Airworthiness Directives; Airbus Airplanes, 49091-49094 [2017-22949]
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Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Rules and Regulations
Consistency With Safety and Soundness
The agencies also have determined
that the exceptions are consistent with
safety and soundness, provided that the
depository institution determines and
maintains appropriate documentation of
the following: (1) The property involved
was located in the major disaster area;
(2) there is a binding commitment to
fund the transaction that was entered
into on or within 36 months of the date
that the area was declared a major
disaster; and (3) the value of the real
property supports the institution’s
decision to enter into the transaction. In
addition, the transaction must continue
to be subject to review by management
and by the agencies in the course of
examinations of the institution.
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Expiration Date
Exceptions made under section 1123
of FIRREA may be provided for no more
than three years after the President
determines a major disaster exists in an
area.11 The agencies have determined
that the exceptions provided for by this
order shall expire three years after the
date the President declared a major
disaster in each state or territory.
Order
In accordance with section 2 of
DIDRA, relief is hereby granted from the
provisions of Title XI of FIRREA and the
agencies’ appraisal regulations for any
real estate-related financial transaction
that requires the services of an appraiser
under those provisions, provided that
the institution determines each of the
following and maintains supporting
documentation made available to the
agencies upon request:
(1) The transaction involves real
property located in an area of a state or
territory that has been declared a major
disaster by the President as a result of
severe storms and flooding related to
Hurricanes Harvey, Irma, or Maria. The
specific areas covered are identified in
the Appendix and include:
a. The 39 counties in Texas under the
declaration of August 25, 2017 (as
amended); 12
b. The two islands in the U.S. Virgin
Islands under the declaration of
September 7, 2017; 13
c. The 48 counties in Florida under
the declaration of September 10, 2017
(as amended); 14
d. The four municipalities in Puerto
Rico under the declaration of September
10, 2017; 15
11 12
U.S.C. 3352(b).
https://www.fema.gov/disaster/4332.
13 See https://www.fema.gov/disaster/4335.
14 See https://www.fema.gov/disaster/4337.
15 See https://www.fema.gov/disaster/4336.
e. The three counties in Georgia under
the declaration of September 15,
2017; 16
f. The 54 municipalities in Puerto
Rico under the declaration of September
20, 2017; 17 and
g. The island in the U.S. Virgin
Islands under the declaration of
September 21, 2017.18
(2) There is a binding commitment to
fund a transaction that was entered into
on or after:
(a) August 25, 2017, but no later than
August 24, 2020, for areas declared a
major disaster in Texas as a result of
Hurricane Harvey;
(b) September 7, 2017, but no later
than September 6, 2020, for areas
declared a major disaster in the U.S.
Virgin Islands as a result of Hurricane
Irma;
(c) September 10, 2017, but no later
than September 9, 2020, for areas
declared a major disaster in Florida and
Puerto Rico as a result of Hurricane
Irma;
(d) September 15, 2017, but no later
than September 14, 2020, for areas
declared a major disaster in Georgia as
a result of Hurricane Irma;
(e) September 20, 2017, but no later
than September 19, 2020, for areas
declared a major disaster in Puerto Rico
as a result of Hurricane Maria; or
(f) September 21, 2017, but no later
than September 20, 2020, for areas
declared a major disaster in the U.S.
Virgin Islands as a result of Hurricane
Maria.
(3) The value of the real property
supports the institution’s decision to
enter into the transaction.
Appendix: Areas Declared a Major
Disaster
Hurricane Harvey
Texas: Aransas, Austin, Bastrop, Bee,
Brazoria, Calhoun, Chambers, Colorado,
DeWitt, Fayette, Fort Bend, Galveston,
Goliad, Gonzales, Hardin, Harris, Jackson,
Jasper, Jefferson, Karnes, Kleberg, Lavaca,
Lee, Liberty, Matagorda, Montgomery,
Newton, Nueces, Orange, Polk, Refugio,
Sabine, San Jacinto, San Patricio, Tyler,
Victoria, Walker, Waller, and Wharton
counties.
Hurricane Irma
Florida: Alachua, Baker, Bradford, Brevard,
Broward, Charlotte, Citrus, Clay, Collier,
Columbia, DeSoto, Dixie, Duval, Flagler,
Gilchrist, Glades, Hardee, Hendry, Hernando,
Highlands, Hillsborough, Indian River,
Lafayette, Lake, Lee, Levy, Manatee, Marion,
Martin, Miami-Dade, Monroe, Nassau,
Okeechobee, Orange, Osceola, Palm Beach,
Pasco, Pinellas, Polk, Putnam, Sarasota,
12 See
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16 See
https://www.fema.gov/disaster/4338.
https://www.fema.gov/disaster/4339.
18 See https://www.fema.gov/disaster/4340.
17 See
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49091
Seminole, St. Johns, St. Lucie, Sumter,
Suwannee, Union, and Volusia counties.
Georgia: Camden, Chatham, and Glynn
counties.
Puerto Rico: Canovanas, Culebra, Loiza,
and Vieques Municipalities.
U.S. Virgin Islands: St. John (Island), St.
Thomas (Island).
Hurricane Maria
U.S. Virgin Islands: St. Croix (Island).
Puerto Rico: Aguas Buenas, Aibonito,
Arecibo, Arroyo, Barceloneta, Barranquitas,
´
´
Bayamon, Caguas, Canovanas, Carolina,
˜
Catano, Cayey, Ceiba, Ciales, Cidra, Coamo,
Comerio, Corozal, Culebra, Dorado, Fajardo,
Florida, Guayama, Guaynabo, Gurabo,
´
Humacao, Jayuya, Juana Dıaz, Juncos, Las
´
Piedras, Loıza, Luquillo, Manati, Maunabo,
Morovis, Naguabo, Naranjito, Orocovis,
Patillas, Ponce, Rio Grande, Salinas, San
Juan, San Lorenzo, Santa Isabel, Toa Alta,
Toa Baja, Trujillo Alto, Utuado, Vega Alta,
Vega Baja, Vieques, Villalba, and Yabucoa
Municipalities.
Dated: October 6, 2017.
Keith A. Noreika,
Acting Comptroller of the Currency.
By order of the Board of Governors of the
Federal Reserve System, October 16, 2017.
Michele Taylor Fennell,
Assistant Secretary of the Board.
Dated at Washington, DC, this 12th day of
October, 2017.
By order of the Board of Directors.
Federal Deposit Insurance Corporation.
Robert E. Feldman,
Executive Secretary.
Dated at Alexandria, VA, this 16th day of
October, 2017.
By order of the Board of Directors.
National Credit Union Administration.
Gerard Poliquin,
Secretary of the Board.
[FR Doc. 2017–22957 Filed 10–23–17; 8:45 am]
BILLING CODE 4810–33–P; 6210–01–P; 6714–01–P;
7535–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6429; Product
Identifier 2015–NM–117–AD; Amendment
39–19083; AD 2017–22–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–05–
02, which applied to all Airbus Model
SUMMARY:
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A318 and A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. AD 2015–05–02
required revising the maintenance or
inspection program to incorporate new,
more restrictive airworthiness
limitations. This new AD requires
revising the maintenance or inspection
program to incorporate new or revised
structural inspection requirements and
adds airplanes to the applicability. This
AD was prompted by an evaluation by
the design approval holder (DAH),
which indicates that principal structural
elements and certain life-limited parts
are subject to widespread fatigue
damage (WFD). We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective November
28, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 28, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of March 2, 2015 (80 FR
3871, January 26, 2015).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6429.
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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–2016–
6429; 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 (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
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New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2015–05–02, Amendment 39–18112 (80
FR 15152, March 23, 2015) (‘‘AD 2015–
05–02’’). AD 2015–05–02 applied to all
Airbus Model A318 and A319 series
airplanes; Model A320–211, –212, –214,
–231, –232, and –233 airplanes; and
Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The SNPRM published in the Federal
Register on May 19, 2017 (82 FR 22910)
(‘‘the SNPRM’’). We preceded the
SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on May 11, 2016
(81 FR 29198) (‘‘the NPRM’’). The
NPRM was prompted by an evaluation
by the DAH, which indicates that
principal structural elements and
certain life limited parts are subject to
WFD. The NPRM proposed to require
revising the maintenance or inspection
program, as applicable, to incorporate
new or revised structural inspection
requirements. The SNPRM proposed to
require more restrictive airworthiness
limitations and add Model A320–251N
and –271N airplanes to the
applicability. We are issuing this AD to
prevent fatigue cracking, accidental
damage, or corrosion in principal
structural elements, and WFD, which
could result in reduced structural
integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0239, dated December 2,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition. The MCAI states:
The airworthiness limitations for Airbus
A320 family aeroplanes are currently
included in Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS)
documents. The Damage Tolerant
Airworthiness Limitation Items are published
in ALS Part 2, approved by EASA.
The instructions contained in the ALS Part
2 have been identified as mandatory actions
for continued airworthiness. Failure to
comply with these instructions could result
in an unsafe condition.
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Previously, EASA issued AD 2015–0083 to
require accomplishment of all maintenance
tasks as described in ALS Part 2 at Revision
03. Since that [EASA] AD was issued, Airbus
issued Revision 04, and later on Revision 05
of the ALS Part 2, including new and/or more
restrictive items, and new A320 models were
certified.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2015–0083, which is superseded,
expands the Applicability by adding the
models A320–251N and A320–271N,
requires accomplishment of all maintenance
tasks as described in the ALS Part 2, Revision
05 (hereafter referred to as ‘the ALS’ in this
[EASA] AD), and provides specific
compliance times for ALS task 572021–01–1
(Wide Spread Fatigue Damage related).
The required action is revising the
maintenance or inspection program to
incorporate new or revised structural
inspection requirements. The unsafe
condition is fatigue cracking, accidental
damage, or corrosion in principal
structural elements, and WFD, which
could result in reduced structural
integrity of the airplane. You may
examine the MCAI in the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6429.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the SNPRM and the FAA’s
response to the comment.
Request To Reference Revised Service
Information
American Airlines (AAL) requested
that we revise the SNPRM to
incorporate Airbus A318/A319/A320/
A321 ALS Part 1—Safe Life
Airworthiness Limitation Items (SL—
ALI), Revision 05, dated April 6, 2017,
including Variations 5.1 and 5.2; and
Airbus A318/A319/A320/A321 ALS
Part 2—Damage Tolerant Airworthiness
Limitation Items (DT—ALI), Revision
06, dated April 10, 2017.
We partially agree with AAL’s
request. We agree that operators should
use the latest service information, and
we agree to account for AAL’s request
in this AD. However, we do not agree
to require the revised service
information in this final rule since it
would expand the scope, requiring
additional notice and comment. We find
that delaying this action would be
inappropriate in light of the identified
unsafe condition. We are considering
further rulemaking to supersede this
final rule to require incorporating the
revised service information.
We have added paragraph (l)(1)(iii) to
this AD to specify that the previous
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alternative methods of compliance
(AMOCs) that are approved for AD
2015–05–02 are approved as AMOCs for
the corresponding provisions of
paragraphs (i) and (j) of this AD. The
previous AMOCs include Airbus A318/
A319/A320/A321 ALS Part 1—Safe Life
Airworthiness Limitation Items (SL—
ALI), Revision 05, dated April 6, 2017,
including Variations 5.1 and 5.2; and
Airbus A318/A319/A320/A321 ALS
Part 2—Damage Tolerant Airworthiness
Limitation Items (DT—ALI), Revision
06, dated April 10, 2017.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting this 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 SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
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Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation
Items (SL—ALI), Revision 04, dated
June 20, 2016. This service information
describes mandatory instructions and
airworthiness limitations for the ‘‘safelife’’ structure.
• A318/A319/A320/A321 ALS Part
2—Damage Tolerant Airworthiness
Limitation Items (DT—ALI), Revision
05, dated July 8, 2016. This service
information describes mandatory
instructions and airworthiness
limitations arising from fatigue and
damage tolerance evaluation of damage
tolerant structural elements.
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.
Costs of Compliance
We estimate that this AD affects 1,182
airplanes of U.S. registry.
The actions required by AD 2015–05–
02, and retained in this AD, take about
2 work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD
2015–05–02 is $170 per product.
We also estimate that it will take
about 2 work-hours per product to
comply with the basic requirements of
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49093
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 $200,940, or $170 per
product.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
Adoption of the Amendment
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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.
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–05–02, Amendment 39–18112 (80
FR 15152, March 23, 2015), and adding
the following new AD:
■
2017–22–03 Airbus Amendment 39–19083;
Docket No. FAA–2016–6429; Product
Identifier 2015–NM–117–AD.
(a) Effective Date
This AD is effective November 28, 2017.
(b) Affected ADs
This AD replaces AD 2015–05–02,
Amendment 39–18112 (80 FR 15152, March
23, 2015) (‘‘AD 2015–05–02’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, with
an original certificate of airworthiness or
original export certificate of airworthiness
issued on or before July 8, 2016.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –216,
–231, –232, –233, –251N, and –271N
airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic Inspections.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder which indicates
that principal structural elements and certain
life-limited parts are subject to widespread
fatigue damage (WFD). We are issuing this
AD to prevent fatigue cracking, accidental
damage, or corrosion in principal structural
elements, and WFD, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Maintenance or Inspection
Program Revision, With No Changes
This paragraph restates the requirements of
paragraph (n) of AD 2015–05–02, with no
changes. Within 30 days after March 2, 2015
(the effective date of AD 2014–23–15,
Amendment 39–18031 (80 FR 3871, January
26, 2015) (‘‘AD 2014–23–15’’)), revise the
maintenance or inspection program, as
applicable, to incorporate the Airworthiness
Limitation Items (ALIs) specified in
paragraphs (g)(1) and (g)(2) of this AD. The
initial compliance time for accomplishing the
actions is at the applicable time identified in
the ALIs specified in paragraphs (g)(1) and
(g)(2) of this AD; or within 4 months after
March 2, 2015 (the effective date of AD 2014–
23–15); whichever occurs later.
(1) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
1—Safe Life Airworthiness Limitation Items,
Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated
May 28, 2013.
(h) Retained Limitation: No Alternative
Actions, Intervals, and/or Critical Design
Configuration Control Limitations (CDCCLs),
With an Exception
This paragraph restates the requirements of
paragraph (o) of AD 2015–05–02, with an
exception. Except as specified in paragraph
(i) or (j) of this AD, as applicable, after
accomplishing the revision required by
paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, and/or
CDCCLs may be used unless the actions,
intervals, and/or CDCCLs are approved as an
alternative method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (l)(1) of this AD.
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(i) New Maintenance or Inspection Program
Revision
Within 60 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
ALIs specified in Airbus A318/A319/A320/
A321 ALS Part 2—Damage Tolerant
Airworthiness Limitation Items (DT—ALI),
Revision 05, dated July 8, 2016. The initial
compliance time for accomplishing the
actions is at the applicable time identified in
the ALIs specified in Airbus A318/A319/
A320/A321 ALS Part 2—DT—ALI, Revision
05, dated July 8, 2016, without exceeding the
inspection intervals in the ALIs specified in
the service information identified in
paragraph (g)(2) of this AD. Accomplishing
this action terminates the requirements of
paragraph (g)(2) of this AD.
(j) New Method of Compliance for
Maintenance or Inspection Program
Revision
Revising the maintenance or inspection
program, as applicable, to incorporate the
ALIs specified in Airbus A318/A319/A320/
A321 ALS Part 1—Safe Life Airworthiness
Limitation Items (SL—ALI), Revision 04,
dated June 20, 2016, is a method of
compliance for the actions required by
paragraph (g)(1) of this AD. The initial
compliance time for accomplishing the
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actions is at the applicable time identified in
the ALIs specified in Airbus A318/A319/
A320/A321 ALS Part 1—SL—ALI, Revision
04, dated June 20, 2016, without exceeding
the inspection intervals in the ALIs specified
in the service information identified in
paragraph (g)(1) of this AD. Accomplishing
this action terminates the requirements of
paragraph (g)(1) of this AD.
(k) New No Alternative Actions and/or
Intervals
After accomplishing the revision required
by paragraph (i) or specified in paragraph (j)
of this AD, no alternative actions (e.g.,
inspections) and/or intervals may be used
unless the actions and/or intervals are
approved as an AMOC in accordance with
the procedures specified in paragraph (l)(1)
of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2015–05–02, are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (h) of this AD.
(iii) AMOCs approved previously for AD
2015–05–02, which are included in the FAA
AMOC letters specified in paragraphs
(l)(1)(iii)(A) and (l)(1)(iii)(B), are approved as
AMOCs for the corresponding provisions of
paragraphs (i) and (j) of this AD.
(A) FAA AMOC letter ANM–116–17–
002R1, dated November 14, 2016.
(B) FAA AMOC letter ANM–116–17–323,
dated June 12, 2017.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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 Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0239, dated
December 2, 2016, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
PO 00000
Frm 00008
Fmt 4700
Sfmt 9990
by searching for and locating Docket No.
FAA–2016–6429.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–1405; fax 425–227–1149.
(n) 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.
(3) The following service information was
approved for IBR on November 28, 2017.
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
1—Safe Life—Airworthiness Limitation Items
(SL—ALI), Revision 04, dated June 20, 2016.
(ii) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
2—Damage Tolerant Airworthiness
Limitation Items (DT—ALI), Revision 05,
dated July 8, 2016.
(4) The following service information was
approved for IBR on March 2, 2015 (80 FR
3871, January 26, 2015).
(i) Airbus A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation Items,
Revision 02, dated May 13, 2011. The
revision level of this document is identified
on only the title page and in the Record of
Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated
May 28, 2013. The revision date of this
document is not identified on the title page
of this document.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(6) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) 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.
Issued in Renton, Washington, on October
11, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–22949 Filed 10–23–17; 8:45 am]
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]]>Agencies
[Federal Register Volume 82, Number 204 (Tuesday, October 24, 2017)]
[Rules and Regulations]
[Pages 49091-49094]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22949]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6429; Product Identifier 2015-NM-117-AD; Amendment
39-19083; AD 2017-22-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-05-02,
which applied to all Airbus Model
[[Page 49092]]
A318 and A319 series airplanes; Model A320-211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. AD 2015-05-02 required revising the
maintenance or inspection program to incorporate new, more restrictive
airworthiness limitations. This new AD requires revising the
maintenance or inspection program to incorporate new or revised
structural inspection requirements and adds airplanes to the
applicability. This AD was prompted by an evaluation by the design
approval holder (DAH), which indicates that principal structural
elements and certain life-limited parts are subject to widespread
fatigue damage (WFD). We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 28, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 28,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
2, 2015 (80 FR 3871, January 26, 2015).
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; Internet
https://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6429.
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-2016-
6429; 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 (telephone 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2015-05-02, Amendment 39-18112 (80
FR 15152, March 23, 2015) (``AD 2015-05-02''). AD 2015-05-02 applied to
all Airbus Model A318 and A319 series airplanes; Model A320-211, -212,
-214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The SNPRM published in the
Federal Register on May 19, 2017 (82 FR 22910) (``the SNPRM''). We
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on May 11, 2016 (81 FR 29198) (``the
NPRM''). The NPRM was prompted by an evaluation by the DAH, which
indicates that principal structural elements and certain life limited
parts are subject to WFD. The NPRM proposed to require revising the
maintenance or inspection program, as applicable, to incorporate new or
revised structural inspection requirements. The SNPRM proposed to
require more restrictive airworthiness limitations and add Model A320-
251N and -271N airplanes to the applicability. We are issuing this AD
to prevent fatigue cracking, accidental damage, or corrosion in
principal structural elements, and WFD, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0239, dated December 2, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition. The MCAI states:
The airworthiness limitations for Airbus A320 family aeroplanes
are currently included in Airbus A318/A319/A320/A321 Airworthiness
Limitations Section (ALS) documents. The Damage Tolerant
Airworthiness Limitation Items are published in ALS Part 2, approved
by EASA.
The instructions contained in the ALS Part 2 have been
identified as mandatory actions for continued airworthiness. Failure
to comply with these instructions could result in an unsafe
condition.
Previously, EASA issued AD 2015-0083 to require accomplishment
of all maintenance tasks as described in ALS Part 2 at Revision 03.
Since that [EASA] AD was issued, Airbus issued Revision 04, and
later on Revision 05 of the ALS Part 2, including new and/or more
restrictive items, and new A320 models were certified.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2015-0083, which is superseded, expands the
Applicability by adding the models A320-251N and A320-271N, requires
accomplishment of all maintenance tasks as described in the ALS Part
2, Revision 05 (hereafter referred to as `the ALS' in this [EASA]
AD), and provides specific compliance times for ALS task 572021-01-1
(Wide Spread Fatigue Damage related).
The required action is revising the maintenance or inspection
program to incorporate new or revised structural inspection
requirements. The unsafe condition is fatigue cracking, accidental
damage, or corrosion in principal structural elements, and WFD, which
could result in reduced structural integrity of the airplane. You may
examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6429.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the SNPRM and
the FAA's response to the comment.
Request To Reference Revised Service Information
American Airlines (AAL) requested that we revise the SNPRM to
incorporate Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items (SL--ALI), Revision 05, dated April 6,
2017, including Variations 5.1 and 5.2; and Airbus A318/A319/A320/A321
ALS Part 2--Damage Tolerant Airworthiness Limitation Items (DT--ALI),
Revision 06, dated April 10, 2017.
We partially agree with AAL's request. We agree that operators
should use the latest service information, and we agree to account for
AAL's request in this AD. However, we do not agree to require the
revised service information in this final rule since it would expand
the scope, requiring additional notice and comment. We find that
delaying this action would be inappropriate in light of the identified
unsafe condition. We are considering further rulemaking to supersede
this final rule to require incorporating the revised service
information.
We have added paragraph (l)(1)(iii) to this AD to specify that the
previous
[[Page 49093]]
alternative methods of compliance (AMOCs) that are approved for AD
2015-05-02 are approved as AMOCs for the corresponding provisions of
paragraphs (i) and (j) of this AD. The previous AMOCs include Airbus
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation
Items (SL--ALI), Revision 05, dated April 6, 2017, including Variations
5.1 and 5.2; and Airbus A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitation Items (DT--ALI), Revision 06, dated April 10,
2017.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this 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
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness
Limitation Items (SL--ALI), Revision 04, dated June 20, 2016. This
service information describes mandatory instructions and airworthiness
limitations for the ``safe-life'' structure.
A318/A319/A320/A321 ALS Part 2--Damage Tolerant
Airworthiness Limitation Items (DT--ALI), Revision 05, dated July 8,
2016. This service information describes mandatory instructions and
airworthiness limitations arising from fatigue and damage tolerance
evaluation of damage tolerant structural elements.
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.
Costs of Compliance
We estimate that this AD affects 1,182 airplanes of U.S. registry.
The actions required by AD 2015-05-02, and retained in this AD,
take about 2 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2015-05-02 is $170 per product.
We also estimate that it will take about 2 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 $200,940, or $170 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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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 removing Airworthiness Directive (AD)
2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), and
adding the following new AD:
2017-22-03 Airbus Amendment 39-19083; Docket No. FAA-2016-6429;
Product Identifier 2015-NM-117-AD.
(a) Effective Date
This AD is effective November 28, 2017.
(b) Affected ADs
This AD replaces AD 2015-05-02, Amendment 39-18112 (80 FR 15152,
March 23, 2015) (``AD 2015-05-02'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, with
an original certificate of airworthiness or original export
certificate of airworthiness issued on or before July 8, 2016.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N,
and -271N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
Inspections.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder which indicates that principal structural elements and
certain life-limited parts are subject to widespread fatigue damage
(WFD). We are issuing this AD to prevent fatigue cracking,
accidental damage, or corrosion in principal structural elements,
and WFD, which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 49094]]
(g) Retained Maintenance or Inspection Program Revision, With No
Changes
This paragraph restates the requirements of paragraph (n) of AD
2015-05-02, with no changes. Within 30 days after March 2, 2015 (the
effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871,
January 26, 2015) (``AD 2014-23-15'')), revise the maintenance or
inspection program, as applicable, to incorporate the Airworthiness
Limitation Items (ALIs) specified in paragraphs (g)(1) and (g)(2) of
this AD. The initial compliance time for accomplishing the actions
is at the applicable time identified in the ALIs specified in
paragraphs (g)(1) and (g)(2) of this AD; or within 4 months after
March 2, 2015 (the effective date of AD 2014-23-15); whichever
occurs later.
(1) Airbus A318/A319/A320/A321 Airworthiness Limitations Section
(ALS) Part 1--Safe Life Airworthiness Limitation Items, Revision 02,
dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013.
(h) Retained Limitation: No Alternative Actions, Intervals, and/or
Critical Design Configuration Control Limitations (CDCCLs), With an
Exception
This paragraph restates the requirements of paragraph (o) of AD
2015-05-02, with an exception. Except as specified in paragraph (i)
or (j) of this AD, as applicable, after accomplishing the revision
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections), intervals, and/or CDCCLs may be used unless the
actions, intervals, and/or CDCCLs are approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (l)(1) of this AD.
(i) New Maintenance or Inspection Program Revision
Within 60 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2--Damage
Tolerant Airworthiness Limitation Items (DT--ALI), Revision 05,
dated July 8, 2016. The initial compliance time for accomplishing
the actions is at the applicable time identified in the ALIs
specified in Airbus A318/A319/A320/A321 ALS Part 2--DT--ALI,
Revision 05, dated July 8, 2016, without exceeding the inspection
intervals in the ALIs specified in the service information
identified in paragraph (g)(2) of this AD. Accomplishing this action
terminates the requirements of paragraph (g)(2) of this AD.
(j) New Method of Compliance for Maintenance or Inspection Program
Revision
Revising the maintenance or inspection program, as applicable,
to incorporate the ALIs specified in Airbus A318/A319/A320/A321 ALS
Part 1--Safe Life Airworthiness Limitation Items (SL--ALI), Revision
04, dated June 20, 2016, is a method of compliance for the actions
required by paragraph (g)(1) of this AD. The initial compliance time
for accomplishing the actions is at the applicable time identified
in the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 1--SL--
ALI, Revision 04, dated June 20, 2016, without exceeding the
inspection intervals in the ALIs specified in the service
information identified in paragraph (g)(1) of this AD. Accomplishing
this action terminates the requirements of paragraph (g)(1) of this
AD.
(k) New No Alternative Actions and/or Intervals
After accomplishing the revision required by paragraph (i) or
specified in paragraph (j) of this AD, no alternative actions (e.g.,
inspections) and/or intervals may be used unless the actions and/or
intervals are approved as an AMOC in accordance with the procedures
specified in paragraph (l)(1) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (m)(2) of this AD. Information
may be emailed to: [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2015-05-02, are approved
as AMOCs for the corresponding provisions of paragraphs (g) and (h)
of this AD.
(iii) AMOCs approved previously for AD 2015-05-02, which are
included in the FAA AMOC letters specified in paragraphs
(l)(1)(iii)(A) and (l)(1)(iii)(B), are approved as AMOCs for the
corresponding provisions of paragraphs (i) and (j) of this AD.
(A) FAA AMOC letter ANM-116-17-002R1, dated November 14, 2016.
(B) FAA AMOC letter ANM-116-17-323, dated June 12, 2017.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0239, dated December 2,
2016, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2016-6429.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
(n) 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.
(3) The following service information was approved for IBR on
November 28, 2017.
(i) Airbus A318/A319/A320/A321 Airworthiness Limitations Section
(ALS) Part 1--Safe Life--Airworthiness Limitation Items (SL--ALI),
Revision 04, dated June 20, 2016.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitations
Section (ALS) Part 2--Damage Tolerant Airworthiness Limitation Items
(DT--ALI), Revision 05, dated July 8, 2016.
(4) The following service information was approved for IBR on
March 2, 2015 (80 FR 3871, January 26, 2015).
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The
revision level of this document is identified on only the title page
and in the Record of Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. The revision date of this document is not identified on the
title page of this document.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; Internet https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(7) 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 October 11, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-22949 Filed 10-23-17; 8:45 am]
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