(7) of this AD at each tire change
or at each maintenance action that requires wheel removal, whichever
occurs first.
(9) If any crack within the acceptable limits shown in Figure 4 Detail H
of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated
March 31, 2014, is detected in the inspection required in paragraph
(f)(7) of this AD, the affected brake assembly must be replaced within
40 flight cycles.
(10) If any crack beyond the acceptable limits shown in Figure 4 Detail H
of Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01,
dated March 31, 2014, is detected, the affected brake assembly must
be replaced before the next flight.
(11) After any repair or replacement of the brake assembly, the brake
assembly P/N DAP00097-01 or P/N DAP00097-02 is subject to the in-
spections required in paragraphs (f)(2) through (f)(10), including
all subparagraphs as applicable, of this AD.
(12) For the purposes of this AD, a GVI is a visual examination of an
interior or exterior area, installation or assembly, to detect
obvious damage, failure, or irregularity. This level of inspection is
made from within touching distance, unless otherwise specified. A
mirror may be necessary to enhance visual access to all exposed
surfaces in the inspection area. This level of inspection is made
under normally available lighting conditions such as daylight, hangar
lighting, flashlight, or drop-light. It may require removal or
opening of access panels or doors. Stands, ladders, or platforms may
be required to gain proximity to the area being checked.
(13) For the purposes of this AD, a DET is an intensive examination of a
specific item, installation or assembly, to detect damage, failure,
or irregularity. Available lighting is normally supplemented with a
direct source of good lighting at an intensity deemed appropriate.
Inspection aids such as mirrors, magnifying lenses, etc., may be
necessary. Surface cleaning and elaborate access procedures may be
required.
(14) As of November 8, 2013 (the effective the date of AD 2013-22-20) and
to October 22, 2014 (the effective date of this AD), do not install
on any airplane a brake assembly P/N DAP00097-01 or P/N DAP00097-02
unless it is inspected per the requirements of AD 2013-22-20 and
continues to be crack free or the cracks do not exceed the allowable
limits; and as of October 22, 2014 (the effective date of this AD),
do not install on any airplane a brake assembly P/N DAP00097-01 or
P/N DAP00097-02 unless it is inspected per the requirements of this
AD and continues to be crack free or the cracks do not exceed the
allowable limits.
(g) CREDIT FOR ACTIONS DONE FOLLOWING PREVIOUS SERVICE INFORMATION
This AD provides credit for the inspections required in paragraphs
(f)(2) and (f)(6) of this AD, if those actions were performed before
October 22, 2014 (the effective date of this AD), using Embraer Alert
Service Bulletin (ASB) 505-32-A011, original issue, dated September
13, 2013; Embraer Alert Service Bulletin (ASB) 505-32-A011, Revision
01, dated November 01, 2013; Embraer Alert Service Bulletin (ASB) 505
-32-A011, Revision 02, dated December 19, 2013; or Embraer Phenom
Service Bulletin No. 505-32-0011, original issue, dated February 11,
2014.
(h) OTHER FAA AD PROVISIONS
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards
Office, FAA, has the authority to approve AMOCs for this AD, if re-
quested using the procedures found in 14 CFR 39.19. Send information
to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; tele-
phone: (816) 329-4165; fax: (816) 329-4090; email: jim.rutherford@faa.
gov. Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain corrective
actions from a manufacturer or other source, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they are approved by the State of Design Authority (or their delegated
agent). You are required to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, a
federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 5 minutes per response, including the time for reviewing
instructions, completing and reviewing the collection of information.
All responses to this collection of information are mandatory.
Comments concerning the accuracy of this burden and suggestions for
reducing the burden should be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(i) RELATED INFORMATION
Refer to MCAI Agencia Nacional De Aviacao Civil (ANAC) AD No.: 2014-
04-01, dated April 16, 2014, for related information. The MCAI can be
found in the AD docket on the Internet at: http://www.regulations.gov/
#!documentDetail;D=FAA-2014-0390-0001.
(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) Embraer Phenom Service Bulletin No. 505-32-0011, Revision 01, dated
March 31, 2014.
(ii) Reserved.
(3) For Embraer S.A. service information identified in this AD, contact
EMBRAER S.A., Phenom Maintenance Support, Avenida Brigadeiro Faria
Lima, 2170, Sao Jose dos Campos-SP, CEP: 12227-901- PO Box: 36/2,
Brasil; telephone: (+55 12) 3927-1000; fax: (+55 12) 3927-6600, ext.
1448; email: phenom.reliability@embraer.com.br; Internet: http://www.
embraerexecutivejets.com/en-US/customer-support/Pages/Service-Center-
Network.aspx.
(4) You may view this service information at FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64106. For information
on the availability of this material at the FAA, call (816) 329-4148.
(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 Kansas City, Missouri, on September 8, 2014. Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: jim.ruther
ford@faa.gov.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0390; Directorate Identifier 2014-CE-013-AD;
Amendment 39-17969; AD 2014-19-01]
RIN 2120-AA64
Airworthiness Directives; Embraer S.A. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an airworthiness directive (AD) 2013-22-20
for Embraer S.A. Model EMB-505 airplanes. This AD results from
mandatory continuing airworthiness information (MCAI) issued by an
aviation authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as cracks beyond acceptable limits in the carbon discs of the
left hand (LH) and right hand (RH) brake assemblies. We are issuing
this AD to require actions to address the unsafe condition on these
products.
DATES: This AD is effective October 22, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 22,
2014.
ADDRESSES: You may examine the AD docket on the Internet at http://www.
regulations.gov by searching for and locating Docket No. FAA-2014-
0390; 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 20590.
For service information identified in this AD, contact EMBRAER
S.A., Phenom Maintenance Support, Avenida Brigadeiro Faria Lima, 2170,
Sao Jose dos Campos--SP, CEP: 12227-901--PO Box: 36/2,
Brasil; telephone: (+55 12) 3927-1000; fax: (+55 12) 3927-6600, ext.
1448; email: phenom.reliability@embraer.com.br; Internet: http://www.embraerexecutivejets.com/en-US/customer-support/Pages/
Service-Center-Network.aspx. You may view this referenced service information
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the availability of this material at
the FAA, call (816) 329-4148.
FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email:
jim.rutherford@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to add an AD that would apply to Embraer S.A. Model EMB-505
airplanes. The NPRM was published in the Federal Register on June 19,
2014 (79 FR 35099), and proposed to supersede AD 2013-22-20, Amendment
39-17652 (78 FR 67018, November 8, 2013).
The NPRM proposed to correct an unsafe condition for the specified
products and was based on mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country. The MCAI states that:
This AD was prompted by reports that identified additional
locations where inspections and corrective actions on the Left Hand
(LH) and Right Hand (RH) brake assemblies are needed. We are issuing
this AD to detect cracks beyond acceptable limit in the carbon discs
of the brake assembly, which may result in reduced brake capability
and loss of brake parts in the runway.
Since this condition may occur in other airplanes of the same
type and affects flight safety, a corrective action is required.
Thus, sufficient reason exists to request compliance with this AD in
the indicated time limit without prior notice.
The MCAI requires an inspection to determine if the airplane has the
affected part number brake assembly installed and an inspection for
cracks of the affected brake assembly with repair or replacement as
necessary. The MCAI can be found in the AD docket on the Internet at:
http://www.regulations.gov/#!documentDetail;D=FAA-0;2014-0390-0001.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 35099, June 19, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD will affect 117 products of U.S. registry.
We also estimate that it would take about 2 work-hours per product to
comply with Part 1 of the inspection and 3 work-hours per product to
comply with Part 2 of the inspection 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 $19,890, or $170
per product for Part 1 of the inspection, and $29,835, or $255 per
product for Part 2 of the inspection.
In addition, we estimate that any necessary follow-on actions would
take 1.5 work-hours and require parts costing $2,405, for a cost of
$2,532.50 per product per side for repair or 3 work-hours and require
parts costing $26,177, for a cost of $26,432 per product per side for
replacement.
We have no way of determining the number of products that may need
these actions.
According to the manufacturer, all of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 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 http://www.regulations.
gov by searching for and locating Docket No. FAA-2014-
0390; 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 the NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-17652 (78 FR
67018; November 8, 2013) and adding the following new AD:
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