Airworthiness Directives; Piper Aircraft, Inc. Airplanes, 48-50 [2016-30716]
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48
Proposed Rules
Federal Register
Vol. 82, No. 1
Tuesday, January 3, 2017
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2016–9550; Directorate
Identifier 2016–CE–026–AD]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, 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
Piper Aircraft, Inc. Models PA–31, PA–
31–300, PA–31–325, and PA–31–350
airplanes. This proposed AD was
prompted by fatigue cracking in the
fuselage station (FS) 332.00 bulkhead
common to the horizontal stabilizer
front spar attachment. This proposed
AD would require repetitive inspections
to detect cracks in the bulkhead and any
necessary repairs. This proposed AD
also provides an optional modification
if no cracks are found that will greatly
reduce the likelihood of the specified
cracks. We are issuing this proposed AD
to correct the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by February 17, 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 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.
sradovich on DSK3GMQ082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
22:13 Dec 30, 2016
Jkt 241001
For service information identified in
this NPRM, contact Piper Aircraft, Inc.,
Customer Service, 2926 Piper Drive,
Vero Beach, Florida 32960; telephone:
(877) 879–0275; fax: none; email:
customer.service@piper.com; Internet:
www.piper.com. You may view this
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9550; 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:
Gregory ‘‘Keith’’ Noles, Aerospace
Engineer, FAA, Atlanta Aircraft
Certification Office, 1701 Columbia
Avenue, College Park, Georgia 30337;
phone: (404) 474–5551; fax: (404) 474–
5606; email: gregory.noles@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–
2016–9550; Directorate Identifier 2016–
CE–026–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
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
substantive verbal contact we receive
about this proposed AD.
Discussion
We received reports of fatigue
cracking in the FS 332.00 bulkhead
common to the horizontal stabilizer
front spar attachment on Piper Aircraft,
Inc. PA–31 airplanes. Cracks in the
bulkhead could compromise the
structural component’s capability to
carry flight loads, increasing the
potential to overload and fail adjacent
structure. This proposed AD also
provides an optional modification if no
cracks are found that will greatly reduce
the likelihood of the specified cracks.
We are proposing this AD to detect and
repair cracks in the bulkhead that could
lead to structural failure and result in
loss of control.
Related Service Information Under
1 CFR Part 51
We reviewed Piper Aircraft, Inc.
Service Bulletin No. 1289A, dated
October 26, 2016. The service
information describes procedures for the
repetitive inspections, necessary repairs,
and the optional modification of the
bulkhead. 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 these same
type designs.
Proposed AD Requirements
This proposed AD would require
repetitive inspections to detect cracks in
the bulkhead and any necessary repairs.
This proposed AD also provides an
optional modification if no cracks are
found that will greatly reduce the
likelihood of the specified cracks. We
are proposing this AD to detect and
repair cracks in the bulkhead, that could
lead to structural failure and result in
loss of control.
Costs of Compliance
We estimate that this proposed AD
affects 955 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\03JAP1.SGM
03JAP1
49
Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Proposed Rules
ESTIMATED COSTS
Action
Cost per
product
Labor cost
Inspect for cracks in the bulkhead
Parts cost
1 work-hour × $85 per hour = $85
Not Applicable ................................
We estimate the following costs to do
any necessary repairs/replacements that
would be required based on the results
of the proposed inspection. We have no
way of determining the number of
$85
Cost on U.S.
operators
$81,175
aircraft that might need these repairs/
replacements:
ON-CONDITION COSTS
Action
Labor cost
Repair/Modification ..........................
26 work-hours × $85 per hour = $2,210 ...................................................
sradovich on DSK3GMQ082PROD with PROPOSALS
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
VerDate Sep<11>2014
22:13 Dec 30, 2016
Jkt 241001
Parts cost
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
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):
■
Piper Aircraft, Inc.: Docket No. FAA–2016–
9550; Directorate Identifier 2016–CE–
026–AD.
(a) Comments Due Date
We must receive comments by February
17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Piper Aircraft, Inc.
Navajo Models PA–31, PA–31–300, and PA–
31–325, serial numbers 31–2 through 31–900,
and 31–7300901 through 31–8312019; and
Chieftain/T–1020 Models PA–31–350, serial
numbers 31–5001 through 31–5004, and 31–
7305005 through 31–8553002, certificated in
any category.
Note 1 to paragraph (c) of this AD: The
Model PA–31 may also be identified as a PA–
31–310 even though the PA–31–310 is not a
model recognized by the Federal Aviation
Administration (FAA) on the type certificate
data sheet.
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
$296
Cost per
product
$2,506
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 5312: Fuselage—Main Bulkhead.
(e) Unsafe Condition
This AD was prompted by fatigue cracking
in the fuselage station (FS) 332.00 bulkhead
common to the horizontal stabilizer front
spar attachment. We are proposing repetitive
inspections to detect cracks in the bulkhead
and any necessary repairs. This proposed AD
also provides an optional modification if no
cracks are found that will greatly reduce the
likelihood of the specified cracks. Cracks in
the bulkhead could compromise the
structural components capability to carry
flight loads, increasing the potential to
overload and fail adjacent structure and lead
to loss of control.
(f) Compliance
Comply with paragraphs (g)(1) through (3)
of this AD within the compliance times
specified, unless already done.
(g) Actions
(1) For airplanes with 3,000 hours time-inservice (TIS) or less as of the effective date
of this AD: Initially within 500 hours TIS
after reaching 3,000 hours TIS and
repetitively thereafter every 200 hours TIS,
inspect the fuselage station (FS) 332.00
bulkhead assembly for cracks following the
instructions in Part I of Piper Aircraft, Inc.
Service Bulletin (SB) No. 1289A, dated
October 26, 2016.
(2) For airplanes with over 3,000 hours TIS
as of the effective date of this AD: Initially
within the next 500 hours TIS after the
effective date of this AD and repetitively
thereafter every 200 hours TIS, inspect the FS
332.00 bulkhead assembly for cracks,
following the instructions in Part I of Piper
Aircraft, Inc. SB No. 1289A, dated October
26, 2016.
(3) If cracks are found during any of the
inspections required in paragraphs (g)(1) or
(2) of this AD, before further flight, repair the
cracks following the modification
instructions in Part II of Piper Aircraft, Inc.
SB No. 1289A, dated October 26, 2016, and
one of the following as applicable:
(i) If the crack does not extend beyond the
inspection/template area of Figure 2 of Piper
E:\FR\FM\03JAP1.SGM
03JAP1
50
Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Proposed Rules
Aircraft, Inc. SB No. 1289A, dated October
26, 2016, and meets the minimum acceptable
distance in Figure 3 and Table 2 of Part II of
Piper Aircraft, Inc. SB No. 1289A, dated
October 26, 2016, then the installation of
Piper Kit 88578–001 Revision B, dated June
23, 2016, is acceptable as a repair and is
considered terminating action for the
repetitive inspection requirement in
paragraphs (g)(1) and (2) of this AD.
(ii) If the crack extends beyond the
inspection/template area of Figure 2 of Piper
Aircraft, Inc. SB No. 1289A, dated October
26, 2016, or does not meet the minimum
acceptable distance in Figure 3 and Table 2
of Part II of Piper Aircraft, Inc. SB No. 1289A,
dated October 26, 2016, then the installation
of Piper Kit 88578–001 Revision B, dated
June 23, 2016, is not an acceptable repair.
You must obtain an alternative method of
compliance (AMOC) for any repair or
modification in this area. You may contact
Piper Aircraft, Inc. for repair instruction
development specific to this condition. For
contact information refer to paragraph (j) of
this AD.
(4) If no cracks are found, you may install
Piper Kit 88578–001 Revision B, dated June
23, 2016, on an uncracked bulkhead
following the Modification instructions in
Part II of Piper Aircraft, Inc. SB No. 1289A,
dated October 26, 2016. Installation of Piper
Kit 88578–001 Revision B, dated June 23,
2016, on an uncracked bulkhead is
considered terminating action for the
repetitive inspection requirement in
paragraphs (g)(1) and (2) of this AD.
(h) Special Flight Permit
A special flight permit is allowed for this
AD per 14 CFR 39.23 with limitations.
Permits are not allowed if cracks are
discovered during any inspection following
Part I of Piper Aircraft, Inc. SB No. 1289A,
dated October 26, 2016. Any cracks found
during any inspection must be repaired
before further flight.
sradovich on DSK3GMQ082PROD with PROPOSALS
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office, 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 (k) of this AD.
(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
(1) For more information about this AD,
contact Gregory ‘‘Keith’’ Noles, Aerospace
Engineer, FAA, Atlanta Aircraft Certification
Office, 1701 Columbia Avenue, College Park,
Georgia 30337; phone: (404) 474–5551; fax:
(404) 474–5606; email: gregory.noles@
faa.gov.
(2) For service information identified in
this AD, contact Piper Aircraft, Inc.,
VerDate Sep<11>2014
22:13 Dec 30, 2016
Jkt 241001
Customer Service, 2926 Piper Drive, Vero
Beach, Florida 32960; telephone: (877) 879–
0275; fax: none; email: customer.service@
piper.com; Internet: www.piper.com. You
may review the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
(816) 329–4148.
Issued in Kansas City, Missouri, on
December 13, 2016.
Robert P. Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–30716 Filed 12–30–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9519; Directorate
Identifier 2016–NM–099–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by in-service
experience and further analysis, which
showed that the galley 5 without kickload retainers, was unable to withstand
the expected loading during several
flight phases or in case of emergency
landing. This proposed AD would
require modification of galley 5 by
adding kick-load retainers. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by February 17, 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 W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
SUMMARY:
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
p.m., Monday through Friday, except
Federal holidays.
• For service information identified
in this NPRM, contact Airbus,
Airworthiness Office–EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425 227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9519; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9519; Directorate Identifier
2016–NM–099–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
E:\FR\FM\03JAP1.SGM
03JAP1
Agencies
[Federal Register Volume 82, Number 1 (Tuesday, January 3, 2017)]
[Proposed Rules]
[Pages 48-50]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30716]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 /
Proposed Rules
[[Page 48]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9550; Directorate Identifier 2016-CE-026-AD]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and
PA-31-350 airplanes. This proposed AD was prompted by fatigue cracking
in the fuselage station (FS) 332.00 bulkhead common to the horizontal
stabilizer front spar attachment. This proposed AD would require
repetitive inspections to detect cracks in the bulkhead and any
necessary repairs. This proposed AD also provides an optional
modification if no cracks are found that will greatly reduce the
likelihood of the specified cracks. We are issuing this proposed AD to
correct the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by February 17,
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 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 Piper
Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach, Florida
32960; telephone: (877) 879-0275; fax: none; email:
customer.service@piper.com; Internet: www.piper.com. You may view this
referenced service information at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9550; 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: Gregory ``Keith'' Noles, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia
Avenue, College Park, Georgia 30337; phone: (404) 474-5551; fax: (404)
474-5606; email: gregory.noles@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-2016-9550;
Directorate Identifier 2016-CE-026-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 received reports of fatigue cracking in the FS 332.00 bulkhead
common to the horizontal stabilizer front spar attachment on Piper
Aircraft, Inc. PA-31 airplanes. Cracks in the bulkhead could compromise
the structural component's capability to carry flight loads, increasing
the potential to overload and fail adjacent structure. This proposed AD
also provides an optional modification if no cracks are found that will
greatly reduce the likelihood of the specified cracks. We are proposing
this AD to detect and repair cracks in the bulkhead that could lead to
structural failure and result in loss of control.
Related Service Information Under 1 CFR Part 51
We reviewed Piper Aircraft, Inc. Service Bulletin No. 1289A, dated
October 26, 2016. The service information describes procedures for the
repetitive inspections, necessary repairs, and the optional
modification of the bulkhead. 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 these same type
designs.
Proposed AD Requirements
This proposed AD would require repetitive inspections to detect
cracks in the bulkhead and any necessary repairs. This proposed AD also
provides an optional modification if no cracks are found that will
greatly reduce the likelihood of the specified cracks. We are proposing
this AD to detect and repair cracks in the bulkhead, that could lead to
structural failure and result in loss of control.
Costs of Compliance
We estimate that this proposed AD affects 955 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 49]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect for cracks in the bulkhead 1 work-hour x $85 per Not Applicable....... $85 $81,175
hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
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 repairs/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair/Modification........................ 26 work-hours x $85 per hour = $296 $2,506
$2,210.
----------------------------------------------------------------------------------------------------------------
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):
Piper Aircraft, Inc.: Docket No. FAA-2016-9550; Directorate
Identifier 2016-CE-026-AD.
(a) Comments Due Date
We must receive comments by February 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Piper Aircraft, Inc. Navajo Models PA-31, PA-
31-300, and PA-31-325, serial numbers 31-2 through 31-900, and 31-
7300901 through 31-8312019; and Chieftain/T-1020 Models PA-31-350,
serial numbers 31-5001 through 31-5004, and 31-7305005 through 31-
8553002, certificated in any category.
Note 1 to paragraph (c) of this AD: The Model PA-31 may also be
identified as a PA-31-310 even though the PA-31-310 is not a model
recognized by the Federal Aviation Administration (FAA) on the type
certificate data sheet.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5312: Fuselage--Main Bulkhead.
(e) Unsafe Condition
This AD was prompted by fatigue cracking in the fuselage station
(FS) 332.00 bulkhead common to the horizontal stabilizer front spar
attachment. We are proposing repetitive inspections to detect cracks
in the bulkhead and any necessary repairs. This proposed AD also
provides an optional modification if no cracks are found that will
greatly reduce the likelihood of the specified cracks. Cracks in the
bulkhead could compromise the structural components capability to
carry flight loads, increasing the potential to overload and fail
adjacent structure and lead to loss of control.
(f) Compliance
Comply with paragraphs (g)(1) through (3) of this AD within the
compliance times specified, unless already done.
(g) Actions
(1) For airplanes with 3,000 hours time-in-service (TIS) or less
as of the effective date of this AD: Initially within 500 hours TIS
after reaching 3,000 hours TIS and repetitively thereafter every 200
hours TIS, inspect the fuselage station (FS) 332.00 bulkhead
assembly for cracks following the instructions in Part I of Piper
Aircraft, Inc. Service Bulletin (SB) No. 1289A, dated October 26,
2016.
(2) For airplanes with over 3,000 hours TIS as of the effective
date of this AD: Initially within the next 500 hours TIS after the
effective date of this AD and repetitively thereafter every 200
hours TIS, inspect the FS 332.00 bulkhead assembly for cracks,
following the instructions in Part I of Piper Aircraft, Inc. SB No.
1289A, dated October 26, 2016.
(3) If cracks are found during any of the inspections required
in paragraphs (g)(1) or (2) of this AD, before further flight,
repair the cracks following the modification instructions in Part II
of Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, and
one of the following as applicable:
(i) If the crack does not extend beyond the inspection/template
area of Figure 2 of Piper
[[Page 50]]
Aircraft, Inc. SB No. 1289A, dated October 26, 2016, and meets the
minimum acceptable distance in Figure 3 and Table 2 of Part II of
Piper Aircraft, Inc. SB No. 1289A, dated October 26, 2016, then the
installation of Piper Kit 88578-001 Revision B, dated June 23, 2016,
is acceptable as a repair and is considered terminating action for
the repetitive inspection requirement in paragraphs (g)(1) and (2)
of this AD.
(ii) If the crack extends beyond the inspection/template area of
Figure 2 of Piper Aircraft, Inc. SB No. 1289A, dated October 26,
2016, or does not meet the minimum acceptable distance in Figure 3
and Table 2 of Part II of Piper Aircraft, Inc. SB No. 1289A, dated
October 26, 2016, then the installation of Piper Kit 88578-001
Revision B, dated June 23, 2016, is not an acceptable repair. You
must obtain an alternative method of compliance (AMOC) for any
repair or modification in this area. You may contact Piper Aircraft,
Inc. for repair instruction development specific to this condition.
For contact information refer to paragraph (j) of this AD.
(4) If no cracks are found, you may install Piper Kit 88578-001
Revision B, dated June 23, 2016, on an uncracked bulkhead following
the Modification instructions in Part II of Piper Aircraft, Inc. SB
No. 1289A, dated October 26, 2016. Installation of Piper Kit 88578-
001 Revision B, dated June 23, 2016, on an uncracked bulkhead is
considered terminating action for the repetitive inspection
requirement in paragraphs (g)(1) and (2) of this AD.
(h) Special Flight Permit
A special flight permit is allowed for this AD per 14 CFR 39.23
with limitations. Permits are not allowed if cracks are discovered
during any inspection following Part I of Piper Aircraft, Inc. SB
No. 1289A, dated October 26, 2016. Any cracks found during any
inspection must be repaired before further flight.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Atlanta Aircraft Certification Office, 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 (k) of this AD.
(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
(1) For more information about this AD, contact Gregory
``Keith'' Noles, Aerospace Engineer, FAA, Atlanta Aircraft
Certification Office, 1701 Columbia Avenue, College Park, Georgia
30337; phone: (404) 474-5551; fax: (404) 474-5606; email:
gregory.noles@faa.gov.
(2) For service information identified in this AD, contact Piper
Aircraft, Inc., Customer Service, 2926 Piper Drive, Vero Beach,
Florida 32960; telephone: (877) 879-0275; fax: none; email:
customer.service@piper.com; Internet: www.piper.com. You may review
the referenced service information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
Issued in Kansas City, Missouri, on December 13, 2016.
Robert P. Busto,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30716 Filed 12-30-16; 8:45 am]
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