Airworthiness Directives; Airbus Airplanes, 52832-52835 [2017-24501]
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52832
Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
(d) Subject
Joint Aircraft System Component (JASC)
Code 7531, Compressor bleed governor.
Burlington, MA 01803; phone: 781–238–
7754; fax: 781–238–7199; email: john.frost@
faa.gov.
(e) Unsafe Condition
This AD was prompted by an engine fire
that occurred as a result of malfunctions
related to the operability bleed valve (OBV).
We are issuing this AD to prevent failure of
the OBV. The unsafe condition, if not
corrected, could result in failure of the OBV,
engine fire, and damage to the airplane.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) General Electric Company (GE) Service
Bulletin CF34–8C–AL S/B 75–0019 Revision
01, dated October 24, 2017.
(ii) Reserved.
(3) For GE service information identified in
this AD, contact General Electric Company,
GE-Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215, phone: 513–552–3272;
fax: 513–552–3329; email: geae.aoc@ge.com.
(4) You may view this service information
at FAA, FAA, Engine & Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(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.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Inspect the bleed air manifold link rod
assemblies and the OBV supply, return, and
drain fuel fittings within 500 flight hours
after the effective date of this AD.
(2) Use the Accomplishment Instructions,
paragraph 3.B., in GE Service Bulletin (SB)
CF34–8C–AL S/B 75–0019 Revision 01, dated
October 24, 2017, to do the inspection.
Replace parts that fail this inspection
according to the following criteria:
(i) Replace any OBV that fails the
inspection with a part eligible for installation
before further flight.
(ii) Replace any additional hardware that
fails inspection within 50 flight cycles. The
engine can be returned to service each day
for up to the 50 flight cycles if the OBV rosan
rings and fittings are examined each day for
fuel leaks and looseness based on the criteria
in Table 1 of GE SB CF34–8C–AL S/B 75–
0019 Revision 01, dated October 24, 2017.
(3) The reporting instructions in
paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and
3.B.(8) of GE SB CF34–8C–AL S/B 75–0019
Revision 01, dated October 24, 2017, are not
required by this AD.
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(h) Credit for Previous Actions
You may take credit for the actions that are
required by paragraph (g) of this AD if you
performed these actions before the effective
date of this AD using GE CF34–8C SB 75–
0019 R00, dated August 4, 2017.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO Branch, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to the attention of the person
identified in paragraph (j) of this AD. You
may email your request to: ANE-AD-AMOC@
faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
For more information about this AD,
contact John Frost, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue,
VerDate Sep<11>2014
15:48 Nov 14, 2017
Jkt 244001
Issued in Burlington, Massachusetts, on
November 9, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2017–24700 Filed 11–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0710; Product
Identifier 2017–NM–019–AD; Amendment
39–19098; AD 2017–23–04]
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 certain
Airbus Model A300 B4–600R series
airplanes; Model A300 B4–603, B4–620,
and B4–622 airplanes; Model A300 C4–
605R Variant F airplanes; and Model
A300 F4–605R airplanes. This AD was
prompted by a determination that the
top stringer joints at rib 18 are an area
of uniform stress distribution, which
SUMMARY:
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indicates that cracks may develop in
adjacent stringers at the same time. This
AD requires an inspection of the upper
wing skin and top stringer joints, and
modification of the stringer joint
couplings if necessary. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective December
20, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 20, 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 account.airworth-eas@
airbus.com; Internet https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0710.
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–2017–
0710; 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 Section, Transport
Standards Branch, 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 certain Airbus Model A300 B4–
600R series airplanes; Model A300 B4–
603, B4–620, and B4–622 airplanes;
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Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
Model A300 C4–605R Variant F
airplanes; and Model A300 F4–605R
airplanes. The NPRM published in the
Federal Register on July 27, 2017 (82 FR
34885) (‘‘the NPRM’’). The NPRM was
prompted by a determination that the
top stringer joints at rib 18 are an area
of uniform stress distribution, which
indicates that cracks may develop in
adjacent stringers at the same time. The
NPRM proposed to require an
inspection of the upper wing skin and
top stringer joints, and modification of
the stringer joint couplings if necessary.
We are issuing this AD to detect and
correct damage (including cracking) at
the stringer joints, which could reduce
the structural integrity of the wing.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0023,
dated February 10, 2017 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A300 B4–600R
series airplanes; Model A300 B4–603,
B4–620, and B4–622 airplanes; Model
A300 C4–605R Variant F airplanes; and
Model A300 F4–605R airplanes. The
MCAI states:
Prompted by the conclusion of the WFD
analysis, Airbus issued Service Bulletin (SB)
A300–57–6118 to provide modification
instructions. The modification will both relife via oversizing and inspect via nondestructive test a defined number of stringer
joint fastener holes at Rib 18. This
modification will delay the onset of cracking
at the stringer joint, providing it is completed
at the specified time and will delay the
requirement for subsequent inspection.
For the reasons described above, this
[EASA] AD requires a detailed visual
inspection (DVI) [for damage, including
cracking] of the upper wing skin and the top
stringer joints at Rib 18, [and corrective
action if necessary] and modification of the
stringer joint couplings at Rib 18, on both
wings [as applicable].
In response to the FAA Part 26 rule change
concerning Widespread Fatigue Damage
(WFD), all wing structural items of the A300–
600 design deemed potentially susceptible to
WFD were assessed. The top stringer joints
at Rib 18 were highlighted as an area of
uniform stress distribution, indicating that
cracks may develop in adjacent stringers at
the same time which is known as Multi
Element Damage (MED). Each affected
stringer joint consists of three main load
transferring parts: An overlapping flange, two
straps attached through the stringer web and
a strap on the top flange. All the components
of the joint are attached with fasteners. The
fastener holes were the subject of a MED
WFD analysis, which showed that cracking
could occur from a number of the holes in
the joint on stringers 11, 12, 13, 14, 15, 16,
17, and 18.
This condition, if not detected and
corrected, could reduce the structural
integrity of the wing.
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
The modification includes a related
investigative action, i.e., a special
detailed (roto-probe) inspection for
damage, including cracking, of the
fastener holes in the upper wing skin,
and corrective action if necessary.
Corrective actions include repairing any
damage.
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–2017–
0710.
Comments
Request To Update the Costs of
Compliance
FedEx supported the intent of the
NPRM, but requested that we update the
parts cost in the Costs of Compliance
section of the proposed AD to reflect the
cost of two parts kits. FedEx noted that
the proposed AD listed the parts cost for
only one kit. FedEx pointed out that
operators may need to modify both
wings and could therefore need two
parts kits per airplane.
We agree with the commenter’s
request. We have revised the Costs of
Compliance section of this final rule to
52833
reflect two parts kits, each costing
$4,770.
Request To Fix a Typographical Error
Airbus requested that we correct a
reference to ‘‘Airbus Model A300 C4–
605 Variant F’’ airplanes in paragraph
(g)(2) of the proposed AD. The correct
model name is ‘‘A300 C4–605R Variant
F’’ airplanes.
We agree with the commenter’s
request. We have corrected the
typographical error in this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–57–6118, Revision 01, dated
January 31, 2017. This service
information describes procedures for an
inspection of the upper wing skin and
top stringer joints at rib 18, and
modification of the stringer joint
couplings. 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 65
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per product
Inspection and modification .................
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Action
37 work-hours × $85 per hour =
$3,145.
Up to $9,540 .........
Up to $12,685 .......
We have received no definitive data
that will allow us to provide cost
estimates for certain on-condition
actions specified in this AD.
VerDate Sep<11>2014
15:48 Nov 14, 2017
Jkt 244001
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Cost on U.S.
operators
Up to $824,525.
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
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52834
Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
sradovich on DSK3GMQ082PROD with RULES
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
1. The authority citation for part 39
continues to read as follows:
■
VerDate Sep<11>2014
15:48 Nov 14, 2017
Jkt 244001
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–23–04 Airbus: Amendment 39–19098;
Docket No. FAA–2017–0710; Product
Identifier 2017–NM–019–AD.
(a) Effective Date
This AD is effective December 20, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4–
605R, B4–622R, B4–603, C4–605R Variant F,
B4–620, B4–622, and F4–605R airplanes,
certificated in any category, all serial
numbers except Model A300 F4–605R
airplanes that have embodied Airbus
modification 12699 in production.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a determination
that the top stringer joints at rib 18 are an
area of uniform stress distribution, which
indicates that cracks may develop in adjacent
stringers at the same time. We are issuing this
AD to detect and correct damage (including
cracking) at the stringer joints, which could
reduce the structural integrity of the wing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definitions
For the purposes of this AD, the definitions
in paragraphs (g)(1) through (g)(5) of this AD
apply.
(1) Group 1 airplanes are defined as Airbus
Model A300 B4–603, B4–605R, B4–620, B4–
622, and B4–622R airplanes.
(2) Group 2 airplanes are defined as Airbus
Model A300 C4–605R Variant F and F4–605R
(if in pre-modification 12699 configuration)
airplanes.
(3) Short range (SR) is defined as airplanes
with an average flight time of less than 1.5
flight hours per flight cycle.
(4) Long range (LR) is defined as airplanes
with an average flight time equal to or higher
than 1.5 flight hours per flight cycle.
(5) For determining the ‘‘short range’’ and
‘‘long range’’ airplanes, the average flight
time is the total accumulated flight hours,
counted from take-off to touch-down, divided
by the total accumulated flight cycles at the
effective date of this AD.
(h) Inspection and Modification
Not before exceeding the applicable lower
thresholds as specified in table 1 to
paragraph (h) of this AD, and within the
compliance times specified in paragraphs
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as
applicable: Accomplish a detailed visual
inspection for damage (including cracking) of
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the upper wing skin and top stringer joints
at rib 18 on both wings, do all applicable
corrective actions, and do the applicable
modification, including related investigative
and corrective actions, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–57–6118, Revision 01,
dated January 31, 2017, except as required by
paragraph (i) of this AD. Do all applicable
modifications, related investigative actions,
and corrective actions before further flight.
(1) For Group 1, LR airplanes: Inspect at
the time specified in paragraph (h)(1)(i) or
(h)(1)(ii) of this AD, whichever occurs later.
(i) Before exceeding 32,500 flight cycles or
70,300 flight hours, whichever occurs first
since first flight of the airplane.
(ii) Within 700 flight cycles, 1,500 flight
hours, or 12 months, whichever occurs first
after the effective date of this AD.
(2) For Group 1, SR airplanes: Inspect at
the time specified in paragraphs (h)(2)(i) or
(h)(2)(ii) of this AD, whichever occurs later.
(i) Before exceeding 35,100 flight cycles or
52,600 flight hours, whichever occurs first
since the first flight of the airplane.
(ii) Within 700 flight cycles or 1,000 flight
hours, or 12 months, whichever occurs first
after the effective date of this AD.
(3) For Group 2, LR airplanes: Inspect
before exceeding 35,000 flight cycles or
75,700 flight hours, whichever occurs first
since the first flight of the airplane.
(4) For Group 2, SR airplanes: Inspect
before exceeding 37,800 flight cycles or
56,700 flight hours, whichever occurs first
since the first flight of the airplane.
TABLE 1 TO PARAGRAPH (h) OF THIS
AD—COMPLIANCE TIME LOWER
THRESHOLDS
Compliance time flight cycles
(FC) or flight hours (FH),
whichever occurs first since
first flight of the airplane
Applicable
airplanes
Group 1, LR
Group 1, SR
Group 2, LR
Group 2, SR
Not before exceeding
66,700 FH.
Not before exceeding
43,000 FH.
Not before exceeding
61,700 FH.
Not before exceeding
51,600 FH.
30,900 FC or
28,700 FC or
28,600 FC or
34,400 FC or
(i) Service Information Exception
Where Airbus Service Bulletin A300–57–
6118, Revision 01, dated January 31, 2017,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
accordance with the procedures specified in
paragraph (k)(2) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (h) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A300–57–6118, dated June 30, 2015.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
(ii) Reserved.
(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 account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(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.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0023, dated February 10, 2017, 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–2017–0710.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–2125; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
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Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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 Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (i) of this AD, 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.
AGENCY:
(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 A300–57–6118,
Revision 01, dated January 31, 2017.
VerDate Sep<11>2014
15:48 Nov 14, 2017
Jkt 244001
Issued in Renton, Washington, on
November 3, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–24501 Filed 11–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0715; Product
Identifier 2017–NM–073–AD; Amendment
39–19096; AD 2017–23–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by an
evaluation by the design approval
holder (DAH) indicating that the
fuselage crown skin panels are subject
to widespread fatigue damage (WFD).
This AD requires repetitive inspections,
replacement, and applicable oncondition actions for certain fuselage
crown skin panels. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective December
20, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 20, 2017.
ADDRESSES: For service information
identified in this final rule, contact
SUMMARY:
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52835
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0715.
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–2017–
0715; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 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:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los
Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: Jennifer.Tsakoumakis@
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 certain The Boeing Company
Model 737–200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
August 10, 2017 (82 FR 37366). The
NPRM was prompted by an evaluation
by the DAH indicating that the fuselage
crown skin panels are subject to WFD.
The NPRM proposed to require
repetitive inspections, replacement, and
applicable on-condition actions for
certain fuselage crown skin panels.
We are issuing this AD to detect and
correct cracking in the fuselage crown
skin panels. Multiple adjacent cracks in
the fuselage crown skin could link up
and lead to decompression or loss of
structural integrity of the airplane.
E:\FR\FM\15NOR1.SGM
15NOR1
]]>Agencies
[Federal Register Volume 82, Number 219 (Wednesday, November 15, 2017)]
[Rules and Regulations]
[Pages 52832-52835]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-24501]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0710; Product Identifier 2017-NM-019-AD; Amendment
39-19098; AD 2017-23-04]
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 certain
Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620,
and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model
A300 F4-605R airplanes. This AD was prompted by a determination that
the top stringer joints at rib 18 are an area of uniform stress
distribution, which indicates that cracks may develop in adjacent
stringers at the same time. This AD requires an inspection of the upper
wing skin and top stringer joints, and modification of the stringer
joint couplings if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective December 20, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 20,
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 account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0710.
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-2017-
0710; 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 Section, Transport Standards Branch, 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 certain Airbus Model A300
B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622
airplanes;
[[Page 52833]]
Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R
airplanes. The NPRM published in the Federal Register on July 27, 2017
(82 FR 34885) (``the NPRM''). The NPRM was prompted by a determination
that the top stringer joints at rib 18 are an area of uniform stress
distribution, which indicates that cracks may develop in adjacent
stringers at the same time. The NPRM proposed to require an inspection
of the upper wing skin and top stringer joints, and modification of the
stringer joint couplings if necessary. We are issuing this AD to detect
and correct damage (including cracking) at the stringer joints, which
could reduce the structural integrity of the wing.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0023, dated February 10, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A300 B4-600R
series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes;
Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R
airplanes. The MCAI states:
In response to the FAA Part 26 rule change concerning Widespread
Fatigue Damage (WFD), all wing structural items of the A300-600
design deemed potentially susceptible to WFD were assessed. The top
stringer joints at Rib 18 were highlighted as an area of uniform
stress distribution, indicating that cracks may develop in adjacent
stringers at the same time which is known as Multi Element Damage
(MED). Each affected stringer joint consists of three main load
transferring parts: An overlapping flange, two straps attached
through the stringer web and a strap on the top flange. All the
components of the joint are attached with fasteners. The fastener
holes were the subject of a MED WFD analysis, which showed that
cracking could occur from a number of the holes in the joint on
stringers 11, 12, 13, 14, 15, 16, 17, and 18.
This condition, if not detected and corrected, could reduce the
structural integrity of the wing.
Prompted by the conclusion of the WFD analysis, Airbus issued
Service Bulletin (SB) A300-57-6118 to provide modification
instructions. The modification will both re-life via oversizing and
inspect via non-destructive test a defined number of stringer joint
fastener holes at Rib 18. This modification will delay the onset of
cracking at the stringer joint, providing it is completed at the
specified time and will delay the requirement for subsequent
inspection.
For the reasons described above, this [EASA] AD requires a
detailed visual inspection (DVI) [for damage, including cracking] of
the upper wing skin and the top stringer joints at Rib 18, [and
corrective action if necessary] and modification of the stringer
joint couplings at Rib 18, on both wings [as applicable].
The modification includes a related investigative action, i.e., a
special detailed (roto-probe) inspection for damage, including
cracking, of the fastener holes in the upper wing skin, and corrective
action if necessary. Corrective actions include repairing any damage.
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-2017-
0710.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Update the Costs of Compliance
FedEx supported the intent of the NPRM, but requested that we
update the parts cost in the Costs of Compliance section of the
proposed AD to reflect the cost of two parts kits. FedEx noted that the
proposed AD listed the parts cost for only one kit. FedEx pointed out
that operators may need to modify both wings and could therefore need
two parts kits per airplane.
We agree with the commenter's request. We have revised the Costs of
Compliance section of this final rule to reflect two parts kits, each
costing $4,770.
Request To Fix a Typographical Error
Airbus requested that we correct a reference to ``Airbus Model A300
C4-605 Variant F'' airplanes in paragraph (g)(2) of the proposed AD.
The correct model name is ``A300 C4-605R Variant F'' airplanes.
We agree with the commenter's request. We have corrected the
typographical error in this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-57-6118, Revision 01, dated
January 31, 2017. This service information describes procedures for an
inspection of the upper wing skin and top stringer joints at rib 18,
and modification of the stringer joint couplings. 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 65 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection and modification....... 37 work-hours x $85 per Up to $9,540................ Up to $12,685............... Up to $824,525.
hour = $3,145.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that will allow us to provide
cost estimates for certain 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.
[[Page 52834]]
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-23-04 Airbus: Amendment 39-19098; Docket No. FAA-2017-0710;
Product Identifier 2017-NM-019-AD.
(a) Effective Date
This AD is effective December 20, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4-605R, B4-622R, B4-603,
C4-605R Variant F, B4-620, B4-622, and F4-605R airplanes,
certificated in any category, all serial numbers except Model A300
F4-605R airplanes that have embodied Airbus modification 12699 in
production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a determination that the top stringer
joints at rib 18 are an area of uniform stress distribution, which
indicates that cracks may develop in adjacent stringers at the same
time. We are issuing this AD to detect and correct damage (including
cracking) at the stringer joints, which could reduce the structural
integrity of the wing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purposes of this AD, the definitions in paragraphs
(g)(1) through (g)(5) of this AD apply.
(1) Group 1 airplanes are defined as Airbus Model A300 B4-603,
B4-605R, B4-620, B4-622, and B4-622R airplanes.
(2) Group 2 airplanes are defined as Airbus Model A300 C4-605R
Variant F and F4-605R (if in pre-modification 12699 configuration)
airplanes.
(3) Short range (SR) is defined as airplanes with an average
flight time of less than 1.5 flight hours per flight cycle.
(4) Long range (LR) is defined as airplanes with an average
flight time equal to or higher than 1.5 flight hours per flight
cycle.
(5) For determining the ``short range'' and ``long range''
airplanes, the average flight time is the total accumulated flight
hours, counted from take-off to touch-down, divided by the total
accumulated flight cycles at the effective date of this AD.
(h) Inspection and Modification
Not before exceeding the applicable lower thresholds as
specified in table 1 to paragraph (h) of this AD, and within the
compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and
(h)(4) of this AD, as applicable: Accomplish a detailed visual
inspection for damage (including cracking) of the upper wing skin
and top stringer joints at rib 18 on both wings, do all applicable
corrective actions, and do the applicable modification, including
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6118,
Revision 01, dated January 31, 2017, except as required by paragraph
(i) of this AD. Do all applicable modifications, related
investigative actions, and corrective actions before further flight.
(1) For Group 1, LR airplanes: Inspect at the time specified in
paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs
later.
(i) Before exceeding 32,500 flight cycles or 70,300 flight
hours, whichever occurs first since first flight of the airplane.
(ii) Within 700 flight cycles, 1,500 flight hours, or 12 months,
whichever occurs first after the effective date of this AD.
(2) For Group 1, SR airplanes: Inspect at the time specified in
paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs
later.
(i) Before exceeding 35,100 flight cycles or 52,600 flight
hours, whichever occurs first since the first flight of the
airplane.
(ii) Within 700 flight cycles or 1,000 flight hours, or 12
months, whichever occurs first after the effective date of this AD.
(3) For Group 2, LR airplanes: Inspect before exceeding 35,000
flight cycles or 75,700 flight hours, whichever occurs first since
the first flight of the airplane.
(4) For Group 2, SR airplanes: Inspect before exceeding 37,800
flight cycles or 56,700 flight hours, whichever occurs first since
the first flight of the airplane.
Table 1 to Paragraph (h) of This AD--Compliance Time Lower Thresholds
------------------------------------------------------------------------
Compliance time flight cycles (FC)
or flight hours (FH), whichever
Applicable airplanes occurs first since first flight of
the airplane
------------------------------------------------------------------------
Group 1, LR....................... Not before exceeding 30,900 FC or
66,700 FH.
Group 1, SR....................... Not before exceeding 28,700 FC or
43,000 FH.
Group 2, LR....................... Not before exceeding 28,600 FC or
61,700 FH.
Group 2, SR....................... Not before exceeding 34,400 FC or
51,600 FH.
------------------------------------------------------------------------
(i) Service Information Exception
Where Airbus Service Bulletin A300-57-6118, Revision 01, dated
January 31, 2017, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (k)(2) of this
AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(h) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A300-57-6118, dated
June 30, 2015.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
[[Page 52835]]
Section, Transport Standards Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
International Section, send it to the attention of the person
identified in paragraph (l)(2) of this AD. 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
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus's EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (i) of this AD, 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
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0023, dated February 10, 2017, 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-2017-0710.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-2125; fax 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(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 A300-57-6118, Revision 01, dated
January 31, 2017.
(ii) Reserved.
(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 account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(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 November 3, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-24501 Filed 11-14-17; 8:45 am]
BILLING CODE 4910-13-P
