Airworthiness Directives; Airbus Airplanes, 37488-37492 [2016-12324]
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Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations
(i) Fokker Service Bulletin SBF28–28–053,
Revision 3, dated January 9, 2014.
(ii) Reserved.
(4) The following service information was
approved for IBR on September 16, 2011 (76
FR 50111, August 12, 2011).
(i) Fokker Service Bulletin SBF28–28–053,
Revision 1, dated September 20, 2010.
(ii) Reserved.
(5) For service information identified in
this AD, contact Fokker Services B.V.,
Technical Services Dept., P.O. Box 1357,
2130 EL Hoofddorp, the Netherlands;
telephone +31 (0)88–6280–350; fax +31
(0)88–6280–111; email technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.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 May 31,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–13545 Filed 6–9–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4813; Directorate
Identifier 2013–NM–161–AD; Amendment
39–18532; AD 2016–11–05]
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 99–16–01
for certain Airbus 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). AD 99–16–
01 required repetitive inspections of
certain bolt holes where parts of the
main landing gear (MLG) are attached to
the wing rear spar, and repair if
necessary. Since we issued AD 99–16–
01, we have determined that the risk of
cracking in the wing rear spar is higher
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This AD becomes effective July
15, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 15, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 9, 1995 (60 FR
52618, October 10, 1995).
ADDRESSES: For service information
identified in this final rule, 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–2015–4813.
DATES:
Examining the AD Docket
RIN 2120–AA64
SUMMARY:
than initially determined. This new AD
adds airplanes to the applicability,
reduces the compliance times and
repetitive intervals for the inspections,
and changes the inspection procedures.
This AD was prompted by a
determination that the risk of cracking
in the wing rear spar is higher than
initially determined. We are issuing this
AD to detect and correct cracking of the
rear spar of the wing, which could result
in reduced structural integrity of the
airplane.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4813; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
PO 00000
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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 99–16–01,
Amendment 39–11236 (64 FR 40743,
July 28, 1999) (‘‘AD 99–16–01’’). AD 99–
16–01 superseded AD 95–20–02,
Amendment 39–9380 (60 FR 52618,
October 10, 1995). AD 99–16–01 applied
to certain Airbus 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). The NPRM
published in the Federal Register on
November 17, 2015 (80 FR 71751) (‘‘the
NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0180, dated August 9,
2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
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). The MCAI states:
During full-scale fatigue testing, cracks
were found on the rear spar from certain bolt
holes at the attachment of the Main Landing
gear (MLG) forward pick-up fitting and the
MLG Rib 5 aft.
This condition, if not detected and
corrected, could reduce the structural
integrity of the aeroplane.
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued * * * [an AD] (later
revised) to require High Frequency Eddy
Current (HFEC) or Ultrasonic (U/S)
inspections of certain fastener holes where
the MLG forward pick-up fitting and MLG
Rib 5 aft are attached to the rear spar.
Since DGAC France * * * [issued a
revised AD, which corresponded to FAA AD
99–16–01, Amendment 39–11236 (64 FR
40743, July 28, 1999), which superseded
FAA AD 95–20–02, Amendment 39–9380 (60
FR 52618, October 10, 1995)] * * *, a fleet
survey and updated Fatigue and Damage
Tolerance analyses have been performed in
order to substantiate the second A300–600
Extended Service Goal (ESG2) exercise. The
results of these analyses have shown that the
threshold and interval must be reduced to
allow timely detection of these cracks and
accomplishment of an applicable corrective
action.
For the reasons described above, this
[EASA] AD retains the requirements of [the
revised DGAC France AD], which is
superseded, but reduces the related
compliance times.
The new, reduced threshold for the
initial inspection ranges between 8,900
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total flight cycles/20,000 total flight
hours, and 34,600 total flight cycles/
77,800 total flight hours, depending on
the modification. The grace periods (750
or 1,500 landings) for airplanes that
have exceeded the specified thresholds
are unchanged from those provided in
AD 99–16–01. The new, reduced
intervals for the repetitive inspections
range between 4,000 flight cycles/9,000
flight hours (whichever occurs first),
and 8,900 flight cycles/20,000 flight
hours (whichever occurs first),
depending on the modification. 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–
4813.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the 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 for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
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Related Service Information Under 1
CFR Part 51
We reviewed Airbus Service Bulletin
A300–57–6017, Revision 04, including
Appendix 1, dated February 4, 2011.
This service information describes
procedures for repetitive inspections of
certain bolt holes where parts of the
MLG are attached to the wing rear spar,
and repair. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 71
airplanes of U.S. registry.
The actions required by AD 99–16–01
and retained in this AD, take about 226
work-hours per product, at an average
labor rate of $85 per work hour.
Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the actions that are
required by AD 99–16–01 is $19,210 per
product, per inspection cycle.
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We also estimate that it will take
about 226 work-hours per product to
comply with the new basic
requirements of this AD. The average
labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of
this AD on U.S. operators to be
$1,363,910, or $19,210 per product.
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this AD.
37489
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.
Authority for This Rulemaking
§ 39.13
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
■
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
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[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
99–16–01, Amendment 39–11236 (64
FR 40743, July 28, 1999), and adding the
following new AD:
2016–11–05 Airbus: Amendment 39–18532;
Docket No. FAA–2015–4813; Directorate
Identifier 2013–NM–161–AD.
(a) Effective Date
This AD becomes effective July 15, 2016.
(b) Affected ADs
This AD replaces AD 99–16–01,
Amendment 39–11236 (64 FR 40743, July 28,
1999) (‘‘AD 99–16–01’’).
(c) Applicability
This AD applies to Airbus Model A300 B4–
601, B4–603, B4–620, and B4–622 airplanes;
Model A300 B4–605R and B4–622R
airplanes; Model A300 F4–605R airplanes;
and Model A300 C4–605R Variant F
airplanes; certificated in any category; all
manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by the results of a
full-scale fatigue test when cracking was
found on the rear spar of the wing, and the
subsequent determination that the risk of
such cracking is higher than initially
determined. We are issuing this AD to detect
and correct cracking of the rear spar of the
wing, 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 Inspections and Corrective
Actions, With Revised Service Information
This paragraph restates the requirements of
paragraphs (a), (b), (c), (d), (e), and (f) of AD
99–16–01 with revised service information
and reduced thresholds and repetitive
intervals, for Airbus Model A300 B4–600,
B4–600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F airplanes;
manufacturer serial numbers (MSNs) 252
through 553 inclusive; except those airplanes
on which Airbus Modification 07601 has
been accomplished prior to delivery.
(1) Perform a high frequency eddy current
(HFEC) rototest inspection to detect cracks in
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Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations
certain bolt holes where the main landing
gear (MLG) forward pick-up fitting and MLG
rib 5 aft are attached to the rear spar, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6017, Revision 01, including Appendix 1,
dated July 25, 1994; or Airbus Service
Bulletin A300–57–6017, Revision 04,
including Appendix 1, dated February 24,
2011. As of the effective date of this AD, only
Airbus Service Bulletin A300–57–6017,
Revision 04, including Appendix 1, dated
February 24, 2011, may be used for the
actions required by this paragraph.
(i) For airplanes that have accumulated
17,300 total landings or less as of November
9, 1995 (the effective date of AD 95–20–02,
Amendment 39–9380 (60 FR 52618, October
10, 1995)) (‘‘AD 95–20–02’’): Inspect prior to
the accumulation of 17,300 total landings, or
within 1,500 landings after November 9,
1995, whichever occurs later.
(ii) For airplanes that have accumulated
17,301 or more total landings, but less than
19,300 total landings as of November 9, 1995
(the effective date of AD 95–20–02): Inspect
within 1,500 landings after November 9,
1995.
(iii) For airplanes that have accumulated
19,300 or more total landings as of November
9, 1995 (the effective date of AD 95–20–02):
Inspect within 750 landings after November
9, 1995 (the effective date of AD 95–20–02).
(2) If no crack is found during the
inspection required by paragraph (g)(1) of
this AD, repeat that inspection thereafter at
the time specified in either paragraph (g)(2)(i)
or (g)(2)(ii) of this AD, as applicable.
(i) For airplanes on which Airbus
Modification 07716 (as specified in Airbus
Service Bulletin A300–57–6020) has not been
accomplished: Inspect at the time specified
in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this
AD, as applicable.
(A) For airplanes having MSNs 465
through 553 inclusive: Repeat the inspection
at intervals not to exceed 13,000 landings,
until the inspection required by paragraph
(g)(4)(ii)(A)(1) of this AD has been
accomplished.
(B) For airplanes having MSNs 252 through
464 inclusive: Repeat the inspection at
intervals not to exceed 8,400 landings, until
the inspection required by paragraph
(g)(4)(ii)(A)(2) of this AD has been
accomplished.
(ii) For airplanes on which Airbus
Modification 07716 has been accomplished:
Inspect at the time specified in either
paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this
AD, as applicable.
(A) For airplanes having MSNs 465
through 553 inclusive: Repeat the inspection
at intervals not to exceed 11,800 landings,
until the inspection required by paragraph
(g)(4)(i)(B) of this AD has been accomplished.
(B) For airplanes having MSNs 252 through
464 inclusive: Repeat the inspection within
10,700 landings following the initial
inspection required by paragraph (g)(1) of
this AD, and thereafter at intervals not to
exceed 7,500 landings, until the inspection
required by paragraph (g)(4)(ii)(B)(2) has been
accomplished.
(3) If any crack is found during the
inspection required by either paragraph (g)(1)
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or (g)(2) of this AD, prior to further flight,
accomplish the requirements of either
paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as
applicable.
(i) For airplanes on which Airbus
Modification 07716 has not been
accomplished: Oversize the bolt hole by 1/32
inch and repeat the HFEC inspection
required by paragraph (g)(1) of this AD, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6017, Revision 01, including Appendix 1,
dated July 25, 1994. After accomplishing the
oversizing and HFEC inspection, repeat the
inspection, as required by paragraph (g)(2) of
this AD, at the applicable schedule specified
in that paragraph, until the inspection
required by paragraph (g)(4)(ii)(B)(1) or
(g)(4)(ii)(B)(2) of this AD has been
accomplished.
(A) If no cracking is detected, install the
second oversize bolt in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6017, Revision 01,
including Appendix 1, dated July 25, 1994.
(B) If any cracking is detected, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate.
(ii) For airplanes on which Airbus
Modification 07716 has been accomplished:
Repair in accordance with a method
approved by the Manager, International
Branch, ANM–116. After repair, repeat the
inspections as required by paragraph (g)(2) of
this AD at the applicable schedule specified
in that paragraph, until the inspection
required by paragraph (g)(4)(ii)(B)(1) or
(g)(4)(ii)(B)(2) of this AD has been
accomplished.
(4) Perform an ultrasonic inspection to
detect cracks in certain bolt holes where the
MLG forward pick-up fitting and MLG rib 5
aft are attached to the rear spar, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6017, Revision 03, dated November 19,
1997; or Revision 04, including Appendix 1,
dated February 24, 2011; at the time specified
in paragraph (g)(4)(i) or (g)(4)(ii) of this AD,
as applicable. As of the effective date of this
AD, only Airbus Service Bulletin A300–57–
6017, Revision 04, including Appendix 1,
dated February 24, 2011, may be used for the
actions in this paragraph.
(i) For airplanes not inspected prior to
September 1, 1999 (the effective date of AD
99–16–01), as specified in Airbus Service
Bulletin A300–57–6017, dated November 22,
1993; or Revision 01, including Appendix 1,
dated July 25, 1994: Inspect at the time
specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B),
or (g)(4)(i)(C) of this AD, as applicable.
Accomplishment of this inspection
terminates the requirements of paragraph
(g)(1) of this AD.
(A) For airplanes that have accumulated
17,300 total landings or fewer as of the
effective date of this AD: Inspect prior to the
accumulation of 17,300 total landings, or
within 1,500 landings after September 1,
1999 (the effective date of AD 99–16–01),
whichever occurs later.
(B) For airplanes that have accumulated
17,301 total landings or more but fewer than
19,300 total landings as of September 1, 1999
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(the effective date of AD 99–16–01): Inspect
within 1,500 landings after September 1,
1999 (the effective date of AD 99–16–01).
(C) For airplanes that have accumulated
19,300 total landings or more as of September
1, 1999 (the effective date of AD 99–16–01):
Inspect within 750 landings after September
1, 1999 (the effective date of AD 99–16–01).
(ii) For airplanes on which an HFEC
inspection was performed prior to September
1, 1999 (the effective date of AD 99–16–01),
in accordance with the requirements of
paragraph (g)(1) of this AD, or in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6017,
dated November 22, 1993: Inspect at the time
specified in paragraph (g)(4)(ii)(A) or
(g)(4)(ii)(B) of this AD, as applicable.
(A) If no cracking was detected during any
HFEC inspection accomplished prior to
September 1, 1999 (the effective date of AD
99–16–01), and if Airbus Modification 07716
has not been accomplished: Inspect at the
time specified in paragraph (g)(4)(ii)(A)(1) or
(g)(4)(ii)(A)(2) of this AD, as applicable.
(1) For airplanes having MSNs 465 through
553 inclusive: Inspect within 13,000 landings
after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,900
landings. Accomplishment of this inspection
constitutes terminating action for the
repetitive inspection requirement of
paragraph (g)(2)(i)(A) of this AD.
(2) For airplanes having MSNs 252 through
464 inclusive: Inspect within 8,400 landings
after the most recent HFEC inspection, and
thereafter at intervals not to exceed 5,500
landings. Accomplishment of this inspection
constitutes terminating action for the
repetitive inspection requirement of
paragraph (g)(2)(i)(B) of this AD.
(B) If any cracking was detected during any
HFEC inspection performed prior to the
effective date of this AD, regardless of the
method of repair, or if Airbus Modification
07716 has been accomplished: Inspect at the
time specified in paragraph (g)(4)(ii)(B)(1) or
(g)(4)(ii)(B)(2) of this AD, as applicable.
(1) For airplanes having MSNs 465 through
553 inclusive: Inspect within 11,800 landings
after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,200
landings. Accomplishment of this inspection
constitutes terminating action for the
repetitive inspection requirement of
paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as
applicable.
(2) For airplanes having MSNs 252 through
464 inclusive: Inspect within 10,700 landings
after the initial inspection in accordance with
paragraph (g)(1) of this AD, or within 7,500
landings after the most recent HFEC
inspection, whichever occurs later, and
thereafter at intervals not to exceed 4,900
landings. Accomplishment of this inspection
constitutes terminating action for the
repetitive inspection requirement of
paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as
applicable.
(5) If no cracking is detected during the
ultrasonic inspection required by paragraph
(g)(4)(i) of this AD, repeat that inspection
thereafter at the time specified in paragraph
(g)(5)(i) or (g)(5)(ii) of this AD, as applicable,
until the initial ultrasonic inspection
required by paragraph (h) of this AD is done.
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(i) For airplanes having MSNs 465 through
553 inclusive: Repeat the inspection at
intervals not to exceed 8,900 landings.
(ii) For airplanes having MSNs 232 through
464 inclusive: Repeat the inspection at
intervals not to exceed 5,500 landings.
(6) If any cracking is detected during any
inspection performed in accordance with the
requirements of paragraph (g)(4) or (g)(5) of
this AD: Prior to further flight, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116; or
´ ´
the Direction Generale de l’Aviation Civile
(or its delegated agent); or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
Note 1 to paragraph (g) of this AD: Airbus
Service Bulletin A300–57–6017, Revision 01,
including Appendix 1, dated July 25, 1994;
and Airbus Service Bulletin A300–57–6017,
Revision 04, including Appendix 1, dated
February 24, 2011; also reference Airbus
Service Bulletin A300–57–6020, dated
November 22, 1993, as an additional source
of service information for installation of
oversize studs in the bolt holes.
(h) New Repetitive Inspections
At the applicable times specified in
paragraph 1.B.(5), ‘‘Accomplishment
Timescale,’’ of Airbus Service Bulletin A300–
57–6017, Revision 04, including Appendix 1,
dated February 24, 2011: Do ultrasonic
inspections to detect cracks in the MLG
attachment fitting holes on the wing rear
spar, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6017, Revision 04,
including Appendix 1, dated February 24,
2011. Repeat the inspections thereafter at the
applicable intervals specified in paragraph
1.B.(5), ‘‘Accomplishment Timescale,’’ of
Airbus Service Bulletin A300–57–6017,
Revision 04, including Appendix 1, dated
February 24, 2011. For airplanes modified as
specified in Airbus Service Bulletin A300–
57–6073, the initial inspection threshold is
counted from the completion date of the
modification. Clarification of compliance
time terminology used in table 1, ‘‘Structural
Inspection Program,’’ of Airbus Service
Bulletin A300–57–6017, Revision 04,
including Appendix 1, dated February 24,
2011, is provided in paragraphs (h)(1)
through (h)(4) of this AD. Accomplishment of
the initial inspection terminates the
repetitive inspections required by paragraph
(g)(5) of this AD.
(1) For pre-Airbus Modification 07716 or
pre-Airbus Modification 11440 airplanes:
(i) The term ‘‘flight cycles’’ in the
‘‘Inspection Threshold’’ column is total flight
cycles accumulated by the airplane.
(ii) The term ‘‘flight hours’’ in the
‘‘Inspection Threshold’’ column is total flight
hours accumulated by the airplane.
(2) For post-Airbus Modification 07716
airplanes:
(i) The term ‘‘flight cycles’’ in the
‘‘Inspection Threshold’’ column is total flight
cycles accumulated by the airplane.
(ii) The term ‘‘flight hours’’ in the
‘‘Inspection Threshold’’ column is total flight
hours accumulated by the airplane.
(3) For post-Airbus Modification 11440
(Airbus Service Bulletin A300–57–6073)
airplanes:
VerDate Sep<11>2014
16:32 Jun 09, 2016
Jkt 238001
(i) The term ‘‘flight cycles’’ in the
‘‘Inspection Threshold’’ column is flight
cycles accumulated by the airplane after the
modification was done.
(ii) The term ‘‘flight hours’’ in the
‘‘Inspection Threshold’’ column is flight
hours accumulated by the airplane after the
modification was done.
(4) For post-Airbus Modification 07601
airplanes:
(i) The term ‘‘flight cycles’’ in the
‘‘Inspection Threshold’’ column is total flight
cycles accumulated by the airplane.
(ii) The term ‘‘flight hours’’ in the
‘‘Inspection Threshold’’ column is total flight
hours accumulated by the airplane.
(i) Repairs
If any crack is found during any inspection
required by paragraph (h) of this AD: Before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus’s
EASA DOA.
(j) Non-Terminating Repair
Accomplishment of any repair as required
by paragraph (i) of this AD is not terminating
action for the repetitive inspections required
by paragraph (g) or (h) of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using any of the
following service information.
(1) Airbus Service Bulletin A300–57–6017,
dated November 22, 1993, which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A300–57–6017,
Revision 01, including Appendix 1, dated
July 25, 1994, which was incorporated by
reference in AD 95–20–02 and is retained in
this AD.
(3) Airbus Service Bulletin A300–57–6017,
Revision 02, dated January 14, 1997,
including Appendix 1, dated July 25, 1994,
which is not incorporated by reference in this
AD.
(4) Airbus Service Bulletin A300–57–6017,
Revision 03, including Appendix 1, dated
November 19, 1997, which was incorporated
by reference in AD 99–16–01, but is not
retained in 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–
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
37491
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
99–16–01 are approved as AMOCs for the
corresponding provisions of 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
EASA; or Airbus’s EASA 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 2013–0180, dated
August 9, 2013, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov
searching for and locating Docket No. FAA–
2015–4813.
(2) Service information identified in this
AD that is not incorporated by reference 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 July 15, 2016.
(i) Airbus Service Bulletin A300–57–6017,
Revision 04, including Appendix 1, dated
February 24, 2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on November 9, 1995 (60
FR 52618, October 10, 1995).
(i) Airbus Service Bulletin A300–57–6017,
Revision 01, including Appendix 1, dated
July 25, 1994.
(ii) Reserved.
(5) 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.
(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
E:\FR\FM\10JNR1.SGM
10JNR1
37492
Federal Register / Vol. 81, No. 112 / Friday, June 10, 2016 / Rules and Regulations
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 18,
2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–12324 Filed 6–9–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2134; Directorate
Identifier 2015–CE–012–AD; Amendment
39–18547; AD 2016–11–20]
RIN 2120–AA64
Airworthiness Directives; B/E
Aerospace Protective Breathing
Equipment Part Number 119003–11
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
B/E Aerospace protective breathing
equipment (PBE) that is installed on
airplanes. This AD was prompted by a
report of a PBE catching fire upon
activation by a crewmember. This AD
requires replacing the PBE. We are
issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective July 15,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 15, 2016.
ADDRESSES: For service information
identified in this final rule, contact B/
E Aerospace, Inc., Commercial Aircraft
Products Group, 10800 Pflumm Road,
Lenexa, Kansas 66215; phone: (913)
338–9800; fax: (913) 338–8419; Internet:
www.beaerospace.com. You may view
this referenced service information at
the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2134.
asabaliauskas on DSK3SPTVN1PROD with RULES
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
VerDate Sep<11>2014
16:32 Jun 09, 2016
Jkt 238001
and locating Docket No. FAA–2015–
2134; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
David Enns, Aerospace Engineer,
Wichita Aircraft Certification Office,
FAA, 1801 S. Airport Road, Room 100,
Wichita, Kansas 67209; phone: (316)
946–4147; fax: (316) 946–4107; email:
david.enns@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain B/E
Aerospace protective breathing
equipment (PBE) that is installed on
airplanes. The SNPRM published in the
Federal Register on January 15, 2016
(81 FR 2131). We preceded the SNPRM
with a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on June 16, 2015 (80 FR 34330).
The NPRM proposed to require
inspecting the PBE to determine if the
pouch has the proper vacuum seal and
replacing if necessary. The NPRM was
prompted by a report of a PBE catching
fire upon activation by a crewmember.
The SNPRM proposed to require
replacement of the PBE following newly
issued service information, regardless of
inspection results. We are issuing this
AD to correct the unsafe condition on
these products.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
We received one anonymous comment
in support of the SNPRM (81 FR 2131,
January 15, 2016).
Request To Change Compliance Time
Penney Baudin of United Airlines
requested a change to the PBE
replacement compliance time.
The commenter requested a 12-month
repetitive inspection with a 36-month
terminating replacement action. The
commenter stated that the change would
alleviate restrictive shipping means and
complex distribution of the PBEs since
the units contain oxygen generators.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
We do not agree with the commenter.
We believe that the replacement
compliance time of 18 months after the
effective date of this AD is sufficient
time since we are allowing even more
time than specified in the related
service information. Also, the public has
been aware of this safety issue since we
first published the first NPRM on June
16, 2015 (80 FR 34330). We have not
changed the final rule AD action based
on this comment.
Request To Correct Service Information
John Barker of B/E Aerospace stated
that Service Bulletin 119003–35–009,
dated November 9, 2015, is incorrectly
referenced as Rev. 009 instead of Rev.
000 in the preamble of the SNPRM (81
FR 2131, January 15, 2016). The
commenter requested the reference to
the revision number be corrected.
We agree with the commenter.
However, on April 12, 2016, Rev. 001 of
B/E Aerospace Service Bulletin 119003–
35–009 was released. We are
incorporating the Revision 001, dated
April 12, 2016, into the final rule AD
action because the procedures for doing
the inspection and replacement of the
PBE have not changed.
We have changed the final rule AD
action to include the newly revised
service bulletin and to give credit to
owners/operators who may have already
done the required replacement
following B/E Aerospace Service
Bulletin No. 119003–35–009, Rev. 000,
dated November 9, 2015, which was
correctly referenced in paragraph (h) of
the regulatory text in the SNPRM (81 FR
2131, January 15, 2016).
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (81 FR
2131, January 15, 2016) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (81 FR 2131,
January 15, 2016).
Related Service Information Under 1
CFR Part 51
We reviewed B/E Aerospace Service
Bulletin No. 119003–35–011, Rev. 000,
dated February 4, 2015, and B/E
Aerospace Service Bulletin 119003–35–
009, Rev. 001, dated April 12, 2016. B/
E Aerospace Service Bulletin No.
119003–35–011, Rev. 000, dated
E:\FR\FM\10JNR1.SGM
10JNR1
]]>Agencies
[Federal Register Volume 81, Number 112 (Friday, June 10, 2016)]
[Rules and Regulations]
[Pages 37488-37492]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12324]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD;
Amendment 39-18532; AD 2016-11-05]
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) 99-16-01 for
certain Airbus 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). AD 99-16-01 required
repetitive inspections of certain bolt holes where parts of the main
landing gear (MLG) are attached to the wing rear spar, and repair if
necessary. Since we issued AD 99-16-01, we have determined that the
risk of cracking in the wing rear spar is higher than initially
determined. This new AD adds airplanes to the applicability, reduces
the compliance times and repetitive intervals for the inspections, and
changes the inspection procedures. This AD was prompted by a
determination that the risk of cracking in the wing rear spar is higher
than initially determined. We are issuing this AD to detect and correct
cracking of the rear spar of the wing, which could result in reduced
structural integrity of the airplane.
DATES: This AD becomes effective July 15, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 15,
2016.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 9, 1995 (60 FR 52618, October 10, 1995).
ADDRESSES: For service information identified in this final rule,
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-
4813.
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-
4813; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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 99-16-01, Amendment 39-11236 (64 FR 40743, July
28, 1999) (``AD 99-16-01''). AD 99-16-01 superseded AD 95-20-02,
Amendment 39-9380 (60 FR 52618, October 10, 1995). AD 99-16-01 applied
to certain Airbus 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). The NPRM published in the
Federal Register on November 17, 2015 (80 FR 71751) (``the NPRM'').
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0180, dated August 9, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus 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). The MCAI states:
During full-scale fatigue testing, cracks were found on the rear
spar from certain bolt holes at the attachment of the Main Landing
gear (MLG) forward pick-up fitting and the MLG Rib 5 aft.
This condition, if not detected and corrected, could reduce the
structural integrity of the aeroplane.
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued * * * [an AD] (later revised) to require High
Frequency Eddy Current (HFEC) or Ultrasonic (U/S) inspections of
certain fastener holes where the MLG forward pick-up fitting and MLG
Rib 5 aft are attached to the rear spar.
Since DGAC France * * * [issued a revised AD, which corresponded
to FAA AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999),
which superseded FAA AD 95-20-02, Amendment 39-9380 (60 FR 52618,
October 10, 1995)] * * *, a fleet survey and updated Fatigue and
Damage Tolerance analyses have been performed in order to
substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses have shown that the
threshold and interval must be reduced to allow timely detection of
these cracks and accomplishment of an applicable corrective action.
For the reasons described above, this [EASA] AD retains the
requirements of [the revised DGAC France AD], which is superseded,
but reduces the related compliance times.
The new, reduced threshold for the initial inspection ranges between
8,900
[[Page 37489]]
total flight cycles/20,000 total flight hours, and 34,600 total flight
cycles/77,800 total flight hours, depending on the modification. The
grace periods (750 or 1,500 landings) for airplanes that have exceeded
the specified thresholds are unchanged from those provided in AD 99-16-
01. The new, reduced intervals for the repetitive inspections range
between 4,000 flight cycles/9,000 flight hours (whichever occurs
first), and 8,900 flight cycles/20,000 flight hours (whichever occurs
first), depending on the modification. 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-2015-4813.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the 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 for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Service Bulletin A300-57-6017, Revision 04,
including Appendix 1, dated February 4, 2011. This service information
describes procedures for repetitive inspections of certain bolt holes
where parts of the MLG are attached to the wing rear spar, and repair.
This service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 71 airplanes of U.S. registry.
The actions required by AD 99-16-01 and retained in this AD, take
about 226 work-hours per product, at an average labor rate of $85 per
work hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the actions that are required by AD 99-
16-01 is $19,210 per product, per inspection cycle.
We also estimate that it will take about 226 work-hours per product
to comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $1,363,910, or $19,210 per product.
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and adding
the following new AD:
2016-11-05 Airbus: Amendment 39-18532; Docket No. FAA-2015-4813;
Directorate Identifier 2013-NM-161-AD.
(a) Effective Date
This AD becomes effective July 15, 2016.
(b) Affected ADs
This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743,
July 28, 1999) (``AD 99-16-01'').
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and
B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model
A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes;
certificated in any category; all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by the results of a full-scale fatigue test
when cracking was found on the rear spar of the wing, and the
subsequent determination that the risk of such cracking is higher
than initially determined. We are issuing this AD to detect and
correct cracking of the rear spar of the wing, 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 Inspections and Corrective Actions, With Revised Service
Information
This paragraph restates the requirements of paragraphs (a), (b),
(c), (d), (e), and (f) of AD 99-16-01 with revised service
information and reduced thresholds and repetitive intervals, for
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and
Model A300 C4-605R Variant F airplanes; manufacturer serial numbers
(MSNs) 252 through 553 inclusive; except those airplanes on which
Airbus Modification 07601 has been accomplished prior to delivery.
(1) Perform a high frequency eddy current (HFEC) rototest
inspection to detect cracks in
[[Page 37490]]
certain bolt holes where the main landing gear (MLG) forward pick-up
fitting and MLG rib 5 aft are attached to the rear spar, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July
25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04,
including Appendix 1, dated February 24, 2011. As of the effective
date of this AD, only Airbus Service Bulletin A300-57-6017, Revision
04, including Appendix 1, dated February 24, 2011, may be used for
the actions required by this paragraph.
(i) For airplanes that have accumulated 17,300 total landings or
less as of November 9, 1995 (the effective date of AD 95-20-02,
Amendment 39-9380 (60 FR 52618, October 10, 1995)) (``AD 95-20-
02''): Inspect prior to the accumulation of 17,300 total landings,
or within 1,500 landings after November 9, 1995, whichever occurs
later.
(ii) For airplanes that have accumulated 17,301 or more total
landings, but less than 19,300 total landings as of November 9, 1995
(the effective date of AD 95-20-02): Inspect within 1,500 landings
after November 9, 1995.
(iii) For airplanes that have accumulated 19,300 or more total
landings as of November 9, 1995 (the effective date of AD 95-20-02):
Inspect within 750 landings after November 9, 1995 (the effective
date of AD 95-20-02).
(2) If no crack is found during the inspection required by
paragraph (g)(1) of this AD, repeat that inspection thereafter at
the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of
this AD, as applicable.
(i) For airplanes on which Airbus Modification 07716 (as
specified in Airbus Service Bulletin A300-57-6020) has not been
accomplished: Inspect at the time specified in paragraph
(g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable.
(A) For airplanes having MSNs 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 13,000 landings, until the
inspection required by paragraph (g)(4)(ii)(A)(1) of this AD has
been accomplished.
(B) For airplanes having MSNs 252 through 464 inclusive: Repeat
the inspection at intervals not to exceed 8,400 landings, until the
inspection required by paragraph (g)(4)(ii)(A)(2) of this AD has
been accomplished.
(ii) For airplanes on which Airbus Modification 07716 has been
accomplished: Inspect at the time specified in either paragraph
(g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable.
(A) For airplanes having MSNs 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 11,800 landings, until the
inspection required by paragraph (g)(4)(i)(B) of this AD has been
accomplished.
(B) For airplanes having MSNs 252 through 464 inclusive: Repeat
the inspection within 10,700 landings following the initial
inspection required by paragraph (g)(1) of this AD, and thereafter
at intervals not to exceed 7,500 landings, until the inspection
required by paragraph (g)(4)(ii)(B)(2) has been accomplished.
(3) If any crack is found during the inspection required by
either paragraph (g)(1) or (g)(2) of this AD, prior to further
flight, accomplish the requirements of either paragraph (g)(3)(i) or
(g)(3)(ii) of this AD, as applicable.
(i) For airplanes on which Airbus Modification 07716 has not
been accomplished: Oversize the bolt hole by 1/32 inch and repeat
the HFEC inspection required by paragraph (g)(1) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July
25, 1994. After accomplishing the oversizing and HFEC inspection,
repeat the inspection, as required by paragraph (g)(2) of this AD,
at the applicable schedule specified in that paragraph, until the
inspection required by paragraph (g)(4)(ii)(B)(1) or
(g)(4)(ii)(B)(2) of this AD has been accomplished.
(A) If no cracking is detected, install the second oversize bolt
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July
25, 1994.
(B) If any cracking is detected, repair in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
(ii) For airplanes on which Airbus Modification 07716 has been
accomplished: Repair in accordance with a method approved by the
Manager, International Branch, ANM-116. After repair, repeat the
inspections as required by paragraph (g)(2) of this AD at the
applicable schedule specified in that paragraph, until the
inspection required by paragraph (g)(4)(ii)(B)(1) or
(g)(4)(ii)(B)(2) of this AD has been accomplished.
(4) Perform an ultrasonic inspection to detect cracks in certain
bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft
are attached to the rear spar, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6017, Revision 03,
dated November 19, 1997; or Revision 04, including Appendix 1, dated
February 24, 2011; at the time specified in paragraph (g)(4)(i) or
(g)(4)(ii) of this AD, as applicable. As of the effective date of
this AD, only Airbus Service Bulletin A300-57-6017, Revision 04,
including Appendix 1, dated February 24, 2011, may be used for the
actions in this paragraph.
(i) For airplanes not inspected prior to September 1, 1999 (the
effective date of AD 99-16-01), as specified in Airbus Service
Bulletin A300-57-6017, dated November 22, 1993; or Revision 01,
including Appendix 1, dated July 25, 1994: Inspect at the time
specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C)
of this AD, as applicable. Accomplishment of this inspection
terminates the requirements of paragraph (g)(1) of this AD.
(A) For airplanes that have accumulated 17,300 total landings or
fewer as of the effective date of this AD: Inspect prior to the
accumulation of 17,300 total landings, or within 1,500 landings
after September 1, 1999 (the effective date of AD 99-16-01),
whichever occurs later.
(B) For airplanes that have accumulated 17,301 total landings or
more but fewer than 19,300 total landings as of September 1, 1999
(the effective date of AD 99-16-01): Inspect within 1,500 landings
after September 1, 1999 (the effective date of AD 99-16-01).
(C) For airplanes that have accumulated 19,300 total landings or
more as of September 1, 1999 (the effective date of AD 99-16-01):
Inspect within 750 landings after September 1, 1999 (the effective
date of AD 99-16-01).
(ii) For airplanes on which an HFEC inspection was performed
prior to September 1, 1999 (the effective date of AD 99-16-01), in
accordance with the requirements of paragraph (g)(1) of this AD, or
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time
specified in paragraph (g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as
applicable.
(A) If no cracking was detected during any HFEC inspection
accomplished prior to September 1, 1999 (the effective date of AD
99-16-01), and if Airbus Modification 07716 has not been
accomplished: Inspect at the time specified in paragraph
(g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) of this AD, as applicable.
(1) For airplanes having MSNs 465 through 553 inclusive: Inspect
within 13,000 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,900 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (g)(2)(i)(A) of this AD.
(2) For airplanes having MSNs 252 through 464 inclusive: Inspect
within 8,400 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 5,500 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (g)(2)(i)(B) of this AD.
(B) If any cracking was detected during any HFEC inspection
performed prior to the effective date of this AD, regardless of the
method of repair, or if Airbus Modification 07716 has been
accomplished: Inspect at the time specified in paragraph
(g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD, as applicable.
(1) For airplanes having MSNs 465 through 553 inclusive: Inspect
within 11,800 landings after the most recent HFEC inspection, and
thereafter at intervals not to exceed 8,200 landings. Accomplishment
of this inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this
AD, as applicable.
(2) For airplanes having MSNs 252 through 464 inclusive: Inspect
within 10,700 landings after the initial inspection in accordance
with paragraph (g)(1) of this AD, or within 7,500 landings after the
most recent HFEC inspection, whichever occurs later, and thereafter
at intervals not to exceed 4,900 landings. Accomplishment of this
inspection constitutes terminating action for the repetitive
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this
AD, as applicable.
(5) If no cracking is detected during the ultrasonic inspection
required by paragraph (g)(4)(i) of this AD, repeat that inspection
thereafter at the time specified in paragraph (g)(5)(i) or
(g)(5)(ii) of this AD, as applicable, until the initial ultrasonic
inspection required by paragraph (h) of this AD is done.
[[Page 37491]]
(i) For airplanes having MSNs 465 through 553 inclusive: Repeat
the inspection at intervals not to exceed 8,900 landings.
(ii) For airplanes having MSNs 232 through 464 inclusive: Repeat
the inspection at intervals not to exceed 5,500 landings.
(6) If any cracking is detected during any inspection performed
in accordance with the requirements of paragraph (g)(4) or (g)(5) of
this AD: Prior to further flight, repair in accordance with a method
approved by the Manager, International Branch, ANM-116; or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent); or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
Note 1 to paragraph (g) of this AD: Airbus Service Bulletin
A300-57-6017, Revision 01, including Appendix 1, dated July 25,
1994; and Airbus Service Bulletin A300-57-6017, Revision 04,
including Appendix 1, dated February 24, 2011; also reference Airbus
Service Bulletin A300-57-6020, dated November 22, 1993, as an
additional source of service information for installation of
oversize studs in the bolt holes.
(h) New Repetitive Inspections
At the applicable times specified in paragraph 1.B.(5),
``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-
6017, Revision 04, including Appendix 1, dated February 24, 2011: Do
ultrasonic inspections to detect cracks in the MLG attachment
fitting holes on the wing rear spar, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6017,
Revision 04, including Appendix 1, dated February 24, 2011. Repeat
the inspections thereafter at the applicable intervals specified in
paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service
Bulletin A300-57-6017, Revision 04, including Appendix 1, dated
February 24, 2011. For airplanes modified as specified in Airbus
Service Bulletin A300-57-6073, the initial inspection threshold is
counted from the completion date of the modification. Clarification
of compliance time terminology used in table 1, ``Structural
Inspection Program,'' of Airbus Service Bulletin A300-57-6017,
Revision 04, including Appendix 1, dated February 24, 2011, is
provided in paragraphs (h)(1) through (h)(4) of this AD.
Accomplishment of the initial inspection terminates the repetitive
inspections required by paragraph (g)(5) of this AD.
(1) For pre-Airbus Modification 07716 or pre-Airbus Modification
11440 airplanes:
(i) The term ``flight cycles'' in the ``Inspection Threshold''
column is total flight cycles accumulated by the airplane.
(ii) The term ``flight hours'' in the ``Inspection Threshold''
column is total flight hours accumulated by the airplane.
(2) For post-Airbus Modification 07716 airplanes:
(i) The term ``flight cycles'' in the ``Inspection Threshold''
column is total flight cycles accumulated by the airplane.
(ii) The term ``flight hours'' in the ``Inspection Threshold''
column is total flight hours accumulated by the airplane.
(3) For post-Airbus Modification 11440 (Airbus Service Bulletin
A300-57-6073) airplanes:
(i) The term ``flight cycles'' in the ``Inspection Threshold''
column is flight cycles accumulated by the airplane after the
modification was done.
(ii) The term ``flight hours'' in the ``Inspection Threshold''
column is flight hours accumulated by the airplane after the
modification was done.
(4) For post-Airbus Modification 07601 airplanes:
(i) The term ``flight cycles'' in the ``Inspection Threshold''
column is total flight cycles accumulated by the airplane.
(ii) The term ``flight hours'' in the ``Inspection Threshold''
column is total flight hours accumulated by the airplane.
(i) Repairs
If any crack is found during any inspection required by
paragraph (h) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA
DOA.
(j) Non-Terminating Repair
Accomplishment of any repair as required by paragraph (i) of
this AD is not terminating action for the repetitive inspections
required by paragraph (g) or (h) of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using any of the following
service information.
(1) Airbus Service Bulletin A300-57-6017, dated November 22,
1993, which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A300-57-6017, Revision 01, including
Appendix 1, dated July 25, 1994, which was incorporated by reference
in AD 95-20-02 and is retained in this AD.
(3) Airbus Service Bulletin A300-57-6017, Revision 02, dated
January 14, 1997, including Appendix 1, dated July 25, 1994, which
is not incorporated by reference in this AD.
(4) Airbus Service Bulletin A300-57-6017, Revision 03, including
Appendix 1, dated November 19, 1997, which was incorporated by
reference in AD 99-16-01, but is not retained in 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.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 99-16-01 are approved as
AMOCs for the corresponding provisions of 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 EASA; or Airbus's EASA 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 2013-0180, dated August 9, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov searching for and
locating Docket No. FAA-2015-4813.
(2) Service information identified in this AD that is not
incorporated by reference 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
July 15, 2016.
(i) Airbus Service Bulletin A300-57-6017, Revision 04, including
Appendix 1, dated February 24, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
November 9, 1995 (60 FR 52618, October 10, 1995).
(i) Airbus Service Bulletin A300-57-6017, Revision 01, including
Appendix 1, dated July 25, 1994.
(ii) Reserved.
(5) 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.
(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
[[Page 37492]]
202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 18, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-12324 Filed 6-9-16; 8:45 am]
BILLING CODE 4910-13-P
