Airworthiness Directives; Airbus Airplanes, 40942-40947 [2015-17201]
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40942
Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
Issued in Washington, DC, on June 30,
2015.
Kathleen B. Hogan,
Deputy Assistant Secretary for Energy
Efficiency and Renewable Energy.
[FR Doc. 2015–17252 Filed 7–13–15; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2461; Directorate
Identifier 2013–NM–202–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
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
currently requires 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.
Since we issued AD 2009–18–15, we
have determined that existing
maintenance requirements and
airworthiness limitations are inadequate
to ensure the structural integrity of the
airplane. This proposed AD would
require revising the maintenance or
inspection program to incorporate new
maintenance requirements and
airworthiness limitations. We are
proposing this AD to prevent failure of
certain system components, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by August 28, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY:
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• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed 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.
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–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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–2461; Directorate Identifier
2013–NM–202–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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substantive verbal contact we receive
about this proposed AD.
Discussion
On August 24, 2009, we issued AD
2009–18–15, Amendment 39–16011 (74
FR 48143, September 22, 2009). AD
2009–18–15 requires actions intended to
address an unsafe condition 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).
Since we issued AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
September 22, 2009), we have
determined that more restrictive
maintenance requirements and
airworthiness limitations are necessary.
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 by searching for
and locating Docket No. FAA–2015–
2461.
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Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information, which describes
procedures for revising the maintenance
or inspection program to incorporate
new maintenance requirements and
airworthiness limitations.
• For Model A300 series airplanes:
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of
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): ‘‘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 Model A300–600
Airworthiness Limitations Section.
• For Model A310 series airplanes:
‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of
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 NPRM.
FAA’s Determination and Requirements
of This Proposed AD
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 177 airplanes of U.S. registry.
The 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
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estimated cost of the actions that were
required by AD 2009–18–15 is $85 per
product.
We also estimate that it would take
about 1 work-hour per product to
comply with the new ALS revision of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $15,045, or $85 per product.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
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.
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40943
§ 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:
■
Airbus: Docket No. FAA–2015–2461;
Directorate Identifier 2013–NM–202–AD.
(a) Comments Due Date
We must receive comments by August 28,
2015.
(b) Affected ADs
This AD replaces AD 2009–18–15,
Amendment 39–16011 (74 FR 48143,
September 22, 2009).
(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
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Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
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.
(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
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
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, with or without using
the information in Airbus Service
Information Letter 32–118, Revision 02,
dated October 24, 2007: 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
Designation
A300
A310
X
X
A300–
600
Compliance time
(whichever occurs first after the ‘‘start
date’’)
Start date
P/N
Landings
X
Calendar time
MAIN LANDING GEAR
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Aft pintle pin .............
Half ball housing
(Fwd pintle bearing).
Ball (Fwd pintle pin)
VerDate Sep<11>2014
A32140032200xx
A32140056200xx
A32140056202xx
A32140057200xx
A32140057202xx
A32140062000xx
A32140063000xx
A32140036200xx
A32140036202xx
A32140036204xx
A32140036206xx
A32140042200xx
X
X
X
X
X
X
X
X
X
X
X
X
A32140042202xx
A32140068002xx
A32140068004xx
A32140069002xx
A32140069004xx
A32140012202xx
A32140043202xx
X
X
X
X
X
X
X
19:37 Jul 13, 2015
Jkt 235001
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Frm 00007
X
X
X
X
X
X
X
Fmt 4702
December
December
December
December
December
December
December
December
December
December
December
December
13,
13,
13,
13,
13,
13,
13,
13,
13,
13,
13,
13,
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
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
9
9
9
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
December
December
December
December
December
December
December
13,
13,
13,
13,
13,
13,
13,
2007
2007
2007
2007
2007
2007
2007
13,500
13,500
13,500
13,500
13,500
13,500
13,500
.....................
.....................
.....................
.....................
.....................
.....................
.....................
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
Sfmt 4702
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14JYP1
40945
Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued
Aircraft type applicability
Designation
A300
A310
X
Pin (Multiple link/
Frame 50).
Pin (Drop link/Frame
50).
X
A300–
600
Compliance time
(whichever occurs first after the ‘‘start
date’’)
Start date
P/N
Landings
X
Calendar time
A53833451200xx
X
December 13, 2007
13,500 .....................
9 years..
A53833451206xx
A53834451200xx
A53834451202xx
A53811122200xx
X
X
X
December 13,
December 13,
April 25, 2007
April 25, 2007
13,500
13,500
13,500
18,000
9
9
9
9
X
X
2007
2007
........
........
.....................
.....................
.....................
.....................
years.
years.
years.
years.
MLG Barrel Assembly
Upper torque link pin
nut.
00–200–402
30 months.
X
X
X
X
X
December 13,
December 13,
December 13,
April 25, 2007
December 13,
2007
2007
2007
........
2007
N/A
N/A
N/A
N/A
N/A
30
30
30
30
30
X
X
X
X
X
X
April 25, 2007
December 13,
April 25, 2007
December 13,
April 25, 2007
December 13,
........
2007
........
2007
........
2007
N/A ..........................
N/A ..........................
N/A ..........................
13,500 .....................
13,500 .....................
13,500 .....................
30 months.
30 months.
30 months.
9 years.
9 years.
9 years.
C65815–1
C65815–20
C66472
C66472–1
C66472–20
D52751
Pin (Connecting rod/
Upper rod).
N/A ..........................
SL40114P
SL40132
SL40132P
C62311–1
C62311–20
C65815
Attaching fitting pin ...
December 13, 2007
SL40089
SL40089P
SL40123
SL40123P
00–200–358
Torque link medium
pin nut.
X
X
X
X
X
X
December 13,
December 13,
December 13,
December 13,
April 25, 2007
April 25, 2007
2007
2007
2007
2007
........
........
13,500
13,500
13,500
13,500
13,500
18,000
9
9
9
9
9
9
X
X
X
X
X
X
X
..........................
..........................
..........................
..........................
..........................
.....................
.....................
.....................
.....................
.....................
.....................
months.
months.
months.
months.
months.
years.
years.
years.
years.
years.
years.
MLG Shock Absorber Assembly
Lower torque link pin
nut.
00–200–402
December 13, 2007
N/A ..........................
30 months.
SL40089
SL40089P
SL40123
SL40123P
X
X
X
X
December 13,
December 13,
December 13,
April 25, 2007
N/A
N/A
N/A
N/A
30
30
30
30
SL40054
X
SL40054P
SL40413P
Bogie beam pivot pin
nut.
X
X
X
X
2007
2007
2007
........
..........................
..........................
..........................
..........................
months.
months.
months.
months.
December 13, 2007
X
X
at next removal/installation.1 2
April 25, 2007 ........
April 25, 2007 ........
at next removal/installation.1 2
at next removal/installation.1 2
MLG Lock Link Assembly
Lock link medium pin
C61485–1
C61485–20
X
X
N/A ..........................
N/A ..........................
30 months.
30 months.
13,500 .....................
9 years.
April 25, 2007 ........
X
December 13, 2007
April 25, 2007 ........
13,500 .....................
9 years.
April 25, 2007 ........
December 13, 2007
April 25, 2007 ........
13,500 .....................
13,200 .....................
13,500 .....................
9 years.
9 years.
9 years.
NOSE LANDING GEAR
Pintle pin ..................
A32210079200xx
X
X
X
April 25, 2007 ........
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
NLG Telescopic Strut Assembly
Nut (Cylinder/Locking
cylinder).
C61375
X
X
Locking sleeve .........
D55955
C61389
C61389–1
X
X
X
X
X
X
X
X
NLG Barrel Assembly
Pin (Clevis/Telescopic strut).
18:44 Jul 13, 2015
X
December 13, 2007
13,200 .....................
9 years.
C62231–2
VerDate Sep<11>2014
C62231–1
X
December 13, 2007
13,200 .....................
9 years.
Jkt 235001
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
E:\FR\FM\14JYP1.SGM
14JYP1
40946
Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued
Aircraft type applicability
Designation
A300
A310
A300–
600
Compliance time
(whichever occurs first after the ‘‘start
date’’)
Start date
P/N
Landings
Calendar time
X
X
X
C62231–20
D56530
C62268–1
X
X
X
X
X
X
X
April 25, 2007 ........
April 25, 2007 ........
December 13, 2007
13,500 .....................
13,500 .....................
13,200 .....................
9 years.
9 years.
9 years.
C62268–2
C62268–20
C62230–1
D56526
C62267–1
X
X
X
X
X
X
X
X
X
X
X
December 13,
April 25, 2007
April 25, 2007
April 25, 2007
December 13,
13,200
13,500
13,500
13,500
13,200
9
9
9
9
9
C62267–2
C62267–20
X
X
X
X
December 13, 2007
April 25, 2007 ........
D68062
MS17825–6
AN6–17
D61183
D68063
NAS1306–22D
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
December
December
December
December
December
December
13,
13,
13,
13,
13,
13,
2007
2007
2007
2007
2007
2007
C62032
C62032–1
C61453
C61453–1
C61453–20
C61453–40
C61453–41
C62223–1
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,
........
........
2007
........
........
........
........
2007
C62223–20
SL40110P
X
X
X
X
X
X
Lower pin (Link/Clevis).
Link (Clevis/Barrel) ...
Upper pin (Link/Barrel).
End fitting pin nut .....
End fitting pin ...........
End fitting .................
Rack .........................
Torque link pin
(Upper & Lower).
Torque link medium
pin nut.
2007
........
........
........
2007
.....................
.....................
.....................
.....................
.....................
13,200 .....................
13,500 .....................
at
at
at
at
at
at
April 25, 2007 ........
April 25, 2007 ........
13,500
13,500
13,200
13,500
13,500
13,500
13,500
13,200
next
next
next
next
next
next
years.
years.
years.
years.
years.
9 years.
9 years.
removal/installation.2
removal/installation.2
removal/installation.2
removal/installation.2
removal/installation.2
removal/installation.2
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
13,500 .....................
N/A ..........................
9 years.
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
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
C62866
C64040
C64040–1
X
X
X
X
X
X
X
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Lower cam dowel .....
Nut (S/A/Barrel) ........
at next removal/installation.
........
........
2007
2007
2007
2007
........
........
2007
........
13,500
13,500
13,200
13,200
13,200
13,200
13,500
13,500
13,500
13,500
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
.....................
9
9
9
9
9
9
9
9
9
9
years.
years.
years.
years.
years.
years.
years.
years.
years.
years.
at next removal/installation.2
at next removal/installation.1 2
at next removal/installation.1 2
December 13, 2007
December 13, 2007
December 13, 2007
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
VerDate Sep<11>2014
19:37 Jul 13, 2015
Jkt 235001
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
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
‘‘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
E:\FR\FM\14JYP1.SGM
14JYP1
Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules
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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(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-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.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
VerDate Sep<11>2014
18:44 Jul 13, 2015
Jkt 235001
40947
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. 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.
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Issued in Renton, Washington, on June 25,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2015–17201 Filed 7–13–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2714; Directorate
Identifier 2014–SW–052–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Airbus
Helicopters Model AS332C1, AS332L1,
AS332L2, EC225LP, AS–365N2, AS 365
N3, EC 155B, and EC155B1 helicopters
with an energy absorbing seat (seat).
This proposed AD would require
inspecting for the presence of labels that
prohibit stowing anything under the
seat. If a label is missing or not clearly
visible to each occupant, installing a
label would be required. This proposed
AD is prompted by the discovery that
required labels had not been
systematically installed. The proposed
actions are intended to prevent objects
from being stowed under the seat as
these objects could reduce the energyabsorbing function of the seat, resulting
in injury to the seat occupants during an
accident.
DATES: We must receive comments on
this proposed AD by September 14,
2015.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
ADDRESSES:
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
European Aviation Safety Agency
(EASA) AD, the economic evaluation,
and other information. The street
address for the Docket Operations Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
For service information identified in
this proposed AD, contact Airbus
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
E:\FR\FM\14JYP1.SGM
14JYP1
]]>Agencies
[Federal Register Volume 80, Number 134 (Tuesday, July 14, 2015)]
[Proposed Rules]
[Pages 40942-40947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17201]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede 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
currently requires 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. Since we issued AD 2009-18-15,
we have determined that existing maintenance requirements and
airworthiness limitations are inadequate to ensure the structural
integrity of the airplane. This proposed AD would require revising the
maintenance or inspection program to incorporate new maintenance
requirements and airworthiness limitations. We are proposing this AD to
prevent failure of certain system components, which could result in
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by August 28, 2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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.
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-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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2461;
Directorate Identifier 2013-NM-202-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On August 24, 2009, we issued AD 2009-18-15, Amendment 39-16011 (74
FR 48143, September 22, 2009). AD 2009-18-15 requires actions intended
to address an unsafe condition 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).
Since we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143,
September 22, 2009), we have determined that more restrictive
maintenance requirements and airworthiness limitations are necessary.
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 by searching for and locating Docket No. FAA-2015-
2461.
[[Page 40943]]
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information, which
describes procedures for revising the maintenance or inspection program
to incorporate new maintenance requirements and airworthiness
limitations.
For Model A300 series airplanes: ``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 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): ``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 Model A300-600 Airworthiness Limitations Section.
For Model A310 series airplanes: ``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 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
NPRM.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 177 airplanes of U.S.
registry.
The 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 would take about 1 work-hour per product
to comply with the new ALS revision of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed 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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus: Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-
202-AD.
(a) Comments Due Date
We must receive comments by August 28, 2015.
(b) Affected ADs
This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 48143,
September 22, 2009).
(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
[[Page 40944]]
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.
(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 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,
with or without using the information in Airbus Service Information
Letter 32-118, Revision 02, dated October 24, 2007: 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 date'')
Designation A300 A310 A300-600 Start date ---------------------------------------
------------------------------------------ P/N
X X X Landings Calendar time
--------------------------------------------------------------------------------------------------------------------------------------------------------
MAIN LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
Aft pintle pin................. 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.
A32140036200xx X December 13, 2007.......... 13,500............ 9 years.
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.
Half ball housing (Fwd pintle A32140042200xx X X December 13, 2007.......... 13,500............ 9 years.
bearing).
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.
[[Page 40945]]
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
[[Page 40946]]
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.
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
[[Page 40947]]
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.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on June 25, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-17201 Filed 7-13-15; 8:45 am]
BILLING CODE 4910-13-P
