Airworthiness Directives; Bell Helicopter Textron, 27055-27057 [2016-10523]
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Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3821; Directorate
Identifier 2014–SW–025–AD
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 75–26–05
for Bell Helicopter Textron (Bell) Model
204B, 205A–1 and 212 helicopters. AD
75–26–05 currently requires removing
and visually inspecting each main rotor
(M/R) blade and, depending on the
inspection’s outcome, repairing or
replacing the M/R blades. This proposed
AD would require more frequent
inspections of certain M/R blades and
would also apply to Model 205A
helicopters. This proposed AD would
have no requirement that helicopter
blades be removed to conduct the initial
visual inspections. These proposed
actions are intended to detect a crack
and prevent failure of an M/R blade and
subsequent loss of helicopter control.
DATES: We must receive comments on
this proposed AD by July 5, 2016.
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.
SUMMARY:
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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–2015–
3821; 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
economic evaluation, any comments
received and other information. The
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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 rule, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817)
280–3391; fax (817) 280–6466; or at
https://www.bellcustomer.com/files/.
You may review service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
FOR FURTHER INFORMATION CONTACT:
Charles Harrison, Project Manager, Fort
Worth Aircraft Certification Office,
FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–
5140; email charles.c.harrison@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 December 3, 1975, we issued AD
75–26–05, Amendment 39–2457 (40 FR
57783, December 12, 1975) for Bell
Model 204B, 205A–1, and 212
helicopters. AD 75–26–05 requires, at
intervals not to exceed 12 months
installed time, visually inspecting the
grip pad, grip plates, doublers, drag
plates, and adjacent surfaces for voids,
edge voids, corrosion, cracks, and
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27055
adhesive squeeze-out along bond lines.
AD 75–26–05 prohibits returning to
service any blade with a crack or an
adhesive void exceeding certain limits.
For damage within certain limits, the
M/R blade can be repaired, refinished,
and reinstalled.
AD 75–26–05 was prompted by an
evaluation of a cracked M/R blade that
concludes that initial cracking resulted
from corrosion. These actions were
intended to detect a crack and corrosion
and prevent further corrosion in the
M/R blade inboard portion.
Actions Since AD 75–26–05 Was Issued
Since we issued AD 75–26–05, Bell
has evaluated an M/R blade installed on
a Model UH–1H helicopter with
multiple fatigue cracks around the blade
retention bolt hole. The cracks resulted
from a void between the lower grip plate
and the grip pad. A ‘‘substantial’’ void
also was found at the outboard doubler
tip on the lower blade surface. Different
part-numbered M/R blades of the same
type may also be installed on Model
204B, 205A, and 205A–1 helicopters.
We have determined that more frequent
inspections than those required by AD
75–26–05 are necessary to detect
cracking or certain damage. While AD
75–26–05 requires removing the blades
from the M/R hub, the inspections in
this proposed AD would not. AD 75–
26–05 applies to the Model 212
helicopter, and this proposed AD would
not because similar inspections on
Model 212 blades addressing the unsafe
condition are required by AD 2011–23–
02 (76 FR 68301, November 4, 2011).
We are including specific partnumbered blades in the applicability so
that the proposed AD would no longer
be required if a new blade is designed
that is not subject to the unsafe
condition.
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.
Related Service Information
Bell issued Alert Service Bulletin
(ASB) No. UH–1H–13–09, dated January
14, 2013, for the Model UH–1H
helicopter (ASB UH–1H–13–09). ASB
UH–1H–13–09 specifies a one-time
visual inspection, within 10 hours timein-service (TIS), of the lower grip pad
and upper and lower grip plates for
cracks, edge voids, and loose or
damaged adhesive squeeze-out. ASB
UH–1H–13–09 also specifies a repetitive
visual inspection, daily and at every 150
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Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules
hours TIS, of the lower grip pad, upper
and lower grip plates, and all upper and
the lower doublers for cracks, corrosion,
edge voids, and loose or damaged
adhesive squeeze-out. Similar
inspections are contained in Bell ASB
No. 204–75–1 (ASB 204–75–1) and No.
205–75–5 (ASB 205–75–5), both
Revision C and both dated April 25,
1979, for Bell Model 204B and 205A–1
helicopters, respectively. ASB 204–75–1
and ASB 205–75–5 call for daily
inspections and for inspections, rework,
and refinishing every 1,000 hours TIS or
12 months, whichever occurs first.
Proposed AD Requirements
This proposed AD would require
within 25 hours TIS or 2 weeks,
whichever occurs first, and thereafter at
intervals not to exceed 25 hours TIS or
2 weeks, whichever occurs first,
cleaning the upper and lower surfaces of
each M/R blade from an area starting at
the butt end of the blade to three inches
outboard of the doublers. The proposed
AD also would require visually
inspecting various M/R parts for a crack
or corrosion using a 3X or higher power
magnifying glass and a light.
If there is a crack, corrosion, an edge
void, loose or damaged adhesive
squeeze-out, or an edge delamination
before further flight, this proposed AD
would require repairing the M/R blade
or replacing it with an airworthy M/R
blade, depending on the condition’s
severity.
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Differences Between This Proposed AD
and the Service Information
The proposed AD would require all
inspections every 25 hours TIS or 2
weeks, whichever occurs first. ASB UH–
1H–13–09 specifies a one-time
inspection within 10 hours TIS, and
then a second repetitive inspection
daily and at every 150 hours TIS, while
ASB 204–75–1 and ASB 205–75–5 call
for daily visual inspections, and
inspections, rework, and refinishing
every 1,000 hours TIS or 12 months,
whichever occurs first. This proposed
AD contains more detailed inspection
requirements and a more specific
inspection area than the instructions in
ASB UH–1H–13–09. The service
information applies to M/R blade, part
number (P/N) 204–011–250, and was
issued for Model 204B and 205A–1
helicopters. The proposed AD also
applies to P/N 204–011–200, because
this blade is of the same type and
susceptible to the unsafe condition. The
proposed AD also applies to certain
M/R blades installed on the Model 205A
helicopters. While none of these models
are registered in the U.S., they were
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included because of blade P/N
eligibility.
Costs of Compliance
We estimate that this proposed AD
would affect 52 helicopters of U.S.
Registry and that labor costs average $85
a work-hour. Based on these estimates,
we expect the following costs:
Cleaning and performing all
inspections of a set of M/R blades (2 per
helicopter) would require a half workhour. No parts would be needed. At an
estimated 24 inspections a year, the cost
would be $1,032 per helicopter and
$53,664 for the U.S. fleet.
Replacing an M/R blade would
require 12 work hours and parts would
cost $90,656 for a total cost of $91,676
per blade.
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, 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,
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Sfmt 4702
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
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
removing Airworthiness Directive (AD)
No. 75–26–05, Amendment 39–2457 (40
FR 57783, December 12, 1975), and
adding the following new AD:
■
Bell Helicopter Textron: Docket No. FAA–
2015–3821; Directorate Identifier 2014–
SW–025–AD.
(a) Applicability
This AD applies to Model 204B, 205A, and
205A–1 helicopters with a main rotor (M/R)
blade, part number (P/N) 204–011–200–001
or P/N 204–011–250–(all dash numbers),
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in an M/R blade, which could result in
failure of an M/R blade and subsequent loss
of helicopter control.
(c) Affected ADs
This AD supersedes AD 75–26–05,
Amendment 39–2457 (40 FR 57783,
December 12, 1975).
(d) Comments Due Date
We must receive comments by July 5, 2016.
(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 25 hours time-in-service (TIS) or
2 weeks, whichever occurs first, and
thereafter at intervals not to exceed 25 hours
TIS or 2 weeks, whichever occurs first, clean
the upper and lower exposed surfaces of each
M/R blade from an area starting at the butt
end of the blade to three inches outboard of
the doublers. Using a 3X or higher power
magnifying glass and a light, inspect as
follows:
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Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules
(i) Visually inspect the exposed areas of the
lower grip pad and upper and lower grip
plates of each M/R blade for a crack and any
corrosion.
(ii) On the upper and lower exposed
surfaces of each M/R blade from blade
stations 24.5 to 35 for the chord width,
visually inspect each layered doubler and
blade skin for a crack and any corrosion. Pay
particular attention for any cracking in a
doubler or skin near or at the same blade
station as the blade retention bolt hole (blade
station 28).
(iii) Visually inspect the exposed areas of
each bond line at the edges of the lower grip
pad, upper and lower grip plates, and each
layered doubler (bond lines) on the upper
and lower surfaces of each M/R blade for the
entire length and chord width for an edge
void, any corrosion, loose or damaged
adhesive squeeze-out, and an edge
delamination. Pay particular attention to any
crack in the paint finish that follows the
outline of a grip pad, grip plate, or doubler,
and to any loose or damaged adhesive
squeeze-out, as these may be the indication
of an edge void.
(2) If there is a crack, any corrosion, an
edge void, loose or damaged adhesive
squeeze-out, or an edge delamination during
any inspection in paragraph (f)(1) of this AD,
before further flight, do the following:
(i) If there is a crack in a grip pad or any
grip plate or doubler, replace the M/R blade
with an airworthy M/R blade.
(ii) If there is a crack in the M/R blade skin
that is within maximum repair damage
limits, repair the M/R blade. If the crack
exceeds maximum repair damage limits,
replace the M/R blade with an airworthy M/
R blade.
(iii) If there is any corrosion within
maximum repair damage limits, repair the M/
R blade. If the corrosion exceeds maximum
repair damage limits, replace the M/R blade
with an airworthy M/R blade.
(iv) If there is an edge void in the grip pad
or in a grip plate or doubler, determine the
length and depth using a feeler gauge. Repair
the M/R blade if the edge void is within
maximum repair damage limits, or replace
the M/R blade with an airworthy M/R blade.
(v) If there is an edge void in a grip plate
or doubler near the outboard tip, tap inspect
the affected area to determine the size and
shape of the void. Repair the M/R blade if the
edge void is within maximum repair damage
limits, or replace the M/R blade with an
airworthy M/R blade.
(vi) If there is any loose or damaged
adhesive squeeze-out along any of the bond
lines, trim or scrape away the adhesive
without damaging the adjacent surfaces or
parent material of the M/R blade. Determine
if there is an edge void or any corrosion by
lightly sanding the trimmed area smooth
using 280 or finer grit paper. If there is no
edge void or corrosion, refinish the sanded
area.
(vii) If there is an edge delamination along
any of the bond lines or a crack in the paint
finish, determine if there is an edge void or
a crack in the grip pad, grip plate, doubler,
or skin by removing paint from the affected
area by lightly sanding in a span-wise
direction using 180–220 grit paper. If there
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Jkt 238001
are no edge voids and no cracks, refinish the
sanded area.
(viii) If any parent material is removed
during any sanding or trimming in
paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD,
repair the M/R blade if the damage is within
maximum repair damage limits, or replace
the M/R blade with an airworthy M/R blade.
Special flight permits are prohibited.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Fort Worth Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Charles Harrison, Project Manager, Fort
Worth Aircraft Certification Office, FAA,
10101 Hillwood Pkwy, Fort Worth, TX
76177; telephone (817) 222–5140; email 7AVS-ASW-170@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
Bell Helicopter Alert Service Bulletin
(ASB) No. UH–1H–13–09, dated January 14,
2013, and ASB No. 204–75–1 and ASB No.
205–75–5, both Revision C and both dated
April 25, 1979, 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, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817) 280–
3391; fax (817) 280–6466; or at https://
www.bellcustomer.com/files/. You may
review the service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy, Room 6N–
321, Fort Worth, TX 76177.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on April 15,
2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–10523 Filed 5–4–16; 8:45 am]
BILLING CODE 4910–13–P
Frm 00009
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3941; Directorate
Identifier 2015–SW–052–AD]
RIN 2120–AA64
(g) Special Flight Permit
PO 00000
27057
Sfmt 4702
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
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 Deutschland GmbH (Airbus
Helicopters) Model MBB–BK 117A–3,
MBB–BK 117A–4, MBB–BK 117B–1,
MBB–BK 117B–2, and MBB–BK 117C–
1 helicopters. This proposed AD would
require removing adhesive seals from
the exterior and interior door jettisoning
system on the left and right sliding
doors. This proposed AD is prompted
by reports that the adhesive seal
prevented the doors from jettisoning
properly. The proposed actions are
intended to remove the adhesive seal to
allow the doors to jettison properly so
occupants can exit the helicopter during
an emergency.
DATES: We must receive comments on
this proposed AD by July 5, 2016.
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.
SUMMARY:
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–2015–
3941; 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,
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Agencies
[Federal Register Volume 81, Number 87 (Thursday, May 5, 2016)]
[Proposed Rules]
[Pages 27055-27057]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10523]
[[Page 27055]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 75-26-05
for Bell Helicopter Textron (Bell) Model 204B, 205A-1 and 212
helicopters. AD 75-26-05 currently requires removing and visually
inspecting each main rotor (M/R) blade and, depending on the
inspection's outcome, repairing or replacing the M/R blades. This
proposed AD would require more frequent inspections of certain M/R
blades and would also apply to Model 205A helicopters. This proposed AD
would have no requirement that helicopter blades be removed to conduct
the initial visual inspections. These proposed actions are intended to
detect a crack and prevent failure of an M/R blade and subsequent loss
of helicopter control.
DATES: We must receive comments on this proposed AD by July 5, 2016.
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 by searching for and locating Docket No. FAA-2015-
3821; 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 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 rule, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/. You may review service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N-321, Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager,
Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5140; email
charles.c.harrison@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 December 3, 1975, we issued AD 75-26-05, Amendment 39-2457 (40
FR 57783, December 12, 1975) for Bell Model 204B, 205A-1, and 212
helicopters. AD 75-26-05 requires, at intervals not to exceed 12 months
installed time, visually inspecting the grip pad, grip plates,
doublers, drag plates, and adjacent surfaces for voids, edge voids,
corrosion, cracks, and adhesive squeeze-out along bond lines. AD 75-26-
05 prohibits returning to service any blade with a crack or an adhesive
void exceeding certain limits. For damage within certain limits, the M/
R blade can be repaired, refinished, and reinstalled.
AD 75-26-05 was prompted by an evaluation of a cracked M/R blade
that concludes that initial cracking resulted from corrosion. These
actions were intended to detect a crack and corrosion and prevent
further corrosion in the M/R blade inboard portion.
Actions Since AD 75-26-05 Was Issued
Since we issued AD 75-26-05, Bell has evaluated an M/R blade
installed on a Model UH-1H helicopter with multiple fatigue cracks
around the blade retention bolt hole. The cracks resulted from a void
between the lower grip plate and the grip pad. A ``substantial'' void
also was found at the outboard doubler tip on the lower blade surface.
Different part-numbered M/R blades of the same type may also be
installed on Model 204B, 205A, and 205A-1 helicopters. We have
determined that more frequent inspections than those required by AD 75-
26-05 are necessary to detect cracking or certain damage. While AD 75-
26-05 requires removing the blades from the M/R hub, the inspections in
this proposed AD would not. AD 75-26-05 applies to the Model 212
helicopter, and this proposed AD would not because similar inspections
on Model 212 blades addressing the unsafe condition are required by AD
2011-23-02 (76 FR 68301, November 4, 2011). We are including specific
part-numbered blades in the applicability so that the proposed AD would
no longer be required if a new blade is designed that is not subject to
the unsafe condition.
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.
Related Service Information
Bell issued Alert Service Bulletin (ASB) No. UH-1H-13-09, dated
January 14, 2013, for the Model UH-1H helicopter (ASB UH-1H-13-09). ASB
UH-1H-13-09 specifies a one-time visual inspection, within 10 hours
time-in-service (TIS), of the lower grip pad and upper and lower grip
plates for cracks, edge voids, and loose or damaged adhesive squeeze-
out. ASB UH-1H-13-09 also specifies a repetitive visual inspection,
daily and at every 150
[[Page 27056]]
hours TIS, of the lower grip pad, upper and lower grip plates, and all
upper and the lower doublers for cracks, corrosion, edge voids, and
loose or damaged adhesive squeeze-out. Similar inspections are
contained in Bell ASB No. 204-75-1 (ASB 204-75-1) and No. 205-75-5 (ASB
205-75-5), both Revision C and both dated April 25, 1979, for Bell
Model 204B and 205A-1 helicopters, respectively. ASB 204-75-1 and ASB
205-75-5 call for daily inspections and for inspections, rework, and
refinishing every 1,000 hours TIS or 12 months, whichever occurs first.
Proposed AD Requirements
This proposed AD would require within 25 hours TIS or 2 weeks,
whichever occurs first, and thereafter at intervals not to exceed 25
hours TIS or 2 weeks, whichever occurs first, cleaning the upper and
lower surfaces of each M/R blade from an area starting at the butt end
of the blade to three inches outboard of the doublers. The proposed AD
also would require visually inspecting various M/R parts for a crack or
corrosion using a 3X or higher power magnifying glass and a light.
If there is a crack, corrosion, an edge void, loose or damaged
adhesive squeeze-out, or an edge delamination before further flight,
this proposed AD would require repairing the M/R blade or replacing it
with an airworthy M/R blade, depending on the condition's severity.
Differences Between This Proposed AD and the Service Information
The proposed AD would require all inspections every 25 hours TIS or
2 weeks, whichever occurs first. ASB UH-1H-13-09 specifies a one-time
inspection within 10 hours TIS, and then a second repetitive inspection
daily and at every 150 hours TIS, while ASB 204-75-1 and ASB 205-75-5
call for daily visual inspections, and inspections, rework, and
refinishing every 1,000 hours TIS or 12 months, whichever occurs first.
This proposed AD contains more detailed inspection requirements and a
more specific inspection area than the instructions in ASB UH-1H-13-09.
The service information applies to M/R blade, part number (P/N) 204-
011-250, and was issued for Model 204B and 205A-1 helicopters. The
proposed AD also applies to P/N 204-011-200, because this blade is of
the same type and susceptible to the unsafe condition. The proposed AD
also applies to certain M/R blades installed on the Model 205A
helicopters. While none of these models are registered in the U.S.,
they were included because of blade P/N eligibility.
Costs of Compliance
We estimate that this proposed AD would affect 52 helicopters of
U.S. Registry and that labor costs average $85 a work-hour. Based on
these estimates, we expect the following costs:
Cleaning and performing all inspections of a set of M/R blades (2
per helicopter) would require a half work-hour. No parts would be
needed. At an estimated 24 inspections a year, the cost would be $1,032
per helicopter and $53,664 for the U.S. fleet.
Replacing an M/R blade would require 12 work hours and parts would
cost $90,656 for a total cost of $91,676 per blade.
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, 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)
No. 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975), and
adding the following new AD:
Bell Helicopter Textron: Docket No. FAA-2015-3821; Directorate
Identifier 2014-SW-025-AD.
(a) Applicability
This AD applies to Model 204B, 205A, and 205A-1 helicopters with
a main rotor (M/R) blade, part number (P/N) 204-011-200-001 or P/N
204-011-250-(all dash numbers), installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in an M/R blade,
which could result in failure of an M/R blade and subsequent loss of
helicopter control.
(c) Affected ADs
This AD supersedes AD 75-26-05, Amendment 39-2457 (40 FR 57783,
December 12, 1975).
(d) Comments Due Date
We must receive comments by July 5, 2016.
(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 25 hours time-in-service (TIS) or 2 weeks, whichever
occurs first, and thereafter at intervals not to exceed 25 hours TIS
or 2 weeks, whichever occurs first, clean the upper and lower
exposed surfaces of each M/R blade from an area starting at the butt
end of the blade to three inches outboard of the doublers. Using a
3X or higher power magnifying glass and a light, inspect as follows:
[[Page 27057]]
(i) Visually inspect the exposed areas of the lower grip pad and
upper and lower grip plates of each M/R blade for a crack and any
corrosion.
(ii) On the upper and lower exposed surfaces of each M/R blade
from blade stations 24.5 to 35 for the chord width, visually inspect
each layered doubler and blade skin for a crack and any corrosion.
Pay particular attention for any cracking in a doubler or skin near
or at the same blade station as the blade retention bolt hole (blade
station 28).
(iii) Visually inspect the exposed areas of each bond line at
the edges of the lower grip pad, upper and lower grip plates, and
each layered doubler (bond lines) on the upper and lower surfaces of
each M/R blade for the entire length and chord width for an edge
void, any corrosion, loose or damaged adhesive squeeze-out, and an
edge delamination. Pay particular attention to any crack in the
paint finish that follows the outline of a grip pad, grip plate, or
doubler, and to any loose or damaged adhesive squeeze-out, as these
may be the indication of an edge void.
(2) If there is a crack, any corrosion, an edge void, loose or
damaged adhesive squeeze-out, or an edge delamination during any
inspection in paragraph (f)(1) of this AD, before further flight, do
the following:
(i) If there is a crack in a grip pad or any grip plate or
doubler, replace the M/R blade with an airworthy M/R blade.
(ii) If there is a crack in the M/R blade skin that is within
maximum repair damage limits, repair the M/R blade. If the crack
exceeds maximum repair damage limits, replace the M/R blade with an
airworthy M/R blade.
(iii) If there is any corrosion within maximum repair damage
limits, repair the M/R blade. If the corrosion exceeds maximum
repair damage limits, replace the M/R blade with an airworthy M/R
blade.
(iv) If there is an edge void in the grip pad or in a grip plate
or doubler, determine the length and depth using a feeler gauge.
Repair the M/R blade if the edge void is within maximum repair
damage limits, or replace the M/R blade with an airworthy M/R blade.
(v) If there is an edge void in a grip plate or doubler near the
outboard tip, tap inspect the affected area to determine the size
and shape of the void. Repair the M/R blade if the edge void is
within maximum repair damage limits, or replace the M/R blade with
an airworthy M/R blade.
(vi) If there is any loose or damaged adhesive squeeze-out along
any of the bond lines, trim or scrape away the adhesive without
damaging the adjacent surfaces or parent material of the M/R blade.
Determine if there is an edge void or any corrosion by lightly
sanding the trimmed area smooth using 280 or finer grit paper. If
there is no edge void or corrosion, refinish the sanded area.
(vii) If there is an edge delamination along any of the bond
lines or a crack in the paint finish, determine if there is an edge
void or a crack in the grip pad, grip plate, doubler, or skin by
removing paint from the affected area by lightly sanding in a span-
wise direction using 180-220 grit paper. If there are no edge voids
and no cracks, refinish the sanded area.
(viii) If any parent material is removed during any sanding or
trimming in paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, repair
the M/R blade if the damage is within maximum repair damage limits,
or replace the M/R blade with an airworthy M/R blade.
(g) Special Flight Permit
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Fort Worth Aircraft Certification Office, FAA,
may approve AMOCs for this AD. Send your proposal to: Charles
Harrison, Project Manager, Fort Worth Aircraft Certification Office,
FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-
5140; email 7-AVS-ASW-170@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
Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09,
dated January 14, 2013, and ASB No. 204-75-1 and ASB No. 205-75-5,
both Revision C and both dated April 25, 1979, 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, Inc., P.O. Box 482, Fort Worth, TX
76101; telephone (817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/. You may review the service information
at the FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor
Blades.
Issued in Fort Worth, Texas, on April 15, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-10523 Filed 5-4-16; 8:45 am]
BILLING CODE 4910-13-P