Airworthiness Directives; The Boeing Company Airplanes, 28023-28026 [2017-12612]
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
Issue 19, dated March 23, 2012; ‘‘Variation to
Issue 19 of ALI Document (referenced in ALS
Part 2) Damage Tolerant Airworthiness
Limitation Items (DT ALI),’’ variation
reference 0GVLG120018/C0S, dated October
24, 2012; and ‘‘Variation to Issue 19 of ALI
Document (referenced in ALS Part 2) Damage
Tolerant Airworthiness Limitation Items (DT
ALI),’’ 0GVLG130002/C01, dated March 26,
2013; are at the times specified in Airbus
Document AI/SE–M4/95A.0089/97, ‘‘A330
Airworthiness Limitation Items,’’ Issue 19,
dated March 23, 2012; ‘‘Variation to Issue 19
of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation
Items (DT ALI),’’ variation ref.
0GVLG120018/C0S, dated October 24, 2012;
and ‘‘Variation to Issue 19 of ALI Document
(referenced in ALS Part 2) Damage Tolerant
Airworthiness Limitation Items (DT ALI),’’
variation ref. 0GVLG130002/C01, dated
March 26, 2013; or within 3 months after
October 8, 2014 (the effective date of AD
2014–17–06), whichever occurs later.
later. Accomplishing the revision specified in
this paragraph terminates the requirements of
paragraph (g) of this AD and the provision
specified in paragraph (h) of this AD.
(1) Airbus A330 Airworthiness Limitations
Section (ALS) Part 2, Damage Tolerant
Airworthiness Limitation Items (DT-ALI),
Revision 01, issue 02, dated November 30,
2015.
(2) Airbus 330 ALS Part 2, DT-ALI,
Variation 1.1, dated December 15, 2015.
(3) Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2, dated May 27, 2016.
(h) Retained Provision: Optional
Compliance, With a New Terminating
Action
This paragraph restates the provision in
paragraph (j) of AD 2014–17–06, with a new
terminating action. Compliance with tasks
533021–02–01, 533021–02–02, and 533021–
02–03, specified in ‘‘Variation to Issue 19 of
ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation
Items (DT ALI),’’ variation ref.
0GVLG120022/C0S, dated December 21,
2012, may be used as a method of
compliance to tasks 533021–01–01, 533021–
01–02, 533021–01–03 specified in Section
2.2.1 and 2.2.2 of Section 2, ‘‘Airworthiness
Limitations,’’ of Airbus Document AI/SE M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012. Accomplishing the revision required
by paragraph (j) of this AD terminates the
provision specified in this paragraph.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to the
attention of the person identified in
paragraph (m)(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: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
(i) Retained Requirement: No Alternative
Intervals or Limits, With a New Exception
This paragraph restates the requirements of
paragraph (k) of AD 2014–17–06, with a new
exception. Except as provided by paragraph
(h) of this AD and as required by paragraph
(j) of this AD, after the maintenance or
inspection program, as applicable, has been
revised as required by paragraph (g) of this
AD, no alternative actions (e.g., inspections)
or intervals may be used unless the actions
or intervals are approved as an alternative
method of compliance (AMOC) under the
provisions of paragraph (l)(1) of this AD.
(j) New Requirement: Maintenance or
Inspection Program Revision
Within 3 months after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, by
incorporating the service information
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD. The initial compliance times for
the actions specified in the service
information referenced in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD are the times
specified in the applicable service
information, or within 3 months after the
effective date of this AD, whichever occurs
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17:28 Jun 19, 2017
Jkt 241001
(k) New Requirement: No Alternative
Actions or Intervals
After the maintenance or inspection
program, as applicable, has been revised, as
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an AMOC in
accordance with the procedures specified in
paragraph (l)(1) of this AD.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0152, dated
July 27, 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–
2017–0561.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
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28023
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on June 9,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12614 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0559; Directorate
Identifier 2017–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
airplanes. This proposed AD was
prompted by a report of damage found
at the lower trailing edge panels of the
left wing and a broken fuse pin of the
landing gear beam end fitting. This
proposed AD would require repetitive
replacement or inspection of certain
fuse pins, and applicable on-condition
actions. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 4, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
DATES:
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28024
Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact 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 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–2017–
0559.
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–
0559; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0559; Directorate Identifier
2017–NM–013–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received a report indicating
damage to the lower trailing edge panels
of the left wing of a 747–400 airplane.
Further inspection revealed that the left
wing fuse pin of the landing gear beam
end fitting had broken into two pieces.
The airplane had 17,879 total flight
cycles and 102,793 total flight hours at
the time of the failure. Boeing has done
an analysis and determined that the fuse
pin broke as a result of fatigue. Fatigue
cracking of the fuse pin, if not corrected,
could result in a broken fuse pin. A
broken fuse pin will not support the
wing landing gear beam, causing
damage to the surrounding structure,
including flight control cables and
hydraulic systems, which could result
in loss of controllability of the airplane.
Related Service Information Under
1 CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–57A2360, dated January
20, 2017. The service information
describes procedures for repetitive
replacement or inspection of certain
fuse pins, and applicable on-condition
actions. 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.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Alert Service
Bulletin 747–57A2360, dated January
20, 2017, described previously, except
for any differences between this
proposed AD and the service
information that are identified in the
regulatory text of this proposed AD.
Although the crack reports that
prompted this proposed AD were found
only on the left wing, this proposed AD
would require actions on both wings.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0559.
Costs of Compliance
We estimate that this proposed AD
affects 158 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Fuse pin replacement 1 ...........................
46 work-hours × $85 per hour = $3,910
per replacement cycle.
$15,150
Magnetic particle inspection 1 ..................
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Action
48 work-hours × $85 per hour = $4,080
per inspection cycle.
10 work-hours × $85 per hour = $850
per inspection cycle.
0
Surface inspection 1 .................................
1 Operators
$19,060 per replacement cycle.
Up to $3,011,480
per replacement
cycle.
Up to $644,640 per
inspection cycle.
Up to $134,300 per
inspection cycle.
0
$4,080 per inspection cycle.
$850 per inspection
cycle.
may choose which action they want to use.
We estimate the following costs to do
any necessary replacements that would
VerDate Sep<11>2014
Cost on U.S.
operators
Parts cost
17:28 Jun 19, 2017
Jkt 241001
be required based on the results of the
proposed inspection. We have no way of
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determining the number of aircraft that
might need these replacements:
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
28025
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Fuse pin replacement .........................................
46 work-hours × $85 per hour = $3,910 ..........
Up to $15,150 .............
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
VerDate Sep<11>2014
17:28 Jun 19, 2017
Jkt 241001
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2017–0559; Directorate Identifier 2017–
NM–013–AD.
(a) Comments Due Date
We must receive comments by August 4,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, and 747SP airplanes, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of
damage found at the lower trailing edge
panels of the left wing and a broken fuse pin
of the landing gear beam end fitting. We are
issuing this AD to detect and correct cracking
in the fuse pin of the wing landing gear beam
end fitting. A broken fuse pin will not
support the wing landing gear beam, causing
damage to the surrounding structure,
including flight control cables and hydraulic
systems, which could result in loss of
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions Required for Compliance
Except as required by paragraph (h) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–57A2360, dated
January 20, 2017, do all applicable actions
identified as required for compliance (‘‘RC’’)
in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2360, dated January
20, 2017.
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Cost per
product
Up to $19,060.
(h) Exception to the Service Information
Where Boeing Alert Service Bulletin 747–
57A2360, dated January 20, 2017, specifies a
compliance time ‘‘after the original issue date
of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6432; fax: 425–
917–6590; email: bill.ashforth@faa.gov.
(2) For service information identified in
this AD, contact 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 Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on June 9,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12612 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0608; Directorate
Identifier 2017–CE–017–AD]
RIN 2120–AA64
Airworthiness Directives; Textron
Aviation Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Textron Aviation Inc. Model 390
airplanes (type certificate previously
held by Beechcraft Corporation). This
proposed AD was prompted by reports
of hydraulic fluid loss from the engine
driven pumps (EDPs) on three different
airplanes. This proposed AD would
require an inspection to determine if an
affected EDP is installed with
replacement as necessary. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by August 4, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:28 Jun 19, 2017
Jkt 241001
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Textron Aviation
Inc., Textron Aviation Customer
Service, P.O. Box 7706, Wichita, Kansas
67277; telephone: (316) 517–5800;
email: premier@txtav.com; Internet:
www.txtavsupport.com. You may view
this 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.
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–
0608; 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 NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Paul
C. DeVore, Aerospace Engineer, Wichita
Aircraft Certification Office, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4142; fax: (316) 946–4107, email:
paul.devore@faa.gov or Wichita-COS@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–0608; Directorate Identifier 2017–
CE–017–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
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Sfmt 4702
Discussion
We received reports of hydraulic fluid
loss from the engine driven pumps
(EDPs) on three different Textron
Aviation Inc. Model 390 airplanes. In
one incident, the airplane exited the
runway at a high speed, resulting in
extensive damage to the airplane. One
manufacturing lot of EDPs has excessive
pitting in the aluminum port caps that
could cause multiple-origin fatigue
cracking of the port caps. Flammable
hydraulic fluid could leak into the
engine compartment, and the leaking
could also cause loss of all normal
hydraulic functions, including normal
anti-skid braking, ground spoilers,
speedbrakes, and normal landing gear
extension. This condition, if not
corrected, could result in loss of normal
hydraulic functions, which could lead
to a high-speed runway overrun and/or
an in-flight fire.
Related Service Information Under 1
CFR Part 51
We reviewed Parker Service Bulletin
66179–29–486, dated August 4, 2016,
which identifies the affected serial
number EDPs. We also reviewed
Beechcraft Mandatory Service Bulletin
SB 29–4161, dated November 18, 2016,
which describes procedures for
determining if an affected serial number
EDP is installed and procedures for
replacing the EDP if necessary. 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.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information.’’
Differences Between This Proposed AD
and the Service Information
The service information specifies a
compliance time of 200 hours time-inservice (TIS) or 12 months, whichever
occurs first. This proposed AD would
require a compliance of 100 hours TIS
to reduce the possibility of another
incident due to a cracked EDP. We
removed the 12 month calendar time
from the compliance time because we
E:\FR\FM\20JNP1.SGM
20JNP1
]]>Agencies
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28023-28026]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12612]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0559; Directorate Identifier 2017-NM-013-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and
747SP airplanes. This proposed AD was prompted by a report of damage
found at the lower trailing edge panels of the left wing and a broken
fuse pin of the landing gear beam end fitting. This proposed AD would
require repetitive replacement or inspection of certain fuse pins, and
applicable on-condition actions. We are proposing this AD to address
the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 4, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room
[[Page 28024]]
W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact 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 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-2017-0559.
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-
0559; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0559;
Directorate Identifier 2017-NM-013-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received a report indicating damage to the lower trailing
edge panels of the left wing of a 747-400 airplane. Further inspection
revealed that the left wing fuse pin of the landing gear beam end
fitting had broken into two pieces. The airplane had 17,879 total
flight cycles and 102,793 total flight hours at the time of the
failure. Boeing has done an analysis and determined that the fuse pin
broke as a result of fatigue. Fatigue cracking of the fuse pin, if not
corrected, could result in a broken fuse pin. A broken fuse pin will
not support the wing landing gear beam, causing damage to the
surrounding structure, including flight control cables and hydraulic
systems, which could result in loss of controllability of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-57A2360, dated
January 20, 2017. The service information describes procedures for
repetitive replacement or inspection of certain fuse pins, and
applicable on-condition actions. 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.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishment of the actions
identified as ``RC'' (required for compliance) in the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2360, dated
January 20, 2017, described previously, except for any differences
between this proposed AD and the service information that are
identified in the regulatory text of this proposed AD. Although the
crack reports that prompted this proposed AD were found only on the
left wing, this proposed AD would require actions on both wings.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0559.
Costs of Compliance
We estimate that this proposed AD affects 158 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement \1\..... 46 work-hours x $85 $15,150 $19,060 per Up to $3,011,480 per
per hour = $3,910 replacement replacement cycle.
per replacement cycle.
cycle.
Magnetic particle inspection 48 work-hours x $85 0 $4,080 per Up to $644,640 per
\1\. per hour = $4,080 inspection inspection cycle.
per inspection cycle. cycle.
Surface inspection \1\....... 10 work-hours x $85 0 $850 per Up to $134,300 per
per hour = $850 per inspection inspection cycle.
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Operators may choose which action they want to use.
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
[[Page 28025]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement............. 46 work-hours x $85 per Up to $15,150....... Up to $19,060.
hour = $3,910.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2017-0559; Directorate Identifier
2017-NM-013-AD.
(a) Comments Due Date
We must receive comments by August 4, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of damage found at the lower
trailing edge panels of the left wing and a broken fuse pin of the
landing gear beam end fitting. We are issuing this AD to detect and
correct cracking in the fuse pin of the wing landing gear beam end
fitting. A broken fuse pin will not support the wing landing gear
beam, causing damage to the surrounding structure, including flight
control cables and hydraulic systems, which could result in loss of
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions Required for Compliance
Except as required by paragraph (h) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-57A2360, dated January 20, 2017,
do all applicable actions identified as required for compliance
(``RC'') in, and in accordance with, the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2360, dated January 20,
2017.
(h) Exception to the Service Information
Where Boeing Alert Service Bulletin 747-57A2360, dated January
20, 2017, specifies a compliance time ``after the original issue
date of this service bulletin,'' this AD requires compliance within
the specified compliance time after the effective date of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
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 manager of the
ACO, send it to the attention of the person identified in paragraph
(j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(i)(4)(i) and (i)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled 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 RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(j) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer,
[[Page 28026]]
Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590;
email: bill.ashforth@faa.gov.
(2) For service information identified in this AD, contact
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 Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on June 9, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12612 Filed 6-19-17; 8:45 am]
BILLING CODE 4910-13-P
