Airworthiness Directives; Airbus Airplanes, 69846-69852 [2015-27449]
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69846
Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
and (i) of AD 2013–09–01, Amendment 39–
17442 (78 FR 27001, May 9, 2013), for the
replaced skin panel only.
(r) Exceptions to Service Information
Specifications
(1) Where Boeing Service Bulletin 737–
53A1177, Revision 7, dated June 14, 2013,
specifies a compliance time ‘‘after the
Revision 7 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) Where Boeing Service Bulletin 737–
53A1177, Revision 6, dated May 31, 2001;
and Boeing Service Bulletin 737–53A1177,
Revision 7, dated June 14, 2013; specify to
contact Boeing for certain procedures: Do the
specified actions before further flight using a
method approved in accordance with the
procedures specified in paragraph (t) of this
AD.
(3) Where Boeing Service Bulletin 737–
53A1177, Revision 6, dated May 31, 2001;
and Boeing Service Bulletin 737–53A1177,
Revision 7, dated June 14, 2013; include the
phrase ‘‘or is Boeing or FAA approved,’’ this
AD requires the ‘‘Boeing Approval’’ to be
requested in accordance with the procedures
specified in paragraph (t) of this AD.
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(s) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraphs
(s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of this AD,
which were incorporated by reference in AD
2002–07–08, Amendment 39–12702 (67 FR
17917, April 12, 2002).
(i) Boeing Service Bulletin 737–53A1177,
Revision 4, dated September 2, 1999.
(ii) Boeing Service Bulletin 737–53A1177,
Revision 5, dated February 15, 2001, which
continues to be incorporated by reference in
this AD.
(iii) Boeing Service Bulletin 737–53A1177,
Revision 6, dated May 31, 2001, which
continues to be incorporated by reference in
this AD.
(2) This paragraph provides credit for the
actions required by paragraphs (i) through (o)
of this AD, if those actions were performed
before the effective date of this AD using
Boeing Service Bulletin 737–53A1177,
Revision 6, dated May 31, 2001, which was
incorporated by reference in AD 2002–07–08,
Amendment 39–12702 (67 FR 17917, April
12, 2002) and continues to be incorporated
by reference in this AD.
(t) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (u)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
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(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2002–07–08,
Amendment 39–12702 (67 FR 17917, April
12, 2002), are approved as AMOCs for the
corresponding provisions of this AD.
Issued in Renton, Washington, on October
11, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–26616 Filed 11–10–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2461; Directorate
Identifier 2013–NM–202–AD; Amendment
39–18310; AD 2015–22–05]
RIN 2120–AA64
(u) Related Information
(1) For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5264; fax: 562–627–5210; email:
Jennifer.Tsakoumakis@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (v)(3) and (v)(4) of this AD.
(v) 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) Boeing Service Bulletin 737–53A1177,
Revision 7, dated June 14, 2013.
(ii) Reserved.
(3) The following service information was
approved for IBR on May 17, 2002 (67 FR
17917, April 12, 2002).
(i) Boeing Service Bulletin 737–53A1177,
Revision 5, dated February 15, 2001.
(ii) Boeing Service Bulletin 737–53A1177,
Revision 6, dated May 31, 2001.
(4) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(5) You may view this service information
at 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2009–18–
15, for all Airbus Model A300, A310,
and A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). AD 2009–18–15
required revising the Airworthiness
Limitations section (ALS) of the
Instructions for Continued
Airworthiness (ICA) to require
additional life limits and/or
replacements for certain main landing
gear and nose landing gear components.
This new AD requires revising the
maintenance or inspection program to
incorporate new maintenance
requirements and airworthiness
limitations. This AD was prompted by
a determination that existing
maintenance requirements and
airworthiness limitations are inadequate
to ensure the structural integrity of the
airplane. We are issuing this AD to
prevent failure of certain system
components, which could result in
reduced structural integrity of the
airplane.
DATES: This AD becomes effective
December 17, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 17, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of October 27, 2009 (74 FR
48143, September 22, 2009).
ADDRESSES: You may examine the AD
docket on the Internet at https://
SUMMARY:
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Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
www.regulations.gov/#!docketDetail;D=
FAA-2015-2461; or in person at the
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC.
For service information identified in
this AD, contact Airbus SAS,
Airworthiness Office—EAW, 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
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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2461.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
September 22, 2009). AD 2009–18–15
applied to all Airbus Model A300,
A310, and A300 B4–600, B4–600R, and
F4–600R series airplanes; and Model
A300 C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). The NPRM published
in the Federal Register on July 14, 2015
(80 FR 40942).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0248, dated October 14,
2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Model A300,
A310, and A300–600 series airplanes.
The MCAI states:
The airworthiness limitations for Airbus
aeroplanes are currently published in
Airworthiness Limitations Section (ALS)
documents.
The mandatory instructions and
airworthiness limitations applicable to the
Aging Systems Maintenance (ASM) are
specified in Airbus A310 or A300–600 ALS
Part 4 documents, which are approved by the
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European Aviation Safety Agency (EASA).
EASA AD 2007–0092 [https://
ad.easa.europa.eu/blob/easa_ad_2007_
0092.pdf/AD_2007-0092] [which corresponds
to FAA AD 2009–06–06, Amendment 39–
15842 (74 FR 12228, March 24, 2009)] was
issued to require compliance to the
requirements as specified in these
documents.
The revision 02 of Airbus A310 and Airbus
A300–600 ALS Part 4 documents introduces
more restrictive maintenance requirements
and/or airworthiness limitations. Failure to
comply with the instructions of ALS Part 4
could result in an unsafe condition [reduced
structural integrity of the airplane.]
For the reasons described above, this new
[EASA] AD retains the requirements of EASA
AD 2007–0092, which is superseded, and
requires the implementation of the new or
more restrictive maintenance requirements
and/or airworthiness limitations as specified
in Airbus A310 ALS Part 4, Revision 02, or
Airbus A300–600 ALS Part 4, Revision 02, as
applicable to aeroplane type/model.
• For Model A300 B4–600, B4–600R,
and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes): Part 1, ‘‘Safe
Life Airworthiness Limitation Items,’’
Revision 01, dated September 5, 2013,
of the Airbus Model A300–600
Airworthiness Limitations Section.
• For Model A310 series airplanes:
Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ Revision 01, dated
September 5, 2013, of the Airbus Model
A310 Airworthiness Limitations
Section.
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 of
this AD.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/#!document
Detail;D=FAA-2015-2461-0002.
Costs of Compliance
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (80
FR 40942, July 14, 2015) or on the
determination of the cost to the public.
Conclusion
We reviewed the available data 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 NPRM (80 FR
40942, July 14, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 40942,
July 14, 2015).
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. ‘‘Sub-part 1–2: Life
Limits’’ and ‘‘Sub-part 1–3:
Demonstrated fatigue lives’’ of Part 1,
‘‘Safe Life Airworthiness Limitation
Items,’’ in each of these documents
describe procedures for revising the
maintenance or inspection program to
incorporate new maintenance
requirements and airworthiness
limitations.
• For Model A300 series airplanes:
Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ Revision 01, dated
September 5, 2013, of the Airbus Model
A300 Airworthiness Limitations
Section.
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We estimate that this AD affects 177
airplanes of U.S. registry.
The retained ALS revision required by
AD 2009–18–15, Amendment 39–16011
(74 FR 48143, September 22, 2009),
takes about 1 work-hour per product, at
an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the actions that were
required by AD 2009–18–15 is $85 per
product.
We also estimate that it takes about 1
work-hour per product to comply with
the new ALS revision 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
$15,045, or $85 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
(a) Effective Date
This AD becomes effective December 17,
2015.
(b) Affected ADs
(1) This AD replaces AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
September 22, 2009).
(2) Accomplishing certain requirements of
paragraph (g) of this AD satisfies the
requirements of paragraph A. of AD 84–02–
04, Amendment 39–4795 (49 FR 2746,
January 23, 1984).
(c) Applicability
This AD applies to Airbus Model A300 B2–
1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
and B4–203 airplanes; Model A300 B4–601,
B4–603, B4–620, and B4–622 airplanes;
Model A300 B4–605R and B4–622R
airplanes; Model A300 F4–605R and F4–
622R, and A300 C4–605R Variant F
airplanes; and Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes;
certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America 32, Landing Gear.
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docket
Detail;D=FAA-2015-2461; or in person
at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section.
(e) Reason
This AD was prompted by a determination
that existing maintenance requirements and
airworthiness limitations are inadequate to
ensure the structural integrity of the airplane.
We are issuing this AD to prevent failure of
certain system components, which could
result in reduced structural integrity of the
airplane.
List of Subjects in 14 CFR Part 39
(g) Retained Revision of Airworthiness
Limitation Section (ALS)
This paragraph restates the requirements of
paragraph (h) of AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
September 22, 2009). For Model A300, A310,
and A300–600 series airplanes: Within 3
months after October 27, 2009 (the effective
date of AD 2009–18–15), revise the ALS of
the instructions for continued airworthiness
(ICA) to incorporate the applicable document
listed in paragraph (g)(1), (g)(2), or (g)(3) of
this AD. Accomplishing the actions specified
in the applicable document satisfies the
requirements of paragraph A. of AD 84–02–
04, Amendment 39–4795 (49 FR 2746,
January 23, 1984).
(1) For Model A300 series airplanes:
Incorporate the applicable document listed in
paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Section 05–10–00, Revision 28, dated
February 27, 1998, of Chapter 05, ‘‘Service
Life Limits and Maintenance Checks,’’ of the
Airbus A300 Aircraft Maintenance Manual,
except that the parts listed in table 1 to
paragraph (g) of this AD are subject to the life
limits defined in the document listed in
paragraph (g)(1)(ii) of this AD.
(ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated Fatigue Lives’’ of Part
1, ‘‘Safe Life Airworthiness Limitation
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive AD
2009–18–15, Amendment 39–16011 (74
FR 48143, September 22, 2009), and
adding the following new AD:
■
2015–22–05 Airbus: Amendment 39–18310.
Docket No. FAA–2015–2461; Directorate
Identifier 2013–NM–202–AD.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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Items,’’ dated September 6, 2007, of the
Airbus A300 ALS.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—PARTS SUBJECT TO THE LIFE
LIMITS SPECIFIED IN THE DOCUMENT
IDENTIFIED IN PARAGRAPH (g)(1)(ii)
OF THIS AD
Part No.
(P/N)
Part name
P/N C61643–2, P/N
C61643–4, P/N
C61643–5.
P/N A32210001205xx
Main landing gear
(MLG) shock absorber end fitting.
Nose landing gear
(NLG) pintle pin.
NLG shock absorber
bottom.
Cross beam (Pratt &
Whitney forward
engine mount).
P/N C62037–1 ..........
P/N 196–0328–501 ...
(2) For Model A310 series airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A310 ALS.
(3) For Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model A300
C4–605R Variant F airplanes (collectively
called Model A300–600 series airplanes):
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A300–600 ALS.
(h) Retained Initial Compliance Times and
Repetitive Inspections
This paragraph restates the requirements of
paragraph (i) of AD 2009–18–15, Amendment
39–16011 (74 FR 48143, September 22, 2009).
Do the replacement at the applicable time
specified in paragraph (h)(1) or (h)(2) of this
AD, except as provided by paragraph (i) of
this AD. The replacement must be done
thereafter within the interval specified in the
applicable document identified in paragraph
(g)(1), (g)(2), or (g)(3) of this AD.
(1) For any life limitation/task that has
been complied with before October 27, 2009
(the effective date of AD 2009–18–15,
Amendment 39–16011), in accordance with
the applicable document listed in paragraph
(g)(1), (g)(2), or (g)(3) of this AD, or in
accordance with paragraph (g) of AD 2009–
18–15, use the last accomplishment of each
limitation/task as a starting point for
accomplishing each corresponding
limitation/task required by this AD.
(2) For any life limitation/task that has not
been complied with before October 27, 2009
(the effective date of AD 2009–18–15,
Amendment 39–16011), in accordance with
the applicable document listed in paragraphs
(g)(1), (g)(2), and (g)(3) of this AD, or in
accordance with paragraph (g) of AD 2009–
18–15, the initial compliance time starts from
the date of initial entry into service as
defined in the applicable document.
(i) Retained Special Compliance Times
This paragraph restates the requirements of
paragraph (j) of AD 2009–18–15, Amendment
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39–16011 (74 FR 48143, September 22, 2009).
For any airplane on which the history of
accumulated landings is partial or unknown,
or where the history of application details
(airplane type, model, weight variant, etc.) is
partial or unknown: Parts listed in figure 1
to paragraph (i) of this AD must be replaced
at the associated compliance time. The
replacement must be done thereafter at the
interval specified in the applicable
document(s) specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD.
Note 1 to paragraph (i) of this AD: Airbus
Service Information Letter 32–118, Revision
02, dated October 24, 2007, provides
operators with guidance on the means to
assign a conservative calculated life to parts
whose history of accumulated landings is
partial or unknown; and to select the
limitations applicable to parts whose history
of application details (aircraft type, aircraft
model, weight variant, etc.) is partial or
unknown.
FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES
Aircraft type applicability
A300
Designation
A310
A300–600
Start date
Compliance time
(whichever occurs first
after the ‘‘start date’’)
P/N
X
X
X
Calendar
time
Landings
MAIN LANDING GEAR
Aft pintle pin .................
Half ball housing (Fwd
pintle bearing).
Ball (Fwd pintle pin) .....
Pin (Multiple link/Frame
50).
Pin (Drop link/Frame
50).
A32140032200xx
A32140056200xx
A32140056202xx
A32140057200xx
A32140057202xx
A32140062000xx
A32140063000xx
A32140036200xx
A32140036202xx
A32140036204xx
A32140036206xx
A32140042200xx
A32140042202xx
A32140068002xx
A32140068004xx
A32140069002xx
A32140069004xx
A32140012202xx
A32140043202xx
A53833451200xx
A53833451206xx
A53834451200xx
A53834451202xx
A53811122200xx
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December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
December 13,
April 25, 2007
April 25, 2007
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
..............
..............
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
18,000
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
December 13,
December 13,
December 13,
December 13,
April 25, 2007
December 13,
April 25, 2007
December 13,
April 25, 2007
December 13,
April 25, 2007
December 13,
December 13,
December 13,
December 13,
December 13,
April 25, 2007
April 25, 2007
2007 .....
2007 .....
2007 .....
2007 .....
..............
2007 .....
..............
2007 .....
..............
2007 .....
..............
2007 .....
2007 .....
2007 .....
2007 .....
2007 .....
..............
..............
N/A
N/A
N/A
N/A
N/A
N/A
N/A
N/A
N/A
13,500
13,500
13,500
13,500
13,500
13,500
13,500
13,500
18,000
30 months.
30 months.
30 months.
30 months.
30 months.
30 months.
30 months.
30 months.
30 months.
9 years.
9 years.
9 years.
9 years.
9 years.
9 years.
9 years.
9 years.
9 years.
December 13,
December 13,
December 13,
December 13,
April 25, 2007
2007 .....
2007 .....
2007 .....
2007 .....
..............
N/A
N/A
N/A
N/A
N/A
MLG Barrel Assembly
Upper torque link pin
nut.
Torque link medium pin
nut.
Attaching fitting pin .......
mstockstill on DSK4VPTVN1PROD with RULES
Pin (Connecting rod/
Upper rod).
00–200–402 .................
SL40089 ......................
SL40089P ....................
SL40123 ......................
SL40123P ....................
00–200–358 .................
SL40114P ....................
SL40132 ......................
SL40132P ....................
C62311–1 ....................
C62311–20 ..................
C65815 ........................
C65815–1 ....................
C65815–20 ..................
C66472 ........................
C66472–1 ....................
C66472–20 ..................
D52751 ........................
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
..................
..................
..................
..................
..................
X
..................
X
..................
..................
..................
..................
..................
..................
..................
..................
..................
..................
X
..................
..................
..................
..................
X
..................
..................
..................
X
..................
X
..................
..................
..................
..................
..................
X
..................
MLG Shock Absorber Assembly
Lower torque link pin
nut.
VerDate Sep<11>2014
00–200–402 .................
SL40089 ......................
SL40089P ....................
SL40123 ......................
SL40123P ....................
17:30 Nov 10, 2015
Jkt 238001
PO 00000
X
X
X
X
X
Frm 00013
..................
..................
..................
..................
X
Fmt 4700
..................
..................
..................
..................
X
Sfmt 4700
E:\FR\FM\12NOR1.SGM
12NOR1
30
30
30
30
30
months.
months.
months.
months.
months.
69850
Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued
Aircraft type applicability
A300
Designation
A310
A300–600
Start date
Compliance time
(whichever occurs first
after the ‘‘start date’’)
P/N
Calendar
time
X
X
SL40054 ......................
X
..................
..................
December 13, 2007 .....
at next removal/
installation.1 2
SL40054P ....................
X
..................
X
April 25, 2007 ..............
at next removal/
installation.1 2
SL40413P ....................
Bogie beam pivot pin
nut.
X
Landings
..................
X
..................
April 25, 2007 ..............
at next removal/
installation.1 2
MLG Lock Link Assembly
Lock link medium pin ...
C61485–1 ....................
C61485–20 ..................
X
X
..................
..................
..................
X
December 13, 2007 .....
April 25, 2007 ..............
N/A
N/A
30 months.
30 months.
April 25, 2007 ..............
13,500
9 years.
April 25, 2007
April 25, 2007
December 13,
April 25, 2007
..............
..............
2007 .....
..............
13,500
13,500
13,200
13,500
9
9
9
9
years.
years.
years.
years.
December 13,
December 13,
April 25, 2007
April 25, 2007
December 13,
December 13,
April 25, 2007
April 25, 2007
April 25, 2007
December 13,
December 13,
April 25, 2007
2007 .....
2007 .....
..............
..............
2007 .....
2007 .....
..............
..............
..............
2007 .....
2007 .....
..............
13,200
13,200
13,500
13,500
13,200
13,200
13,500
13,500
13,500
13,200
13,200
13,500
9
9
9
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
NOSE LANDING GEAR
Pintle pin .......................
A32210079200xx .........
X
X
X
NLG Telescopic Strut Assembly
Nut (Cylinder/Locking
cylinder).
Locking sleeve ..............
C61375 ........................
D55955 ........................
C61389 ........................
C61389–1 ....................
X
X
X
X
X
X
X
X
..................
X
..................
X
NLG Barrel Assembly
Pin (Clevis/Telescopic
strut).
End fitting pin ...............
mstockstill on DSK4VPTVN1PROD with RULES
End fitting .....................
Rack .............................
Torque link pin (Upper
& Lower).
VerDate Sep<11>2014
D68062 ........................
X
X
X
December 13, 2007 .....
at next removal/
installation.2
X
X
X
December 13, 2007 .....
at next removal/
installation.2
AN6–17 ........................
X
X
X
December 13, 2007 .....
at next removal/
installation.2
X
X
X
December 13, 2007 .....
at next removal/
installation.2
X
X
X
December 13, 2007 .....
at next removal/
installation.2
NAS1306–22D .............
End fitting pin nut .........
..................
..................
X
X
..................
..................
X
X
X
..................
..................
X
D68063 ........................
Upper pin (Link/Barrel)
..................
..................
X
X
..................
..................
X
X
X
..................
..................
X
D61183 ........................
Link (Clevis/Barrel) .......
X
X
X
X
X
X
X
X
X
X
X
X
MS17825–6 .................
Lower pin (Link/Clevis)
C62231–1 ....................
C62231–2 ....................
C62231–20 ..................
D56530 ........................
C62268–1 ....................
C62268–2 ....................
C62268–20 ..................
C62230–1 ....................
D56526 ........................
C62267–1 ....................
C62267–2 ....................
C62267–20 ..................
X
X
X
December 13, 2007 .....
at next removal/
installation.2
C62032 ........................
C62032–1 ....................
C61453 ........................
C61453–1 ....................
C61453–20 ..................
C61453–40 ..................
C61453–41 ..................
C62223–1 ....................
C62223–20 ..................
X
X
X
X
X
X
X
X
X
X
X
..................
X
X
X
X
..................
X
X
X
..................
X
X
X
X
..................
X
April 25, 2007
April 25, 2007
December 13,
April 25, 2007
April 25, 2007
April 25, 2007
April 25, 2007
December 13,
April 25, 2007
13,500
13,500
13,200
13,500
13,500
13,500
13,500
13,200
13,500
17:30 Nov 10, 2015
Jkt 238001
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
E:\FR\FM\12NOR1.SGM
..............
..............
2007 .....
..............
..............
..............
..............
2007 .....
..............
12NOR1
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
69851
Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued
Aircraft type applicability
A300
Designation
A310
A300–600
Start date
Compliance time
(whichever occurs first
after the ‘‘start date’’)
P/N
X
Torque link medium pin
nut.
X
X
SL40110P ....................
X
X
Calendar
time
Landings
X
April 25, 2007 ..............
N/A
30 months.
4,000
24 months.
NLG Shock Absorber Assembly
Wheel axle nut .............
C62879 ........................
X
X
X
April 25, 2007 ..............
Upper cam dowel .........
C62270 ........................
X
X
X
December 13, 2007 .....
at next removal/
installation.
Upper cam ....................
Lower cam ....................
Restrictor ......................
C62034–1 ....................
C62035 ........................
C62036 ........................
C62036–1 ....................
C62036–2 ....................
C67863 ........................
C67863–1 ....................
C67863–2 ....................
C67863–3 ....................
C67863–4 ....................
X
X
X
X
X
X
X
X
X
X
X
X
..................
..................
..................
..................
X
X
..................
X
X
X
..................
..................
..................
..................
X
X
..................
X
April 25, 2007
April 25, 2007
December 13,
December 13,
December 13,
December 13,
April 25, 2007
April 25, 2007
December 13,
April 25, 2007
13,500
13,500
13,200
13,200
13,200
13,200
13,500
13,500
13,500
13,500
Lower cam dowel .........
C62866 ........................
X
X
X
December 13, 2007 .....
at next removal/
installation.2
Nut (S/A/Barrel) ............
C64040 ........................
X
..................
..................
December 13, 2007 .....
at next removal/
installation.1 2
C64040–1 ....................
X
X
X
December 13, 2007 .....
at next removal/
installation.1 2
..............
..............
2007 .....
2007 .....
2007 .....
2007 .....
..............
..............
2007 .....
..............
9
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
1 When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time
in service during the period between the removal and reinstallation.
2 If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after
October 27, 2009 (the effective date of AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009)).
mstockstill on DSK4VPTVN1PROD with RULES
(j) New Requirements of This AD:
Maintenance Program Revision
Items,’’ dated Revision 01, September 5,
2013, of the Airbus A310 ALS.
Within 3 months after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, to
incorporate the applicable limitation,
replacement, or inspection specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as
applicable. Doing any task required by this
paragraph terminates the corresponding task
required by paragraph (g), (h), and (i) of this
AD.
(1) For Model A300 series airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ Revision 01, dated September 5,
2013, of the Airbus A300 ALS.
(2) For Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model A300
C4 605R Variant F airplanes (collectively
called Model A300–600 series airplanes):
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ Revision 01, dated September 5,
2013, of the Airbus A300–600 ALS.
(3) For Model A310 series airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
(k) New Limitation: No Alternative Actions
or Intervals
After accomplishment of the revision
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (l) of this AD.
VerDate Sep<11>2014
17:30 Nov 10, 2015
Jkt 238001
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: 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 Branch, ANM–
116, Transport Airplane Directorate, 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 2013–0248, dated
October 14, 2013, 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–2015–2461–0002.
E:\FR\FM\12NOR1.SGM
12NOR1
69852
Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (n)(5) and (n)(6) of this AD.
(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 27, 2015.
(i) ALS Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ Revision 01, dated
September 5, 2013, of the Airbus Model A300
Airworthiness Limitations Section.
(ii) ALS Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ Revision 01, dated
September 5, 2013, of the Airbus Model
A300–600 Airworthiness Limitations
Section.
(iii) ALS Part 1, ‘‘Safe Life Airworthiness
Limitation Items,’’ Revision 01, dated
September 5, 2013, of the Airbus Model A310
Airworthiness Limitations Section.
(4) The following service information was
approved for IBR on October 27, 2009 (74 FR
48143, September 22, 2009).
(i) Section 05–10–00 of Chapter 05,
‘‘Service Life Limits and Maintenance
Checks,’’ of the Airbus A300 Aircraft
Maintenance Manual (AMM), Revision 28,
dated February 27, 1998.
(A) The AMM title page; the Record of
Revisions, Effective Pages, and Table of
Content pages; and Section 05–10–00; for
Chapter 05 of Airbus A300 AMM are all
dated February 27, 1998.
(B) The revision level of Chapter 05 of the
Airbus A300 AMM is indicated only in the
Record of Revisions section of Chapter 05.
(C) The List of Effective Pages (LOEP) for
Chapter 05 of the Airbus A300 AMM
contains the discrepancies identified in
paragraphs (n)(4)(i)(C)(1) through
(n)(4)(i)(C)(4) of this AD.
(1) The Transmittal Letter page, page 4 of
the LOEP and Table of Contents sections,
page 2 of Subsection 05–00–01, Subsection
05–10–00, and page 1 of Subsection 05–11–
11, are not listed in the LOEP for Chapter 05
of the Airbus A300 AMM.
(2) The LOEP for Chapter 05 of the Airbus
A300 AMM does not specify a date for the
Record of Revisions page.
(3) The LOEP for Chapter 05 of the Airbus
A300 AMM identifies three pages for
Subsection 05–11–00, Configuration 5;
however, only one page exists.
(4) The LOEP for Chapter 05 of the Airbus
A300 AMM identifies three pages for
Subsection 05–11–00, Configuration 9;
however, those pages do not exist.
(ii) Airbus A300 Airworthiness Limitations
Section, ALS Part 1, ‘‘Safe Life Airworthiness
Limitations Items’’ dated September 6, 2007.
(iii) Airbus A300–600 Airworthiness
Limitations Section, ALS Part 1, ‘‘Safe Life
Airworthiness Limitations Items’’ dated
December 21, 2006.
(iv) Airbus A310 Airworthiness
Limitations Section, ALS Part 1, ‘‘Safe Life
VerDate Sep<11>2014
17:30 Nov 10, 2015
Jkt 238001
Airworthiness Limitation Items’’ dated
December 21, 2006.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 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.
(6) 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.
(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
21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–27449 Filed 11–10–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
15 CFR Part 744
[Docket No. 150911846–5846–01]
RIN 0694–AG74
Addition of Certain Persons and
Modification of Certain Entries to the
Entity List; and Removal of Certain
Persons From the Entity List
Bureau of Industry and
Security, Commerce.
ACTION: Final rule.
AGENCY:
This rule amends the Export
Administration Regulations (EAR) by
adding seven persons under ten entries
to the Entity List. The seven persons
who are added to the Entity List have
been determined by the U.S.
Government to be acting contrary to the
national security or foreign policy
interests of the United States. These
persons will be listed on the Entity List
under the destinations of China and
Hong Kong.
This final rule also removes two
persons from the Entity List. One entity
requested removal from the Entity List
in accordance with the procedure for
requesting removal or modification of
an Entity List entity. The End-User
Review Committee (ERC) decided to
remove this entity following a review of
information provided in the removal
request. The ERC decided to remove a
SUMMARY:
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
second person from the Entity List
following a proposal submitted by an
ERC member agency, in accordance
with the procedure for requesting
removal or modification of an Entity
List entity.
Finally, this final rule modifies ten
existing entries on the Entity List
consisting of one entry under China and
nine entries under Hong Kong to
provide additional or modified
addresses and/or aliases for these
persons.
DATES: This rule is effective on
November 12, 2015.
FOR FURTHER INFORMATION CONTACT:
Chair, End-User Review Committee,
Office of the Assistant Secretary, Export
Administration, Bureau of Industry and
Security, Department of Commerce,
Phone: (202) 482–5991, Fax: (202) 482–
3911, Email: ERC@bis.doc.gov.
SUPPLEMENTARY INFORMATION:
Background
The Entity List (Supplement No. 4 to
Part 744) identifies entities and other
persons reasonably believed to be
involved, or to pose a significant risk of
being or becoming involved, in
activities contrary to the national
security or foreign policy interests of the
United States. The EAR imposes
additional license requirements on, and
limits the availability of most license
exceptions for, exports, reexports, and
transfers (in-country) to those listed.
The ‘‘license review policy’’ for each
listed entity or other person is identified
in the License Review Policy column on
the Entity List and the impact on the
availability of license exceptions is
described in the Federal Register notice
adding entities or other persons to the
Entity List. BIS places entities and other
persons on the Entity List pursuant to
sections of part 744 (Control Policy:
End-User and End-Use Based) and part
746 (Embargoes and Other Special
Controls) of the EAR.
The ERC, composed of representatives
of the Departments of Commerce
(Chair), State, Defense, Energy and,
where appropriate, the Treasury, makes
all decisions regarding additions to,
removals from, or other modifications to
the Entity List. The ERC makes all
decisions to add an entry to the Entity
List by majority vote and all decisions
to remove or modify an entry by
unanimous vote.
ERC Entity List Decisions
Additions to the Entity List
This rule implements the decision of
the ERC to add seven persons under ten
entries to the Entity List. These seven
persons are being added on the basis of
E:\FR\FM\12NOR1.SGM
12NOR1
]]>Agencies
[Federal Register Volume 80, Number 218 (Thursday, November 12, 2015)]
[Rules and Regulations]
[Pages 69846-69852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27449]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD;
Amendment 39-18310; AD 2015-22-05]
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) 2009-18-15,
for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes). AD 2009-18-15
required revising the Airworthiness Limitations section (ALS) of the
Instructions for Continued Airworthiness (ICA) to require additional
life limits and/or replacements for certain main landing gear and nose
landing gear components. This new AD requires revising the maintenance
or inspection program to incorporate new maintenance requirements and
airworthiness limitations. This AD was prompted by a determination that
existing maintenance requirements and airworthiness limitations are
inadequate to ensure the structural integrity of the airplane. We are
issuing this AD to prevent failure of certain system components, which
could result in reduced structural integrity of the airplane.
DATES: This AD becomes effective December 17, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 17,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of October
27, 2009 (74 FR 48143, September 22, 2009).
ADDRESSES: You may examine the AD docket on the Internet at https://
[[Page 69847]]
www.regulations.gov/#!docketDetail;D= FAA-2015-2461; or in person at
the Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Airbus SAS,
Airworthiness Office--EAW, 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
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 https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-2461.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-18-15, Amendment 39-16011 (74 FR 48143,
September 22, 2009). AD 2009-18-15 applied to all Airbus Model A300,
A310, and A300 B4-600, B4-600R, and F4-600R series airplanes; and Model
A300 C4-605R Variant F airplanes (collectively called Model A300-600
series airplanes). The NPRM published in the Federal Register on July
14, 2015 (80 FR 40942).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0248, dated October 14, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Model A300, A310,
and A300-600 series airplanes. The MCAI states:
The airworthiness limitations for Airbus aeroplanes are currently
published in Airworthiness Limitations Section (ALS) documents.
The mandatory instructions and airworthiness limitations
applicable to the Aging Systems Maintenance (ASM) are specified in
Airbus A310 or A300-600 ALS Part 4 documents, which are approved by
the European Aviation Safety Agency (EASA). EASA AD 2007-0092
[https://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092]
[which corresponds to FAA AD 2009-06-06, Amendment 39-15842 (74 FR
12228, March 24, 2009)] was issued to require compliance to the
requirements as specified in these documents.
The revision 02 of Airbus A310 and Airbus A300-600 ALS Part 4
documents introduces more restrictive maintenance requirements and/
or airworthiness limitations. Failure to comply with the
instructions of ALS Part 4 could result in an unsafe condition
[reduced structural integrity of the airplane.]
For the reasons described above, this new [EASA] AD retains the
requirements of EASA AD 2007-0092, which is superseded, and requires
the implementation of the new or more restrictive maintenance
requirements and/or airworthiness limitations as specified in Airbus
A310 ALS Part 4, Revision 02, or Airbus A300-600 ALS Part 4,
Revision 02, as applicable to aeroplane type/model.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-2461-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 40942, July 14,
2015) or on the determination of the cost to the public.
Conclusion
We reviewed the available data 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
NPRM (80 FR 40942, July 14, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 40942, July 14, 2015).
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. ``Sub-part 1-
2: Life Limits'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' in each of these
documents describe procedures for revising the maintenance or
inspection program to incorporate new maintenance requirements and
airworthiness limitations.
For Model A300 series airplanes: Part 1, ``Safe Life
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013,
of the Airbus Model A300 Airworthiness Limitations Section.
For Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes): Part 1, ``Safe Life
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013,
of the Airbus Model A300-600 Airworthiness Limitations Section.
For Model A310 series airplanes: Part 1, ``Safe Life
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013,
of the Airbus Model A310 Airworthiness Limitations Section.
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 of this
AD.
Costs of Compliance
We estimate that this AD affects 177 airplanes of U.S. registry.
The retained ALS revision required by AD 2009-18-15, Amendment 39-
16011 (74 FR 48143, September 22, 2009), takes about 1 work-hour per
product, at an average labor rate of $85 per work-hour. Based on these
figures, the estimated cost of the actions that were required by AD
2009-18-15 is $85 per product.
We also estimate that it takes about 1 work-hour per product to
comply with the new ALS revision 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 $15,045, or $85 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
[[Page 69848]]
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-2461; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive AD
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), and
adding the following new AD:
2015-22-05 Airbus: Amendment 39-18310. Docket No. FAA-2015-2461;
Directorate Identifier 2013-NM-202-AD.
(a) Effective Date
This AD becomes effective December 17, 2015.
(b) Affected ADs
(1) This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR
48143, September 22, 2009).
(2) Accomplishing certain requirements of paragraph (g) of this
AD satisfies the requirements of paragraph A. of AD 84-02-04,
Amendment 39-4795 (49 FR 2746, January 23, 1984).
(c) Applicability
This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603,
B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R
airplanes; Model A300 F4-605R and F4-622R, and A300 C4-605R Variant
F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America 32, Landing Gear.
(e) Reason
This AD was prompted by a determination that existing
maintenance requirements and airworthiness limitations are
inadequate to ensure the structural integrity of the airplane. We
are issuing this AD to prevent failure of certain system components,
which could result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Revision of Airworthiness Limitation Section (ALS)
This paragraph restates the requirements of paragraph (h) of AD
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009).
For Model A300, A310, and A300-600 series airplanes: Within 3 months
after October 27, 2009 (the effective date of AD 2009-18-15), revise
the ALS of the instructions for continued airworthiness (ICA) to
incorporate the applicable document listed in paragraph (g)(1),
(g)(2), or (g)(3) of this AD. Accomplishing the actions specified in
the applicable document satisfies the requirements of paragraph A.
of AD 84-02-04, Amendment 39-4795 (49 FR 2746, January 23, 1984).
(1) For Model A300 series airplanes: Incorporate the applicable
document listed in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Section 05-10-00, Revision 28, dated February 27, 1998, of
Chapter 05, ``Service Life Limits and Maintenance Checks,'' of the
Airbus A300 Aircraft Maintenance Manual, except that the parts
listed in table 1 to paragraph (g) of this AD are subject to the
life limits defined in the document listed in paragraph (g)(1)(ii)
of this AD.
(ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3:
Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness
Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS.
Table 1 to Paragraph (g) of This AD--Parts Subject to the Life Limits
Specified in the Document Identified in Paragraph (g)(1)(ii) of This AD
------------------------------------------------------------------------
Part No. (P/N) Part name
------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N C61643-5.. Main landing gear (MLG)
shock absorber end fitting.
P/N A32210001205xx........................ Nose landing gear (NLG)
pintle pin.
P/N C62037-1.............................. NLG shock absorber bottom.
P/N 196-0328-501.......................... Cross beam (Pratt & Whitney
forward engine mount).
------------------------------------------------------------------------
(2) For Model A310 series airplanes: Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December
21, 2006, of the Airbus A310 ALS.
(3) For Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December
21, 2006, of the Airbus A300-600 ALS.
(h) Retained Initial Compliance Times and Repetitive Inspections
This paragraph restates the requirements of paragraph (i) of AD
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). Do
the replacement at the applicable time specified in paragraph (h)(1)
or (h)(2) of this AD, except as provided by paragraph (i) of this
AD. The replacement must be done thereafter within the interval
specified in the applicable document identified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD.
(1) For any life limitation/task that has been complied with
before October 27, 2009 (the effective date of AD 2009-18-15,
Amendment 39-16011), in accordance with the applicable document
listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in
accordance with paragraph (g) of AD 2009-18-15, use the last
accomplishment of each limitation/task as a starting point for
accomplishing each corresponding limitation/task required by this
AD.
(2) For any life limitation/task that has not been complied with
before October 27, 2009 (the effective date of AD 2009-18-15,
Amendment 39-16011), in accordance with the applicable document
listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in
accordance with paragraph (g) of AD 2009-18-15, the initial
compliance time starts from the date of initial entry into service
as defined in the applicable document.
(i) Retained Special Compliance Times
This paragraph restates the requirements of paragraph (j) of AD
2009-18-15, Amendment
[[Page 69849]]
39-16011 (74 FR 48143, September 22, 2009). For any airplane on
which the history of accumulated landings is partial or unknown, or
where the history of application details (airplane type, model,
weight variant, etc.) is partial or unknown: Parts listed in figure
1 to paragraph (i) of this AD must be replaced at the associated
compliance time. The replacement must be done thereafter at the
interval specified in the applicable document(s) specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Note 1 to paragraph (i) of this AD: Airbus Service Information
Letter 32-118, Revision 02, dated October 24, 2007, provides
operators with guidance on the means to assign a conservative
calculated life to parts whose history of accumulated landings is
partial or unknown; and to select the limitations applicable to
parts whose history of application details (aircraft type, aircraft
model, weight variant, etc.) is partial or unknown.
Figure 1 to Paragraph (i) of This AD--Special Compliance Times
--------------------------------------------------------------------------------------------------------------------------------------------------------
Aircraft type applicability Compliance time (whichever
-------------------------------------------------------------- occurs first after the ``start
Designation A300 A310 A300-600 Start date date'')
------------------------------------------------- P/N ---------------------------------
X X X Landings Calendar time
--------------------------------------------------------------------------------------------------------------------------------------------------------
MAIN LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Aft pintle pin.................... A32140032200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140056200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140056202xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140057200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140057202xx....... X ........... X December 13, 2007... 13,500 9 years.
A32140062000xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140063000xx....... X ........... X December 13, 2007... 13,500 9 years.
Half ball housing (Fwd pintle A32140036200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
bearing). A32140036202xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140036204xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140036206xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140042200xx....... X ........... X December 13, 2007... 13,500 9 years.
A32140042202xx....... X ........... X December 13, 2007... 13,500 9 years.
A32140068002xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140068004xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140069002xx....... X ........... X December 13, 2007... 13,500 9 years.
A32140069004xx....... X ........... X December 13, 2007... 13,500 9 years.
Ball (Fwd pintle pin)............. A32140012202xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A32140043202xx....... X ........... X December 13, 2007... 13,500 9 years.
Pin (Multiple link/Frame 50)...... A53833451200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A53833451206xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A53834451200xx....... X ........... ........... December 13, 2007... 13,500 9 years.
A53834451202xx....... X ........... X April 25, 2007...... 13,500 9 years.
Pin (Drop link/Frame 50).......... A53811122200xx....... ........... X ........... April 25, 2007...... 18,000 9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
MLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Upper torque link pin nut......... 00-200-402........... X ........... ........... December 13, 2007... N/A 30 months.
SL40089.............. X ........... ........... December 13, 2007... N/A 30 months.
SL40089P............. X ........... ........... December 13, 2007... N/A 30 months.
SL40123.............. X ........... ........... December 13, 2007... N/A 30 months.
SL40123P............. X X X April 25, 2007...... N/A 30 months.
Torque link medium pin nut........ 00-200-358........... X ........... ........... December 13, 2007... N/A 30 months.
SL40114P............. X X ........... April 25, 2007...... N/A 30 months.
SL40132.............. X ........... ........... December 13, 2007... N/A 30 months.
SL40132P............. X ........... X April 25, 2007...... N/A 30 months.
Attaching fitting pin............. C62311-1............. X ........... ........... December 13, 2007... 13,500 9 years.
C62311-20............ X ........... X April 25, 2007...... 13,500 9 years.
Pin (Connecting rod/Upper rod).... C65815............... X ........... ........... December 13, 2007... 13,500 9 years.
C65815-1............. X ........... ........... December 13, 2007... 13,500 9 years.
C65815-20............ X ........... ........... December 13, 2007... 13,500 9 years.
C66472............... X ........... ........... December 13, 2007... 13,500 9 years.
C66472-1............. X ........... ........... December 13, 2007... 13,500 9 years.
C66472-20............ X ........... X April 25, 2007...... 13,500 9 years.
D52751............... ........... X ........... April 25, 2007...... 18,000 9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
MLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lower torque link pin nut......... 00-200-402........... X ........... ........... December 13, 2007... N/A 30 months.
SL40089.............. X ........... ........... December 13, 2007... N/A 30 months.
SL40089P............. X ........... ........... December 13, 2007... N/A 30 months.
SL40123.............. X ........... ........... December 13, 2007... N/A 30 months.
SL40123P............. X X X April 25, 2007...... N/A 30 months.
---------------------------------
[[Page 69850]]
Bogie beam pivot pin nut.......... SL40054.............. X ........... ........... December 13, 2007... at next removal/installation.1 2
---------------------------------
SL40054P............. X ........... X April 25, 2007...... at next removal/installation.1 2
---------------------------------
SL40413P............. ........... X ........... April 25, 2007...... at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
MLG Lock Link Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lock link medium pin.............. C61485-1............. X ........... ........... December 13, 2007... N/A 30 months.
C61485-20............ X ........... X April 25, 2007...... N/A 30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
NOSE LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pintle pin........................ A32210079200xx....... X X X April 25, 2007...... 13,500 9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
NLG Telescopic Strut Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Nut (Cylinder/Locking cylinder)... C61375............... X X ........... April 25, 2007...... 13,500 9 years.
D55955............... X X X April 25, 2007...... 13,500 9 years.
Locking sleeve.................... C61389............... X X ........... December 13, 2007... 13,200 9 years.
C61389-1............. X X X April 25, 2007...... 13,500 9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
NLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pin (Clevis/Telescopic strut)..... C62231-1............. X ........... ........... December 13, 2007... 13,200 9 years.
C62231-2............. X ........... ........... December 13, 2007... 13,200 9 years.
C62231-20............ X X X April 25, 2007...... 13,500 9 years.
D56530............... X X X April 25, 2007...... 13,500 9 years.
Lower pin (Link/Clevis)........... C62268-1............. X ........... ........... December 13, 2007... 13,200 9 years.
C62268-2............. X ........... ........... December 13, 2007... 13,200 9 years.
C62268-20............ X X X April 25, 2007...... 13,500 9 years.
Link (Clevis/Barrel).............. C62230-1............. X X X April 25, 2007...... 13,500 9 years.
D56526............... X X X April 25, 2007...... 13,500 9 years.
Upper pin (Link/Barrel)........... C62267-1............. X ........... ........... December 13, 2007... 13,200 9 years.
C62267-2............. X ........... ........... December 13, 2007... 13,200 9 years.
C62267-20............ X X X April 25, 2007...... 13,500 9 years.
---------------------------------
End fitting pin nut............... D68062............... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
MS17825-6............ X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
End fitting pin................... AN6-17............... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
D61183............... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
D68063............... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
NAS1306-22D.......... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
End fitting....................... C62032............... X X X April 25, 2007...... 13,500 9 years.
C62032-1............. X X X April 25, 2007...... 13,500 9 years.
Rack.............................. C61453............... X ........... ........... December 13, 2007... 13,200 9 years.
C61453-1............. X X X April 25, 2007...... 13,500 9 years.
C61453-20............ X X X April 25, 2007...... 13,500 9 years.
C61453-40............ X X X April 25, 2007...... 13,500 9 years.
C61453-41............ X X X April 25, 2007...... 13,500 9 years.
Torque link pin (Upper & Lower)... C62223-1............. X ........... ........... December 13, 2007... 13,200 9 years.
C62223-20............ X X X April 25, 2007...... 13,500 9 years.
[[Page 69851]]
Torque link medium pin nut........ SL40110P............. X X X April 25, 2007...... N/A 30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
NLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Wheel axle nut.................... C62879............... X X X April 25, 2007...... 4,000 24 months.
---------------------------------
Upper cam dowel................... C62270............... X X X December 13, 2007... at next removal/installation.
---------------------------------
Upper cam......................... C62034-1............. X X X April 25, 2007...... 13,500 9 years.
Lower cam......................... C62035............... X X X April 25, 2007...... 13,500 9 years.
Restrictor........................ C62036............... X ........... ........... December 13, 2007... 13,200 9 years.
C62036-1............. X ........... ........... December 13, 2007... 13,200 9 years.
C62036-2............. X ........... ........... December 13, 2007... 13,200 9 years.
C67863............... X ........... ........... December 13, 2007... 13,200 9 years.
C67863-1............. X X X April 25, 2007...... 13,500 9 years.
C67863-2............. X X X April 25, 2007...... 13,500 9 years.
C67863-3............. X ........... ........... December 13, 2007... 13,500 9 years.
C67863-4............. X X X April 25, 2007...... 13,500 9 years.
---------------------------------
Lower cam dowel................... C62866............... X X X December 13, 2007... at next removal/installation.\2\
---------------------------------
Nut (S/A/Barrel).................. C64040............... X ........... ........... December 13, 2007... at next removal/installation.1 2
---------------------------------
C64040-1............. X X X December 13, 2007... at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required
provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service
during the period between the removal and reinstallation.
\2\ If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after
October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009)).
(j) New Requirements of This AD: Maintenance Program Revision
Within 3 months after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, to incorporate the
applicable limitation, replacement, or inspection specified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing
any task required by this paragraph terminates the corresponding
task required by paragraph (g), (h), and (i) of this AD.
(1) For Model A300 series airplanes: Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01,
dated September 5, 2013, of the Airbus A300 ALS.
(2) For Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4 605R Variant F airplanes (collectively
called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01,
dated September 5, 2013, of the Airbus A300-600 ALS.
(3) For Model A310 series airplanes: Incorporate ``Sub-part 1-2:
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated Revision
01, September 5, 2013, of the Airbus A310 ALS.
(k) New Limitation: No Alternative Actions or Intervals
After accomplishment of the revision required by paragraph (j)
of this AD, no alternative actions (e.g., inspections) or intervals
may be used unless the actions or intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (l) 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 Branch, ANM-116, Transport Airplane Directorate, 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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: 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 Branch, ANM-116, Transport
Airplane Directorate, 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 2013-0248, dated October 14,
2013, 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-2015-2461-0002.
[[Page 69852]]
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (n)(5) and (n)(6) of this AD.
(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 27, 2015.
(i) ALS Part 1, ``Safe Life Airworthiness Limitation Items,''
Revision 01, dated September 5, 2013, of the Airbus Model A300
Airworthiness Limitations Section.
(ii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,''
Revision 01, dated September 5, 2013, of the Airbus Model A300-600
Airworthiness Limitations Section.
(iii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,''
Revision 01, dated September 5, 2013, of the Airbus Model A310
Airworthiness Limitations Section.
(4) The following service information was approved for IBR on
October 27, 2009 (74 FR 48143, September 22, 2009).
(i) Section 05-10-00 of Chapter 05, ``Service Life Limits and
Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual
(AMM), Revision 28, dated February 27, 1998.
(A) The AMM title page; the Record of Revisions, Effective
Pages, and Table of Content pages; and Section 05-10-00; for Chapter
05 of Airbus A300 AMM are all dated February 27, 1998.
(B) The revision level of Chapter 05 of the Airbus A300 AMM is
indicated only in the Record of Revisions section of Chapter 05.
(C) The List of Effective Pages (LOEP) for Chapter 05 of the
Airbus A300 AMM contains the discrepancies identified in paragraphs
(n)(4)(i)(C)(1) through (n)(4)(i)(C)(4) of this AD.
(1) The Transmittal Letter page, page 4 of the LOEP and Table of
Contents sections, page 2 of Subsection 05-00-01, Subsection 05-10-
00, and page 1 of Subsection 05-11-11, are not listed in the LOEP
for Chapter 05 of the Airbus A300 AMM.
(2) The LOEP for Chapter 05 of the Airbus A300 AMM does not
specify a date for the Record of Revisions page.
(3) The LOEP for Chapter 05 of the Airbus A300 AMM identifies
three pages for Subsection 05-11-00, Configuration 5; however, only
one page exists.
(4) The LOEP for Chapter 05 of the Airbus A300 AMM identifies
three pages for Subsection 05-11-00, Configuration 9; however, those
pages do not exist.
(ii) Airbus A300 Airworthiness Limitations Section, ALS Part 1,
``Safe Life Airworthiness Limitations Items'' dated September 6,
2007.
(iii) Airbus A300-600 Airworthiness Limitations Section, ALS
Part 1, ``Safe Life Airworthiness Limitations Items'' dated December
21, 2006.
(iv) Airbus A310 Airworthiness Limitations Section, ALS Part 1,
``Safe Life Airworthiness Limitation Items'' dated December 21,
2006.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 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.
(6) 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.
(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 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-27449 Filed 11-10-15; 8:45 am]
BILLING CODE 4910-13-P
