Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Helicopters, 54922-54925 [2014-21919]
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Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules
(g) Determine Date of Installation or Date of
Last Replacement of the Lateral Fuselage Tie
Rods and Attaching Nuts
Within the next 30 days after the effective
date of this AD, review the aircraft records
to determine the date of installation or date
of last replacement of the lateral fuselage tie
rods and attaching nuts.
rmajette on DSK2TPTVN1PROD with PROPOSALS
(h) Replace the Lateral Fuselage Tie Rod and
Attaching Nuts
Initially replace the lateral fuselage tie rod
and attaching nuts at whichever of the
compliance times specified in paragraph
(h)(1) or paragraph (h)(2) of this AD that
applies. Repetitively thereafter replace the
lateral fuselage tie rod and attaching nuts
every 2,000 hours TIS or 18 years, whichever
occurs first. Do the replacement following the
procedures in paragraph 2.C. of the
Accomplishment Instructions and the table
on Figure 1 in British Aerospace Military
Aircraft and Aerostructures BAe Aircraft
Bulletin for De Havilland Moth Aircraft,
Document Type and Ref No Technical News
Sheet CT (Moth) No 29, Issue 3, dated March
1, 1999.
(1) If the date of lateral fuselage tie rod
installation or date of last replacement is
known: Do the initial replacement at
whichever of the following compliance times
in paragraph (h)(1)(i) or paragraph (h)(1)(ii) of
this AD that occurs later:
(i) Upon accumulating 2,000 hours TIS on
the lateral fuselage tie rod or upon reaching
18 years from the last lateral fuselage tie rod
replacement, whichever occurs first; or
(ii) Within the next 6 months after the
effective date of this AD or within the next
100 hours TIS after the effective date of this
AD, whichever occurs first.
(2) If the date of lateral fuselage tie rod
installation or date of last replacement is not
known: Do the initial replacement within the
next 6 months after the effective date of this
AD or within the next 100 hours TIS after the
effective date of this AD, whichever occurs
first.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager of the Fort Worth
Airplane Certification Office (ACO), the
Manager of the Los Angeles Aircraft
Certification Office (ACO), and the Manager
of the Standards Office, FAA, have the
authority to approve AMOCs for their
respective products covered by 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 applicable FAA office,
send it to the attention of the person
identified in paragraphs (j)(1), (j)(2), or (j)(3),
as applicable.
(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 for
airplanes covered under Type Certificate
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Data Sheet (TCDS) A5PC (Model de
Havilland DH 82A airplanes built in
Australia), contact Andrew McAnaul,
Aerospace Engineer, FAA, Fort Worth ACO,
ASW–150 (c/o San Antonio MIDO), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308–3365; fax:
(210) 308–3370; email: andrew.mcanaul@
faa.gov.
(2) For more information about this AD for
airplanes covered under TCDS A8EU (Model
de Havilland DH 82A airplanes built in the
United Kingdom), contact Fred Guerin,
Aerospace Engineer, FAA, Los Angeles ACO,
3960 Paramount Blvd., Suite 100, Lakewood,
California 90712; phone (562) 627–5232; fax:
(562) 627–5210; email: fred.guerin@faa.gov.
(3) For more information about this AD for
airplanes covered under TCDS 2–439 (Model
de Havilland DH 83 airplanes built in the
United Kingdom), contact Karl Schletzbaum,
Aerospace Engineer, FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329–
4123; fax: (816) 329–4090; email:
karl.schletzbaum@faa.gov.
(4) For British Aerospace Military Aircraft
and Aerostructures BAe Aircraft Bulletin for
De Havilland Moth Aircraft, Technical New
Sheet CT (Moth) No 29, Issue 3, dated March
1, 1999, service information identified in this
AD, contact:
(i) For de Havilland DH 82A airplanes: de
Havilland Support Ltd, Building 213,
Duxford Airfield, Cambridge, United
Kingdom CB22 4QR, telephone: +44 (0) 1223
830090; fax: +44 (0) 1223 83008; email: info@
dhsupport.com; Internet: https://
www.dhsupport.com/moth.php.
(ii) For de Havilland DH 83 airplanes: Air
Stratus Ltd., Oaksey Park Airfield, Oaksey,
Malmesbury, Wiltshite, United Kingdom SN
16 9SD, telephone: +44 (0) 1666 575111; no
known Internet address.
(5) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64016. For
information on the availability of this
material at the FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on
September 8, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2014–21916 Filed 9–12–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0643; Directorate
Identifier 2013–SW–059–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (Bell)
Helicopters
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
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Fmt 4702
Sfmt 4702
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede
airworthiness directive (AD) 2001–13–
51 for Bell Model 206L–4, 407, and 427
helicopters. AD 2001–13–51 currently
requires inspecting certain driveshafts
for a crack, a loose bolt or nut, or red
powder residue and replacing a
driveshaft if there is a crack, a loose bolt
or nut, or red powder residue. AD 2001–
13–51 also requires notifying the FAA
within 10 days if a crack is found in the
driveshaft. Since we issued AD 2001–
13–51, the Model 429 helicopter has
been certificated, and the reporting
requirement is no longer necessary. This
proposed AD would retain the
inspection requirement of AD 2001–13–
51, expand the applicability to include
the Model 429 helicopter, and remove
the reporting requirement. These
proposed actions are intended to
prevent failure of a driveshaft, loss of
drive to the main rotor system, and a
subsequent emergency landing.
DATES: We must receive comments on
this proposed AD by November 14,
2014.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
foreign authority’s AD, the economic
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 service information identified in
this proposed AD, contact Bell
Helicopter Textron Canada Limited,
12,800 Rue de l’Avenir, Mirabel, Quebec
J7J1R4; telephone (450) 437–2862 or
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Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules
(800) 363–8023; fax (450) 433–0272; or
at https://www.bellcustomer.com/files/.
You may review service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
FOR FURTHER INFORMATION CONTACT:
Matthew Fuller, Aviation Safety
Engineer, Safety Management Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
rmajette on DSK2TPTVN1PROD with PROPOSALS
Discussion
On June 27, 2001, the FAA issued
Emergency AD 2001–13–51, which we
published by issuing a Final rule;
request for comment on September 21,
2001 (66 FR 48535 FR), for Bell Model
206L–4, 407 and 427 helicopters. AD
2001–13–51 requires visually inspecting
driveshaft, part number (P/N) 206–340–
300–105, for a crack, a loose bolt or nut,
or red powder residue and replacing a
driveshaft if there is a crack, a loose bolt
or nut, or red powder residue. AD 2001–
13–51 also requires notifying the FAA
within 10 days if a crack is found in the
driveshaft, and prohibits interchanging
a driveshaft between different models if
the driveshaft has ever been installed on
a Bell Model 407 helicopter. AD 2001–
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13–51 was prompted by a driveshaft
failure on a Bell Model 407 helicopter
that resulted in an engine shutdown and
an emergency landing, as well as three
other incidents of a cracked flex frame
on the forward end of the driveshaft on
other Model 407 helicopters. AD 2001–
13–51 was prompted by AD No. CF–
2001–24, dated June 11, 2001, issued by
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada. TCCA AD No. CF–2001–24
required a one-time visual inspection of
the driveshaft.
Actions Since AD 2001–13–51 Was
Issued
Since we issued AD 2001–13–51 (66
FR 48535, September 21, 2001), the
Model 429 helicopter was certificated,
and TCCA issued Revision 3, dated
September 26, 2013, to AD No. CF–
2001–24. Revision 3 adds Model 429
helicopters to the applicability section
and requires removing any driveshaft,
P/N 206–340–300–105, if it has ever
been installed on a Bell Model 407
helicopter.
This proposed AD would expand the
applicability to include the Bell Model
429 helicopter because the driveshaft,
P/N 206–340–300–105, can also be
installed on the Bell Model 429
helicopter. Also, we have removed the
requirement to notify the FAA if a crack
is found in the driveshaft because we
did not receive any reports of driveshaft
problems. This proposed AD would
retain the one-time inspection, if not
previously accomplished, for a crack, a
loose bolt or nut, and red powder
residue, and if there is a crack, a loose
bolt or nut, or red powder residue,
replacing each unairworthy driveshaft
with an airworthy driveshaft before
further flight. The one-time inspection
is not required for Bell Model 429
helicopters because that model would
have had the inspection done when it
was certificated. Lastly, this proposed
AD would require for all applicable
models, within 1,250 hours time-inservice (TIS), removing from service any
driveshaft, P/N 206–340–300–105, if it
has ever been installed on a Bell Model
407 helicopter.
FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, TCAA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
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54923
develop on other helicopters of the same
type design.
Related Service Information
We reviewed Bell Alert Service
Bulletin (ASB) No. 206L–01–123,
Revision A, dated February 22, 2006, for
Bell Model 206L–4 helicopters and ASB
No. 427–01–04, Revision A, dated
March 31, 2006, for Bell Model 427
helicopters. Both ASBs describe
inspecting the Historical Service Record
of the engine-to-transmission driveshaft,
P/N 206–340–300–105, to determine
whether the driveshaft has ever been
installed on a Bell Model 407 helicopter
and removing the driveshaft if it has
ever been installed on a Model 407
helicopter. We also reviewed Bell ASB
No. 407–01–45, Revision B, dated April
23, 2013, for Bell Model 407 helicopters,
which describes an engine-totransmission driveshaft 1,250-Hour
overhaul. TCCA classified these ASBs as
mandatory and issued AD No. CF–
2002–03R3, dated September 26, 2013,
to ensure the continued airworthiness of
these helicopters.
Proposed AD Requirements
This proposed AD would require:
• Within 50 hours TIS, determining
whether driveshaft, P/N 206–340–300–
105, has ever been installed on a Bell
Model 407 helicopter and making a note
on the component history card or
equivalent record. If a driveshaft has
ever been installed on a Model 407
helicopter:
Æ Within 25 hours TIS, inspecting
each Model 206L–4, 407, and 427
helicopter with an affected driveshaft
installed for a crack, loose bolts or nuts,
and red powder residue. If there is a
crack, a loose bolt or nut, or red powder
residue, replacing the driveshaft with an
airworthy driveshaft before further
flight.
Æ For each helicopter with an affected
driveshaft installed, on or before
accumulating 1,250 hours TIS, replacing
the driveshaft with an airworthy
driveshaft.
This proposed AD would also
prohibit installing driveshaft, P/N 206–
340–300–105, on any helicopter if it has
ever been installed on a Bell Model 407
helicopter.
Differences Between the Proposed AD
and the TCCA AD
The TCCA AD requires following the
compliance time specified in the Bell
ASBs, which allows more time, based
on the hours TIS, for removing the
driveshaft. This proposed AD would
require replacing the driveshaft before
accumulating 1,250 hours TIS. The
proposed AD would also prohibit the
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Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules
use of driveshaft, P/N 206–340–300–
105, on the Model 407 helicopter.
Costs of Compliance
We estimate that this proposed AD
would affect 970 helicopters of U.S.
Registry. We estimate that operators
may incur the following costs in order
to comply with this proposed AD. Labor
costs are estimated at $85 per workhour. We estimate 0.25 work-hour to
determine whether the driveshaft has
ever been installed on a Bell Model 407
helicopter for a total cost of $22 per
helicopter or $21,340 for the fleet. If a
driveshaft has been installed on a Model
407 helicopter, we estimate 1 work hour
to inspect the driveshaft for a cost of $85
per helicopter, and 2 work hours and
$39,724 for required parts to replace a
driveshaft for a cost of $39,894 per
helicopter.
rmajette on DSK2TPTVN1PROD 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 proposed
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, 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 to the extent that it justifies
making a regulatory distinction; and
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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.
We prepared an economic evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2001–13–51, Amendment 39–12443 (66
FR 48535, September 21, 2001), and
adding the following new AD:
■
Bell Helicopter Textron Canada (Bell):
Docket No. FAA–2014–0643; Directorate
Identifier 2013–SW–059–AD.
(a) Applicability
This AD applies to Model 206L–4, 407,
427, and 429 helicopters with an engine-totransmission driveshaft assembly
(driveshaft), part number (P/N) 206–340–
300–105, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a driveshaft due to cracking of the
flex frame on the forward end of the
driveshaft. This condition could result in loss
of drive to the main rotor system and a
subsequent emergency forced landing.
(c) Affected ADs
This AD supersedes AD 2001–13–51,
Amendment 39–12443, Docket No. 2001–
SW–29–AD (66 FR 48535, September 21,
2001).
(d) Comments Due Date
We must receive comments by November
14, 2014.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Within 50 hours time-in-service (TIS),
determine whether driveshaft, P/N 206–340–
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(g) Special Flight Permit
Special flight permits are prohibited.
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
300–105, has ever been installed on a Bell
Model 407 helicopter, and record this on the
component history card or equivalent record.
If driveshaft, P/N 206–340–300–105, has ever
been installed on a Bell Model 407
helicopter:
(i) For Bell Model 206L–4, 407, and 427
helicopters, within 25 hours TIS, inspect
each driveshaft for a crack, a loose bolt or
nut, and red powder residue. If there is a
crack, a loose bolt or nut, or red powder
residue, replace the driveshaft with an
airworthy driveshaft before further flight.
(ii) For all affected Bell model helicopters,
on or before accumulating 1,250 hours TIS,
replace each driveshaft with an airworthy
driveshaft.
(2) Do not install driveshaft, P/N 206–340–
300–105, on any helicopter if it has ever been
installed on a Bell Model 407 helicopter.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matthew Fuller,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
(1) Bell Alert Service Bulletin (ASB) No.
206L–01–123, Revision A, dated February 22,
2006; ASB No. 427–01–04, Revision A, dated
March 31, 2006; and ASB No. 407–01–45,
Revision B, dated April 23, 2013, which are
not incorporated by reference, contain
additional information about the subject of
this AD. For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4; telephone (450)
437–2862 or (800) 363–8023; fax (450) 433–
0272; or at https://www.bellcustomer.com/
files/. You may review a copy of the service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
No. CF–2002–03R3, Revision 3, dated
September 26, 2013. You may view the TCCA
AD on the Internet at https://
www.regulations.gov in Docket No. FAA–
2014–0643.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6300 Main Rotor Drive System.
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Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules
Issued in Fort Worth, Texas, on August 22,
2014.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2014–21919 Filed 9–12–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0646; Directorate
Identifier 2013–SW–053–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters, Inc. (Previously
Eurocopter France) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Airbus
Helicopters, Inc. (previously Eurocopter
France) Model AS355E, AS355F,
AS355F1, and AS355F2 helicopters
with a Fueltron flowmeter installed.
This proposed AD would require
removing each flowmeter, replacing the
fuel system hoses, and disabling the
electrical connections for the flowmeter
installation. This proposed AD is
prompted by a report of particle
contamination creating an obstruction
in a flowmeter which resulted in an
uncontrolled flame-out of the engine.
The proposed actions are intended to
prevent obstruction of the fuel supply to
the flowmeter, which could result in
engine flame-out and subsequent loss of
control of the helicopter.
DATES: We must receive comments on
this proposed AD by November 14,
2014.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
rmajette on DSK2TPTVN1PROD with PROPOSALS
ADDRESSES:
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
European Aviation Safety Agency
(EASA) AD, the economic 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 service information identified in
this proposed AD, contact Airbus
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
James Blyn, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
54925
proposal in light of the comments we
receive.
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2013–
0205, dated September 9, 2013, to
correct an unsafe condition for
Eurocopter (now Airbus Helicopters,
Inc.) Model AS355 E, AS355 F, AS355
F1, and AS355 F2 helicopters with
modification 350A070791 (installation
of the Fueltron flowmeter), except
helicopters with modification
355A085801 (removal of the Fueltron
flowmeter). EASA advises that, after
landing, an AS355 helicopter
experienced an uncontrolled flame-out
of the No. 1 engine. Following an
analysis, EASA states that particle
contamination in the fuel had
obstructed the Fueltron flowmeter
because the cross-section areas of the
passages in the flowmeter are smaller
than the mesh in the upstream fuel
pump strainer, allowing particles to
pass through the strainer and into the
flowmeter. EASA further states that the
flowmeter installation is identical on
both engines, and that this condition
could lead to flame-out of both engines
in flight, possibly resulting in reduced
control of the helicopter. EASA AD No.
2013–0205 requires removing the
flowmeter from each engine, modifying
the fuel line system with a new fuel line
part number (P/N) 704A34–416–029 for
the left-hand (LH) engine and P/N
704A34–416–030 for the right-hand
(RH) engine, removing the flowmeter
indicator, and disabling the flowmeter
electrical connections.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other helicopters of the same
type design.
Related Service Information
Eurocopter has issued Alert Service
Bulletin (ASB) No. AS355–28.00.20,
Revision 0, dated June 6, 2013, for
Model AS355 E, AS355 F, AS355 F1,
and AS355 F2 helicopters, which
describes procedures for removing and
disabling the Fueltron flowmeter
installation. The ASB corresponds to
Eurocopter modification 355A085801.
E:\FR\FM\15SEP1.SGM
15SEP1
]]>Agencies
[Federal Register Volume 79, Number 178 (Monday, September 15, 2014)]
[Proposed Rules]
[Pages 54922-54925]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-21919]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0643; Directorate Identifier 2013-SW-059-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada (Bell)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2001-13-
51 for Bell Model 206L-4, 407, and 427 helicopters. AD 2001-13-51
currently requires inspecting certain driveshafts for a crack, a loose
bolt or nut, or red powder residue and replacing a driveshaft if there
is a crack, a loose bolt or nut, or red powder residue. AD 2001-13-51
also requires notifying the FAA within 10 days if a crack is found in
the driveshaft. Since we issued AD 2001-13-51, the Model 429 helicopter
has been certificated, and the reporting requirement is no longer
necessary. This proposed AD would retain the inspection requirement of
AD 2001-13-51, expand the applicability to include the Model 429
helicopter, and remove the reporting requirement. These proposed
actions are intended to prevent failure of a driveshaft, loss of drive
to the main rotor system, and a subsequent emergency landing.
DATES: We must receive comments on this proposed AD by November 14,
2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the foreign
authority's AD, the economic 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 service information identified in this proposed AD, contact
Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir,
Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or
[[Page 54923]]
(800) 363-8023; fax (450) 433-0272; or at https://www.bellcustomer.com/files/. You may review service information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Matthew Fuller, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
On June 27, 2001, the FAA issued Emergency AD 2001-13-51, which we
published by issuing a Final rule; request for comment on September 21,
2001 (66 FR 48535 FR), for Bell Model 206L-4, 407 and 427 helicopters.
AD 2001-13-51 requires visually inspecting driveshaft, part number (P/
N) 206-340-300-105, for a crack, a loose bolt or nut, or red powder
residue and replacing a driveshaft if there is a crack, a loose bolt or
nut, or red powder residue. AD 2001-13-51 also requires notifying the
FAA within 10 days if a crack is found in the driveshaft, and prohibits
interchanging a driveshaft between different models if the driveshaft
has ever been installed on a Bell Model 407 helicopter. AD 2001-13-51
was prompted by a driveshaft failure on a Bell Model 407 helicopter
that resulted in an engine shutdown and an emergency landing, as well
as three other incidents of a cracked flex frame on the forward end of
the driveshaft on other Model 407 helicopters. AD 2001-13-51 was
prompted by AD No. CF-2001-24, dated June 11, 2001, issued by Transport
Canada Civil Aviation (TCCA), which is the aviation authority for
Canada. TCCA AD No. CF-2001-24 required a one-time visual inspection of
the driveshaft.
Actions Since AD 2001-13-51 Was Issued
Since we issued AD 2001-13-51 (66 FR 48535, September 21, 2001),
the Model 429 helicopter was certificated, and TCCA issued Revision 3,
dated September 26, 2013, to AD No. CF-2001-24. Revision 3 adds Model
429 helicopters to the applicability section and requires removing any
driveshaft, P/N 206-340-300-105, if it has ever been installed on a
Bell Model 407 helicopter.
This proposed AD would expand the applicability to include the Bell
Model 429 helicopter because the driveshaft, P/N 206-340-300-105, can
also be installed on the Bell Model 429 helicopter. Also, we have
removed the requirement to notify the FAA if a crack is found in the
driveshaft because we did not receive any reports of driveshaft
problems. This proposed AD would retain the one-time inspection, if not
previously accomplished, for a crack, a loose bolt or nut, and red
powder residue, and if there is a crack, a loose bolt or nut, or red
powder residue, replacing each unairworthy driveshaft with an airworthy
driveshaft before further flight. The one-time inspection is not
required for Bell Model 429 helicopters because that model would have
had the inspection done when it was certificated. Lastly, this proposed
AD would require for all applicable models, within 1,250 hours time-in-
service (TIS), removing from service any driveshaft, P/N 206-340-300-
105, if it has ever been installed on a Bell Model 407 helicopter.
FAA's Determination
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
our bilateral agreement with Canada, TCAA, its technical
representative, has notified us of the unsafe condition described in
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other helicopters of the same type design.
Related Service Information
We reviewed Bell Alert Service Bulletin (ASB) No. 206L-01-123,
Revision A, dated February 22, 2006, for Bell Model 206L-4 helicopters
and ASB No. 427-01-04, Revision A, dated March 31, 2006, for Bell Model
427 helicopters. Both ASBs describe inspecting the Historical Service
Record of the engine-to-transmission driveshaft, P/N 206-340-300-105,
to determine whether the driveshaft has ever been installed on a Bell
Model 407 helicopter and removing the driveshaft if it has ever been
installed on a Model 407 helicopter. We also reviewed Bell ASB No. 407-
01-45, Revision B, dated April 23, 2013, for Bell Model 407
helicopters, which describes an engine-to-transmission driveshaft
1,250-Hour overhaul. TCCA classified these ASBs as mandatory and issued
AD No. CF-2002-03R3, dated September 26, 2013, to ensure the continued
airworthiness of these helicopters.
Proposed AD Requirements
This proposed AD would require:
Within 50 hours TIS, determining whether driveshaft, P/N
206-340-300-105, has ever been installed on a Bell Model 407 helicopter
and making a note on the component history card or equivalent record.
If a driveshaft has ever been installed on a Model 407 helicopter:
[cir] Within 25 hours TIS, inspecting each Model 206L-4, 407, and
427 helicopter with an affected driveshaft installed for a crack, loose
bolts or nuts, and red powder residue. If there is a crack, a loose
bolt or nut, or red powder residue, replacing the driveshaft with an
airworthy driveshaft before further flight.
[cir] For each helicopter with an affected driveshaft installed, on
or before accumulating 1,250 hours TIS, replacing the driveshaft with
an airworthy driveshaft.
This proposed AD would also prohibit installing driveshaft, P/N
206-340-300-105, on any helicopter if it has ever been installed on a
Bell Model 407 helicopter.
Differences Between the Proposed AD and the TCCA AD
The TCCA AD requires following the compliance time specified in the
Bell ASBs, which allows more time, based on the hours TIS, for removing
the driveshaft. This proposed AD would require replacing the driveshaft
before accumulating 1,250 hours TIS. The proposed AD would also
prohibit the
[[Page 54924]]
use of driveshaft, P/N 206-340-300-105, on the Model 407 helicopter.
Costs of Compliance
We estimate that this proposed AD would affect 970 helicopters of
U.S. Registry. We estimate that operators may incur the following costs
in order to comply with this proposed AD. Labor costs are estimated at
$85 per work-hour. We estimate 0.25 work-hour to determine whether the
driveshaft has ever been installed on a Bell Model 407 helicopter for a
total cost of $22 per helicopter or $21,340 for the fleet. If a
driveshaft has been installed on a Model 407 helicopter, we estimate 1
work hour to inspect the driveshaft for a cost of $85 per helicopter,
and 2 work hours and $39,724 for required parts to replace a driveshaft
for a cost of $39,894 per helicopter.
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 proposed 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, 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 to the extent that
it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
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 removing Airworthiness Directive (AD)
2001-13-51, Amendment 39-12443 (66 FR 48535, September 21, 2001), and
adding the following new AD:
Bell Helicopter Textron Canada (Bell): Docket No. FAA-2014-0643;
Directorate Identifier 2013-SW-059-AD.
(a) Applicability
This AD applies to Model 206L-4, 407, 427, and 429 helicopters
with an engine-to-transmission driveshaft assembly (driveshaft),
part number (P/N) 206-340-300-105, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a driveshaft
due to cracking of the flex frame on the forward end of the
driveshaft. This condition could result in loss of drive to the main
rotor system and a subsequent emergency forced landing.
(c) Affected ADs
This AD supersedes AD 2001-13-51, Amendment 39-12443, Docket No.
2001-SW-29-AD (66 FR 48535, September 21, 2001).
(d) Comments Due Date
We must receive comments by November 14, 2014.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Within 50 hours time-in-service (TIS), determine whether
driveshaft, P/N 206-340-300-105, has ever been installed on a Bell
Model 407 helicopter, and record this on the component history card
or equivalent record. If driveshaft, P/N 206-340-300-105, has ever
been installed on a Bell Model 407 helicopter:
(i) For Bell Model 206L-4, 407, and 427 helicopters, within 25
hours TIS, inspect each driveshaft for a crack, a loose bolt or nut,
and red powder residue. If there is a crack, a loose bolt or nut, or
red powder residue, replace the driveshaft with an airworthy
driveshaft before further flight.
(ii) For all affected Bell model helicopters, on or before
accumulating 1,250 hours TIS, replace each driveshaft with an
airworthy driveshaft.
(2) Do not install driveshaft, P/N 206-340-300-105, on any
helicopter if it has ever been installed on a Bell Model 407
helicopter.
(g) Special Flight Permit
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matthew Fuller, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email matthew.fuller@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(i) Additional Information
(1) Bell Alert Service Bulletin (ASB) No. 206L-01-123, Revision
A, dated February 22, 2006; ASB No. 427-01-04, Revision A, dated
March 31, 2006; and ASB No. 407-01-45, Revision B, dated April 23,
2013, which are not incorporated by reference, contain additional
information about the subject of this AD. For service information
identified in this AD, contact Bell Helicopter Textron Canada
Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone
(450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at https://www.bellcustomer.com/files/. You may review a copy of the service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in Transport Canada
Civil Aviation (TCCA) AD No. CF-2002-03R3, Revision 3, dated
September 26, 2013. You may view the TCCA AD on the Internet at
https://www.regulations.gov in Docket No. FAA-2014-0643.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6300 Main Rotor
Drive System.
[[Page 54925]]
Issued in Fort Worth, Texas, on August 22, 2014.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2014-21919 Filed 9-12-14; 8:45 am]
BILLING CODE 4910-13-P
