Airworthiness Directives; Airbus Airplanes, 12401-12405 [2017-03951]
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Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations
Issued in Renton, Washington, on February
17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03968 Filed 3–2–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9298; Directorate
Identifier 2015–NM–161–AD; Amendment
39–18811; AD 2017–05–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes.
This AD was prompted by an evaluation
by the design approval holder (DAH)
that indicates that a section of the wing
and aft fuselage is subject to widespread
fatigue damage (WFD). This AD requires
an inspection to determine if certain
modifications have been done. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 7,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 7, 2017.
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:
continued.airworthiness-wb.external@
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–2016–9298.
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SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9298; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket 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 by adding an AD that would
apply to all Airbus Model A300 series
airplanes. The NPRM published in the
Federal Register on October 26, 2016
(81 FR 74354) (‘‘the NPRM’’). The
NPRM was prompted by an evaluation
by the DAH that indicates that a section
of the wing and aft fuselage is subject to
WFD. The NPRM proposed to require an
inspection to determine if certain
modifications have been done. For
airplanes on which the specified
modifications have not been done, this
AD requires accomplishing those
modifications, including doing related
investigative and corrective actions if
necessary. We are issuing this AD to
prevent reduced structural integrity of
these airplanes due to the failure of
certain structural components.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2015–
0173R1, dated August 31, 2016,
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A300
series airplanes. The MCAI states:
A widespread fatigue damage (WFD)
analysis conducted on A300 aeroplanes
identified areas which are susceptible to
crack development.
This condition, if not corrected, could
affect the structural integrity of the
aeroplane.
To address this issue, Airbus developed a
modification (mod) to reinforce the structure
of the aeroplane. Airbus issued Service
Bulletin (SB) A300–53–0271 to provide
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12401
instructions for a cold expansion of the foot
attachment holes of certain fuselage frames,
´ ´
and DGAC [Direction Generale de l’Aviation
Civile] France issued AD F–2004–001 to
require this mod [which corresponds with
certain requirements in FAA AD 2004–23–
20, Amendment 39–13875 (69 FR 68779,
November 26, 2004)].
Since that [DGAC] AD was issued, Airbus
released twelve other mods with
corresponding SBs, to complete the set of
inspections and repairs in the frame of the
A300 WFD campaign. EASA issued AD
2015–0115 to require ten of these mods
through section 3 of ALS [Airworthiness
Limitations Section] Part 2, and decision is
made to delete section 3 from ALS Part 2.
For the reasons described above, EASA
issued AD 2015–0173, retaining the
requirements of DGAC France AD F–2004–
001, which was superseded, to require
implementation of the additional inspection,
modification and/or repair actions, as
applicable to aeroplane model.
This [EASA] AD is revised to give credit
for previous use of any earlier revision of an
affected Airbus SB, based on the fact that no
additional work is included in the later SB
revisions.
Required actions include an
inspection to determine if certain
modifications have been done. For
airplanes on which the specified
modifications have not been done, this
AD requires accomplishing those
modifications, including doing related
investigative and corrective actions if
necessary. Depending on airplane
configuration, the compliance times for
modifying the airplane structure range
between 13,300 flight cycles and 48,000
flight cycles since first flight of the
airplane. You may examine the MCAI in
the AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9298.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting 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
Airbus issued the following service
information:
• Airbus Service Bulletin A300–53–
0239, Revision 02, dated March 6, 2000.
This service information describes
procedures to modify the longitudinal
junction. The modification includes the
addition of external doublers and
installation of interference fit
attachments and related investigative
and corrective actions. The related
investigative actions are rotary probe
inspections for cracking of the fastener
holes. The corrective action is repair.
• Airbus Service Bulletin A300–53–
247, Revision 2, dated July 20, 1990.
This service information describes
procedures to modify the fuselage upper
door frame structure, which consists of
eddy current inspections of certain
structure for cracks, and structural
modification or repair.
• Airbus Service Bulletin A300–53–
0271, Revision 05, dated June 21, 2013.
This service information describes
procedures to modify the fuselage frame
(FR), which includes cold expansion of
the fastener holes between FR 41 and FR
54, and related investigative and
corrective actions. The related
investigative actions including rotary
probe inspections for cracking of the
fastener holes. The corrective action is
repair.
• Airbus Service Bulletin A300–53–
0366, dated April 7, 2005. This service
information describes procedures to
modify the fuselage frame, which
includes installing an additional
external doubler on the fuselage lap
joint at fuselage stringers (STGR) 22, left
and right, between FR 26 and FR 40.
• Airbus Service Bulletin A300–53–
0368, dated April 7, 2005. This service
information describes procedures to
modify the rear fuselage, which
includes installing an additional
external doubler on the fuselage lap
joint at STGR 51, left and right, between
FR 72 and FR 80.
• Airbus Service Bulletin A300–53–
0369, Revision 03, dated September 1,
2010. This service information describes
procedures to modify the rear fuselage,
which includes reinforcing the butt joint
at FR 72 by installation of an additional
external doubler at the butt joint of FR
72 at STGR 14, left and right.
• Airbus Service Bulletin A300–53–
0373, Revision 03, dated September 1,
2010. This service information describes
procedures to modify the rear fuselage,
which includes reinforcing the butt joint
at FR65 by installation of an additional
external doubler at the butt joint of
FR65 between STGR 13 left and right.
• Airbus Service Bulletin A300–53–
0374, Revision 04, dated July 5, 2013.
This service information describes
procedures to modify the rear fuselage,
which includes reinforcing the butt
joints at FR55 and FR58 by installation
of additional external doublers without
cutout at certain butt joints.
• Airbus Service Bulletin A300–53–
0375, Revision 01, dated June 24, 2013.
This service information describes
procedures to modify the forward
fuselage, which includes reinforcing the
fuselage circumferential butt joint at FR
26 by installation of an additional
external doubler at the butt joint of FR
26 between STGR 13 left and STGR 13
right.
• Airbus Service Bulletin A300–53–
0393, dated September 27, 2013. This
service information describes
procedures to modify the fuselage frame
which includes reinforcing the
longitudinal butt joints with additional
butt straps at certain fuselage frames
and stringers.
• Airbus Service Bulletin A300–57–
0203, Revision 04, dated February 18,
2015. This service information describes
procedures to modify the outer wing,
which includes removal of the wing
stringer and run-out plate at STGR 19 on
the bottom wing skin; replacement of
the taper-lok bolts with interference fit
parallel bolts; and related investigative
and corrective actions. Related
investigative actions include detailed
visual and high frequency eddy current
(HFEC) inspections of the stringer
runouts for cracks; eddy current
inspections for cracks of the fastener
holes; and detailed visual and HFEC
inspections of the stringer run-outs for
cracks and damage. Corrective actions
include repair.
• Airbus Service Bulletin A300–57–
0258, dated September 30, 2014 (for
Model A300 B4–103 and A300 B4–2C
airplanes). This service information
describes procedures to modify the wing
structure, which includes a first
oversize of the critical holes on certain
wing stringers, and related investigative
and corrective actions. Related
investigated actions include detailed
visual inspections for damage of the top
wing skin external surface and the
stringer joint; and roto-probe
inspections for damage of the fastener
holes. Corrective actions include repair.
• Airbus Service Bulletin A300–57–
0259, dated September 30, 2014 (for
Model A300 B2–1C, A300 B2–203, and
A300 B2K–3C airplanes). This service
information describes procedures to
modify the wing structure, which
includes a first oversize of the critical
holes on certain wing stringers, and
related investigative and corrective
actions. Related investigated actions
include detailed visual inspections for
damage of the top wing skin external
surface and the stringer joint; and rotoprobe inspections for damage of the
fastener holes. Corrective actions
include 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 8
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Modification .............................
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Action
3,291 work-hours × $85 per hour = $279,735 .......................
In addition, we estimate that any
necessary follow-on actions will take
about 15 work-hours and require parts
costing $10,000, for a cost of $11,275
per product. We have no way of
determining the number of aircraft that
might need this action.
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Parts cost
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
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$142,845
Cost per
product
$422,580
Cost on U.S.
operators
$3,380,640
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
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Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations
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:
and B4–203 airplanes, certificated in any
category, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder that indicates that
a section of the wing and aft fuselage is
subject to widespread fatigue damage. We are
issuing this AD to prevent reduced structural
integrity of these airplanes due to the failure
of certain structural components.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
(f) Compliance
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
12403
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–05–01 Airbus: Amendment 39–18811;
Docket No. FAA–2016–9298; Directorate
Identifier 2015–NM–161–AD.
(a) Effective Date
This AD is effective April 7, 2017.
(b) Affected ADs
This AD affects AD 2004–23–20,
Amendment 39–13875 (69 FR 68779,
November 26, 2004) (‘‘AD 2004–23–20’’).
(c) Applicability
This AD applies to Airbus Model A300 B2–
1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103,
Comply with this AD within the
compliance times specified, unless already
done.
(g) Verification of Embodied Modifications
Within 4 months after the effective date of
this AD, verify whether the Airbus
modifications specified in table 1 to
paragraphs (g), (h), and (i) of this AD, as
applicable to airplane model, have been
embodied on the airplane, in accordance
with the Accomplishment Instructions of the
applicable Airbus service bulletin specified
in table 1 to paragraphs (g), (h), and (i) of this
AD. A review of the airplane maintenance
records is acceptable to accomplish the
verification required by this paragraph,
provided those records can be used to
conclusively determine whether the
modifications have been embodied.
TABLE 1 TO PARAGRAPHS (g), (h), AND (i) OF THIS AD—AIRBUS MODIFICATION AND APPLICABLE SERVICE BULLETIN
Set
Airbus modification
Set 1A .............................................
751 .................................................
7301 ...............................................
10326 .............................................
12735 .............................................
12736 .............................................
12737 .............................................
12798 .............................................
07757 and 12977 ..........................
13611 .............................................
13692 .............................................
13716 .............................................
12794 .............................................
12796 .............................................
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Set 1B .............................................
(h) Corrective Actions for Modifications
Which Have Not Been Embodied
If, during the verification required by
paragraph (g) of this AD, it is determined that
any modification has not been embodied, do
the applicable actions specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this
AD.
(1) If it is determined that any Airbus
modification, specified in the applicable
Airbus Service Bulletin, identified in ‘‘Set
1A’’ of table 1 to paragraphs (g), (h), and (i)
of this AD is not embodied: Within the
applicable compliance time specified in the
applicable Airbus Service Bulletin identified
in ‘‘Set 1A’’ of table 1 to paragraphs (g), (h),
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Applicable Airbus service bulletin
A300–53–247, Revision 2, dated July 20, 1990.
A300–53–0239, Revision 02, dated March 6, 2000.
A300–57–0203, Revision 04, dated February 18, 2015.
A300–53–0366, dated April 7, 2005.
A300–53–0368, dated April 7, 2005.
A300–53–0369, Revision 03, dated September 1, 2010.
A300–53–0375, Revision 01, dated June 24, 2013.
A300–53–0271, Revision 05, dated June 21, 2013.
A300–57–0258, dated September 30, 2014.
A300–53–0393, dated September 27, 2013.
A300–57–0259, dated September 30, 2014.
A300–53–0374, Revision 04, dated July 5, 2013.
A300–53–0373, Revision 03, dated September 1, 2010.
and (i) of this AD, or within 4 months after
the effective date of this AD, whichever
occurs later, do the applicable actions
specified in paragraphs (h)(1)(i) through
(h)(1)(xi) of this AD, except as required by
paragraph (i) of this AD. Do all applicable
related investigative and corrective actions
before further flight.
(i) For airplanes on which Airbus Service
Bulletin A300–53–0239, Revision 02, dated
March 6, 2000, has not been embodied:
Modify the longitudinal junction and do all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
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Service Bulletin A300–53–0239, Revision 02,
dated March 6, 2000.
(ii) For airplanes on which Airbus Service
Bulletin A300–53–247, Revision 2, dated July
20, 1990, has not been embodied: Modify the
fuselage upper door frame structure by doing
eddy current inspections for cracks of the
structure specified in Airbus Service Bulletin
A300–53–247, Revision 2, dated July 20,
1990, and a structural modification or repair,
as applicable, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–247, Revision 2,
dated July 20, 1990.
(iii) For airplanes on which Airbus Service
Bulletin A300–53–0271, Revision 05, dated
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June 21, 2013, has not been embodied:
Modify the fuselage frame, and do all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0271, Revision 05,
dated June 21, 2013.
(iv) For airplanes on which Airbus Service
Bulletin A300–53–0366, dated April 7, 2005,
has not been embodied: Modify the fuselage
frame, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0366, dated April
7, 2005.
(v) For airplanes on which Airbus Service
Bulletin A300–53–0368, dated April 7, 2005,
has not been embodied: Modify the rear
fuselage, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–0366, dated April
7, 2005.
(vi) For airplanes on which Airbus Service
Bulletin A300–53–0369, Revision 03, dated
September 1, 2010, has not been embodied:
Modify the rear fuselage, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–53–0369, Revision 03,
dated September 1, 2010.
(vii) For airplanes on which Airbus Service
Bulletin A300–53–0375, Revision 01, dated
June 24, 2013, has not been embodied:
Modify the forward fuselage, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–53–0375,
Revision 01, dated June 24, 2013.
(viii) For airplanes on which Airbus
Service Bulletin A300–53–0393, dated
September 27, 2013, has not been embodied:
Modify the fuselage frame, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–53–0393,
dated September 27, 2013.
(ix) For airplanes on which Airbus Service
Bulletin A300–57–0203, Revision 04, dated
February 18, 2015, has not been embodied:
Modify the outer wing, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0203, Revision 04, dated February 18,
2015.
(x) For airplanes on which Airbus Service
Bulletin A300–57–0258, dated September 30,
2014, has not been embodied: Modify the
wing structure and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0258, dated September 30, 2014.
(xi) For airplanes on which Airbus Service
Bulletin A300–57–0259, dated September 30,
2014, has not been embodied: Modify the
wing structure, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0259, dated September 30, 2014.
(2) If it is determined that Airbus Service
Bulletin A300–53–0374, Revision 04 dated
July 5, 2013 (mod 12794) has not been
embodied: Within the compliance time
specified in paragraphs (h)(2)(i), (h)(2)(ii),
(h)(2)(iii), and (h)(2)(iv) of this AD, as
applicable, modify the rear fuselage, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
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53–0374, Revision 04, dated July 5, 2013,
except as required by paragraph (i) of this
AD.
(i) For Model A300 B2 and A300 B4–100
airplanes, fuselage frame (FR) 55: Within
31,300 flight cycles since first flight of the
airplane, or within 4 months after the
effective date of this AD, whichever occurs
later.
(ii) For Model A300 B2 and A300 B4–100
airplanes, FR 58: Within 49,700 flight cycles
since first flight of the airplane, or within 4
months after the effective date of this AD,
whichever occurs later.
(iii) For Model A300 B4–200 airplanes, FR
55: Within 33,600 flight cycles since first
flight of the airplane, or within 4 months
after the effective date of this AD, whichever
occurs later.
(iv) For Model A300 B4–200 airplanes, FR
58: Within 55,800 flight cycles since first
flight of the airplane, or within 4 months
after the effective date of this AD, whichever
occurs later.
(3) If it is determined that Airbus Service
Bulletin A300–53–0373, Revision 03, dated
September 1, 2010 (mod 12796) has not been
embodied: Within the compliance time
specified in paragraphs (h)(3)(i), (h)(3)(ii),
and (h)(3)(iii) of this AD, as applicable,
modify the rear fuselage, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–53–0373, Revision 03,
dated September 1, 2010, except as required
by paragraph (i) of this AD.
(i) For Model A300 B2 airplanes: Within
42,700 flight cycles since first flight of the
airplane, or within 4 months after the
effective date of this AD, whichever occurs
later.
(ii) For Model A300 B4–100 airplanes:
Within 41,700 flight cycles since first flight
of the airplane, or within 4 months after the
effective date of this AD, whichever occurs
later.
(iii) For Model A300 B4–200 airplanes:
Within 47,900 flight cycles since first flight
of the airplane, or within 4 months after the
effective date of this AD, whichever occurs
later.
(i) Exception to the Service Information
Where any service information identified
in table 1 to paragraphs (g), (h), and (i) of this
AD specifies to contact the manufacturer for
instructions or solutions, before further
flight, repair 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).
(j) Terminating Action for Certain
Requirements in AD 2004–23–20
Accomplishing the modification required
by paragraph (h)(1)(iii) of this AD terminates
the modification required by paragraph (i) of
AD 2004–23–20 for that airplane only.
(k) 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
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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 425–227–1405; fax 425–227–2125.
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.
(2) Contacting the Manufacturer: 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.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0173R1, dated August 31, 2016, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–9298.
(m) 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.
(i) Airbus Service Bulletin A300–53–0239,
Revision 02, dated March 6, 2000.
(ii) Airbus Service Bulletin A300–53–247,
Revision 2, dated July 20, 1990.
(iii) Airbus Service Bulletin A300–53–
0271, Revision 05, dated June 21, 2013.
(iv) Airbus Service Bulletin A300–53–
0366, dated April 7, 2005.
(v) Airbus Service Bulletin A300–53–0368,
dated April 7, 2005.
(vi) Airbus Service Bulletin A300–53–
0369, Revision 03, dated September 1, 2010.
(vii) Airbus Service Bulletin A300–53–
0373, Revision 03, dated September 1, 2010.
E:\FR\FM\03MRR1.SGM
03MRR1
Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations
(viii) Airbus Service Bulletin A300–53–
0374, Revision 04, dated July 5, 2013.
(ix) Airbus Service Bulletin A300–53–
0375, Revision 01, dated June 24, 2013.
(x) Airbus Service Bulletin A300–53–0393,
dated September 27, 2013.
(xi) Airbus Service Bulletin A300–57–
0203, Revision 04, dated February 18, 2015.
(xii) Airbus Service Bulletin A300–57–
0258, dated September 30, 2014.
(xiii) Airbus Service Bulletin A300–57–
0259, dated September 30, 2014.
(3) 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:
continued.airworthiness-wb.external@
airbus.com; Internet https://www.airbus.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03951 Filed 3–2–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9357; Directorate
Identifier 2016–CE–030–AD; Amendment
39–18798; AD 2017–04–03]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Pilatus
Aircraft Ltd. Models PC–6, PC–6–H1,
PC–6–H2, PC–6/350, PC–6/350–H1, PC–
6/350–H2, PC–6/A, PC–6/A–H1, PC–6/
A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/
B2–H2, PC–6/B2–H4, PC–6/C–H2, and
PC–6/C1–H2 airplanes. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
mstockstill on DSK3G9T082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:07 Mar 02, 2017
Jkt 241001
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as certain combinations of the
aileron counterweight and the attaching
parts possibly resulting in reduced
thread engagement and leading to
disconnection of the aileron
counterweight from the aileron. We are
issuing this AD to require actions to
address the unsafe condition on these
products.
DATES: This AD is effective April 7,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 7, 2017.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9357; or in person at 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 service information identified in
this AD, contact Pilatus Aircraft Ltd.,
Customer Technical Support (MCC),
P.O. Box 992, CH–6371 Stans,
Switzerland; phone: +41 (0)41 619 3333;
fax: +41 (0)41 619 7311; email:
supportPC12@pilatus-aircraft.com;
Internet: https://www.pilatusaircraft.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 Docket No. FAA–2016–
9357.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Pilatus Aircraft Ltd. Models
PC–6, PC–6–H1, PC–6–H2, PC–6/350,
PC–6/350–H1, PC–6/350–H2, PC–6/A,
PC–6/A–H1, PC–6/A–H2, PC–6/B–H2,
PC–6/B1–H2, PC–6/B2–H2, PC–6/B2–
H4, PC–6/C–H2, and PC–6/C1–H2
airplanes. The NPRM was published in
the Federal Register on November 4,
2016 (81 FR 76883). The NPRM
proposed to correct an unsafe condition
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
12405
for the specified products and was
based on mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country. The MCAI states:
The proper installation of the aileron
counterweight requires a combination,
peculiar to each aileron, of anchor nut types,
bolt types, number of washers, and the
definition of the bolt torque. Some
combinations of counterweight and attaching
parts, which could result in reduced thread
engagement, have been reported on a PC–6
aeroplane.
This condition, if not detected and
corrected, may lead to a disconnection of the
aileron counterweight from the aileron,
possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition,
Pilatus issued Service Bulletin (SB) No. 57–
006 (hereafter referred to as ‘the SB’ in this
AD) to provide inspection instructions.
For the reason described above, this AD
requires identification and inspection of the
affected aileron mass-balance counterweight
attachment parts and, depending on findings,
accomplishment of applicable corrective
action(s).
The MCAI can be found in the AD
docket on the Internet at: https://www.
regulations.gov/document?D=FAA2016-9357-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the proposal and the FAA’s
response to the comment.
Request for Clarification on the Unsafe
Condition
Lukas Owens stated that in the event
of loss of the ailerons, some degree of
roll control is available by using the
secondary effect of rudder. The
requester stated that while not an
efficient way to turn the aircraft, a pilot
has at least some directional control and
that short or rapid bursts of power may
increase the effectiveness of the rudder
to some degree, acting as a form of
torque and slipstream effect. The
requester asked why the AD change is
needed or how it is justified.
We infer that the commenter, in
addition to asking why the AD action is
necessary and how it is justified,
believes the AD action is not needed
and is not justified. However, the
commenter does not present solutions
that address the unsafe condition of the
mass balance weight potentially
separating from the airplane. For this
reason, we have not changed this AD
based on this comment.
Conclusion
We reviewed the relevant data,
considered the comment received, and
E:\FR\FM\03MRR1.SGM
03MRR1
Agencies
[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)]
[Rules and Regulations]
[Pages 12401-12405]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03951]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9298; Directorate Identifier 2015-NM-161-AD;
Amendment 39-18811; AD 2017-05-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A300 series airplanes. This AD was prompted by an
evaluation by the design approval holder (DAH) that indicates that a
section of the wing and aft fuselage is subject to widespread fatigue
damage (WFD). This AD requires an inspection to determine if certain
modifications have been done. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 7, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 7,
2017.
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: continued.airworthiness-wb.external@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-2016-9298.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9298; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket 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 by adding an AD that would apply to all Airbus Model A300
series airplanes. The NPRM published in the Federal Register on October
26, 2016 (81 FR 74354) (``the NPRM''). The NPRM was prompted by an
evaluation by the DAH that indicates that a section of the wing and aft
fuselage is subject to WFD. The NPRM proposed to require an inspection
to determine if certain modifications have been done. For airplanes on
which the specified modifications have not been done, this AD requires
accomplishing those modifications, including doing related
investigative and corrective actions if necessary. We are issuing this
AD to prevent reduced structural integrity of these airplanes due to
the failure of certain structural components.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2015-0173R1, dated August 31, 2016, (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus Model A300 series airplanes.
The MCAI states:
A widespread fatigue damage (WFD) analysis conducted on A300
aeroplanes identified areas which are susceptible to crack
development.
This condition, if not corrected, could affect the structural
integrity of the aeroplane.
To address this issue, Airbus developed a modification (mod) to
reinforce the structure of the aeroplane. Airbus issued Service
Bulletin (SB) A300-53-0271 to provide instructions for a cold
expansion of the foot attachment holes of certain fuselage frames,
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD F-2004-001 to require this mod [which corresponds
with certain requirements in FAA AD 2004-23-20, Amendment 39-13875
(69 FR 68779, November 26, 2004)].
Since that [DGAC] AD was issued, Airbus released twelve other
mods with corresponding SBs, to complete the set of inspections and
repairs in the frame of the A300 WFD campaign. EASA issued AD 2015-
0115 to require ten of these mods through section 3 of ALS
[Airworthiness Limitations Section] Part 2, and decision is made to
delete section 3 from ALS Part 2.
For the reasons described above, EASA issued AD 2015-0173,
retaining the requirements of DGAC France AD F-2004-001, which was
superseded, to require implementation of the additional inspection,
modification and/or repair actions, as applicable to aeroplane
model.
This [EASA] AD is revised to give credit for previous use of any
earlier revision of an affected Airbus SB, based on the fact that no
additional work is included in the later SB revisions.
Required actions include an inspection to determine if certain
modifications have been done. For airplanes on which the specified
modifications have not been done, this AD requires accomplishing those
modifications, including doing related investigative and corrective
actions if necessary. Depending on airplane configuration, the
compliance times for modifying the airplane structure range between
13,300 flight cycles and 48,000 flight cycles since first flight of the
airplane. You may examine the MCAI in the AD docket on the Internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2016-9298.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting 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.
[[Page 12402]]
Related Service Information Under 1 CFR Part 51
Airbus issued the following service information:
Airbus Service Bulletin A300-53-0239, Revision 02, dated
March 6, 2000. This service information describes procedures to modify
the longitudinal junction. The modification includes the addition of
external doublers and installation of interference fit attachments and
related investigative and corrective actions. The related investigative
actions are rotary probe inspections for cracking of the fastener
holes. The corrective action is repair.
Airbus Service Bulletin A300-53-247, Revision 2, dated
July 20, 1990. This service information describes procedures to modify
the fuselage upper door frame structure, which consists of eddy current
inspections of certain structure for cracks, and structural
modification or repair.
Airbus Service Bulletin A300-53-0271, Revision 05, dated
June 21, 2013. This service information describes procedures to modify
the fuselage frame (FR), which includes cold expansion of the fastener
holes between FR 41 and FR 54, and related investigative and corrective
actions. The related investigative actions including rotary probe
inspections for cracking of the fastener holes. The corrective action
is repair.
Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
This service information describes procedures to modify the fuselage
frame, which includes installing an additional external doubler on the
fuselage lap joint at fuselage stringers (STGR) 22, left and right,
between FR 26 and FR 40.
Airbus Service Bulletin A300-53-0368, dated April 7, 2005.
This service information describes procedures to modify the rear
fuselage, which includes installing an additional external doubler on
the fuselage lap joint at STGR 51, left and right, between FR 72 and FR
80.
Airbus Service Bulletin A300-53-0369, Revision 03, dated
September 1, 2010. This service information describes procedures to
modify the rear fuselage, which includes reinforcing the butt joint at
FR 72 by installation of an additional external doubler at the butt
joint of FR 72 at STGR 14, left and right.
Airbus Service Bulletin A300-53-0373, Revision 03, dated
September 1, 2010. This service information describes procedures to
modify the rear fuselage, which includes reinforcing the butt joint at
FR65 by installation of an additional external doubler at the butt
joint of FR65 between STGR 13 left and right.
Airbus Service Bulletin A300-53-0374, Revision 04, dated
July 5, 2013. This service information describes procedures to modify
the rear fuselage, which includes reinforcing the butt joints at FR55
and FR58 by installation of additional external doublers without cutout
at certain butt joints.
Airbus Service Bulletin A300-53-0375, Revision 01, dated
June 24, 2013. This service information describes procedures to modify
the forward fuselage, which includes reinforcing the fuselage
circumferential butt joint at FR 26 by installation of an additional
external doubler at the butt joint of FR 26 between STGR 13 left and
STGR 13 right.
Airbus Service Bulletin A300-53-0393, dated September 27,
2013. This service information describes procedures to modify the
fuselage frame which includes reinforcing the longitudinal butt joints
with additional butt straps at certain fuselage frames and stringers.
Airbus Service Bulletin A300-57-0203, Revision 04, dated
February 18, 2015. This service information describes procedures to
modify the outer wing, which includes removal of the wing stringer and
run-out plate at STGR 19 on the bottom wing skin; replacement of the
taper-lok bolts with interference fit parallel bolts; and related
investigative and corrective actions. Related investigative actions
include detailed visual and high frequency eddy current (HFEC)
inspections of the stringer runouts for cracks; eddy current
inspections for cracks of the fastener holes; and detailed visual and
HFEC inspections of the stringer run-outs for cracks and damage.
Corrective actions include repair.
Airbus Service Bulletin A300-57-0258, dated September 30,
2014 (for Model A300 B4-103 and A300 B4-2C airplanes). This service
information describes procedures to modify the wing structure, which
includes a first oversize of the critical holes on certain wing
stringers, and related investigative and corrective actions. Related
investigated actions include detailed visual inspections for damage of
the top wing skin external surface and the stringer joint; and roto-
probe inspections for damage of the fastener holes. Corrective actions
include repair.
Airbus Service Bulletin A300-57-0259, dated September 30,
2014 (for Model A300 B2-1C, A300 B2-203, and A300 B2K-3C airplanes).
This service information describes procedures to modify the wing
structure, which includes a first oversize of the critical holes on
certain wing stringers, and related investigative and corrective
actions. Related investigated actions include detailed visual
inspections for damage of the top wing skin external surface and the
stringer joint; and roto-probe inspections for damage of the fastener
holes. Corrective actions include 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 8 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Modification....................... 3,291 work-hours x $85 per $142,845 $422,580 $3,380,640
hour = $279,735.
----------------------------------------------------------------------------------------------------------------
In addition, we estimate that any necessary follow-on actions will
take about 15 work-hours and require parts costing $10,000, for a cost
of $11,275 per product. We have no way of determining the number of
aircraft that might need this action.
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
[[Page 12403]]
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 adding the following new airworthiness
directive (AD):
2017-05-01 Airbus: Amendment 39-18811; Docket No. FAA-2016-9298;
Directorate Identifier 2015-NM-161-AD.
(a) Effective Date
This AD is effective April 7, 2017.
(b) Affected ADs
This AD affects AD 2004-23-20, Amendment 39-13875 (69 FR 68779,
November 26, 2004) (``AD 2004-23-20'').
(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, certificated in any
category, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder that indicates that a section of the wing and aft fuselage is
subject to widespread fatigue damage. We are issuing this AD to
prevent reduced structural integrity of these airplanes due to the
failure of certain structural components.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Verification of Embodied Modifications
Within 4 months after the effective date of this AD, verify
whether the Airbus modifications specified in table 1 to paragraphs
(g), (h), and (i) of this AD, as applicable to airplane model, have
been embodied on the airplane, in accordance with the Accomplishment
Instructions of the applicable Airbus service bulletin specified in
table 1 to paragraphs (g), (h), and (i) of this AD. A review of the
airplane maintenance records is acceptable to accomplish the
verification required by this paragraph, provided those records can
be used to conclusively determine whether the modifications have
been embodied.
Table 1 to Paragraphs (g), (h), and (i) of This AD--Airbus Modification
and Applicable Service Bulletin
------------------------------------------------------------------------
Airbus Applicable Airbus
Set modification service bulletin
------------------------------------------------------------------------
Set 1A........................ 751.............. A300-53-247, Revision
2, dated July 20,
1990.
7301............. A300-53-0239,
Revision 02, dated
March 6, 2000.
10326............ A300-57-0203,
Revision 04, dated
February 18, 2015.
12735............ A300-53-0366, dated
April 7, 2005.
12736............ A300-53-0368, dated
April 7, 2005.
12737............ A300-53-0369,
Revision 03, dated
September 1, 2010.
12798............ A300-53-0375,
Revision 01, dated
June 24, 2013.
07757 and 12977.. A300-53-0271,
Revision 05, dated
June 21, 2013.
13611............ A300-57-0258, dated
September 30, 2014.
13692............ A300-53-0393, dated
September 27, 2013.
13716............ A300-57-0259, dated
September 30, 2014.
Set 1B........................ 12794............ A300-53-0374,
Revision 04, dated
July 5, 2013.
12796............ A300-53-0373,
Revision 03, dated
September 1, 2010.
------------------------------------------------------------------------
(h) Corrective Actions for Modifications Which Have Not Been Embodied
If, during the verification required by paragraph (g) of this
AD, it is determined that any modification has not been embodied, do
the applicable actions specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD.
(1) If it is determined that any Airbus modification, specified
in the applicable Airbus Service Bulletin, identified in ``Set 1A''
of table 1 to paragraphs (g), (h), and (i) of this AD is not
embodied: Within the applicable compliance time specified in the
applicable Airbus Service Bulletin identified in ``Set 1A'' of table
1 to paragraphs (g), (h), and (i) of this AD, or within 4 months
after the effective date of this AD, whichever occurs later, do the
applicable actions specified in paragraphs (h)(1)(i) through
(h)(1)(xi) of this AD, except as required by paragraph (i) of this
AD. Do all applicable related investigative and corrective actions
before further flight.
(i) For airplanes on which Airbus Service Bulletin A300-53-0239,
Revision 02, dated March 6, 2000, has not been embodied: Modify the
longitudinal junction and do all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0239, Revision 02,
dated March 6, 2000.
(ii) For airplanes on which Airbus Service Bulletin A300-53-247,
Revision 2, dated July 20, 1990, has not been embodied: Modify the
fuselage upper door frame structure by doing eddy current
inspections for cracks of the structure specified in Airbus Service
Bulletin A300-53-247, Revision 2, dated July 20, 1990, and a
structural modification or repair, as applicable, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
247, Revision 2, dated July 20, 1990.
(iii) For airplanes on which Airbus Service Bulletin A300-53-
0271, Revision 05, dated
[[Page 12404]]
June 21, 2013, has not been embodied: Modify the fuselage frame, and
do all applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-0271, Revision 05, dated June 21, 2013.
(iv) For airplanes on which Airbus Service Bulletin A300-53-
0366, dated April 7, 2005, has not been embodied: Modify the
fuselage frame, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
(v) For airplanes on which Airbus Service Bulletin A300-53-0368,
dated April 7, 2005, has not been embodied: Modify the rear
fuselage, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
(vi) For airplanes on which Airbus Service Bulletin A300-53-
0369, Revision 03, dated September 1, 2010, has not been embodied:
Modify the rear fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0369, Revision 03,
dated September 1, 2010.
(vii) For airplanes on which Airbus Service Bulletin A300-53-
0375, Revision 01, dated June 24, 2013, has not been embodied:
Modify the forward fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0375, Revision 01,
dated June 24, 2013.
(viii) For airplanes on which Airbus Service Bulletin A300-53-
0393, dated September 27, 2013, has not been embodied: Modify the
fuselage frame, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0393, dated September 27, 2013.
(ix) For airplanes on which Airbus Service Bulletin A300-57-
0203, Revision 04, dated February 18, 2015, has not been embodied:
Modify the outer wing, and do all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0203, Revision 04,
dated February 18, 2015.
(x) For airplanes on which Airbus Service Bulletin A300-57-0258,
dated September 30, 2014, has not been embodied: Modify the wing
structure and do all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-0258, dated September 30, 2014.
(xi) For airplanes on which Airbus Service Bulletin A300-57-
0259, dated September 30, 2014, has not been embodied: Modify the
wing structure, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0259, dated
September 30, 2014.
(2) If it is determined that Airbus Service Bulletin A300-53-
0374, Revision 04 dated July 5, 2013 (mod 12794) has not been
embodied: Within the compliance time specified in paragraphs
(h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as
applicable, modify the rear fuselage, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-0374,
Revision 04, dated July 5, 2013, except as required by paragraph (i)
of this AD.
(i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame
(FR) 55: Within 31,300 flight cycles since first flight of the
airplane, or within 4 months after the effective date of this AD,
whichever occurs later.
(ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within
49,700 flight cycles since first flight of the airplane, or within 4
months after the effective date of this AD, whichever occurs later.
(iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600
flight cycles since first flight of the airplane, or within 4 months
after the effective date of this AD, whichever occurs later.
(iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800
flight cycles since first flight of the airplane, or within 4 months
after the effective date of this AD, whichever occurs later.
(3) If it is determined that Airbus Service Bulletin A300-53-
0373, Revision 03, dated September 1, 2010 (mod 12796) has not been
embodied: Within the compliance time specified in paragraphs
(h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable,
modify the rear fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0373, Revision 03,
dated September 1, 2010, except as required by paragraph (i) of this
AD.
(i) For Model A300 B2 airplanes: Within 42,700 flight cycles
since first flight of the airplane, or within 4 months after the
effective date of this AD, whichever occurs later.
(ii) For Model A300 B4-100 airplanes: Within 41,700 flight
cycles since first flight of the airplane, or within 4 months after
the effective date of this AD, whichever occurs later.
(iii) For Model A300 B4-200 airplanes: Within 47,900 flight
cycles since first flight of the airplane, or within 4 months after
the effective date of this AD, whichever occurs later.
(i) Exception to the Service Information
Where any service information identified in table 1 to
paragraphs (g), (h), and (i) of this AD specifies to contact the
manufacturer for instructions or solutions, before further flight,
repair 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).
(j) Terminating Action for Certain Requirements in AD 2004-23-20
Accomplishing the modification required by paragraph (h)(1)(iii)
of this AD terminates the modification required by paragraph (i) of
AD 2004-23-20 for that airplane only.
(k) 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 425-227-1405; fax 425-227-2125. 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.
(2) Contacting the Manufacturer: 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.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA AD 2015-0173R1, dated August 31, 2016, for related information.
This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-9298.
(m) 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.
(i) Airbus Service Bulletin A300-53-0239, Revision 02, dated
March 6, 2000.
(ii) Airbus Service Bulletin A300-53-247, Revision 2, dated July
20, 1990.
(iii) Airbus Service Bulletin A300-53-0271, Revision 05, dated
June 21, 2013.
(iv) Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
(v) Airbus Service Bulletin A300-53-0368, dated April 7, 2005.
(vi) Airbus Service Bulletin A300-53-0369, Revision 03, dated
September 1, 2010.
(vii) Airbus Service Bulletin A300-53-0373, Revision 03, dated
September 1, 2010.
[[Page 12405]]
(viii) Airbus Service Bulletin A300-53-0374, Revision 04, dated
July 5, 2013.
(ix) Airbus Service Bulletin A300-53-0375, Revision 01, dated
June 24, 2013.
(x) Airbus Service Bulletin A300-53-0393, dated September 27,
2013.
(xi) Airbus Service Bulletin A300-57-0203, Revision 04, dated
February 18, 2015.
(xii) Airbus Service Bulletin A300-57-0258, dated September 30,
2014.
(xiii) Airbus Service Bulletin A300-57-0259, dated September 30,
2014.
(3) 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: continued.airworthiness-wb.external@airbus.com; Internet https://www.airbus.com.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03951 Filed 3-2-17; 8:45 am]
BILLING CODE 4910-13-P