Airworthiness Directives; Various Restricted Category Helicopters, 83660-83662 [2016-27767]
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83660
Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations
ST00830SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the stringer (S)–14L and S–14R lap
splices are subject to widespread fatigue
damage (WFD). We are issuing this AD to
detect and correct widespread cracking in the
S–14L and S–14R lap splices that could
rapidly link up and result in possible rapid
decompression and reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
At the applicable compliance time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1352,
Revision 1, dated March 10, 2016, do a low
frequency eddy current inspection for
cracking of the lower fastener row of S–14L
and S–14R lap splices, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1352,
Revision 1, dated March 10, 2016. Repeat the
inspection thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1352,
Revision 1, dated March 10, 2016. If any
cracking is found, before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (i) of
this AD.
sradovich on DSK3GMQ082PROD with RULES
(h) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 737–53A1352, dated October
2, 2015.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
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modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
For more information about this AD,
contact Gaetano Settineri, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6577; fax: 425–917–6590; email:
gaetano.settineri@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737–
53A1352, Revision 1, dated March 10, 2016.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Issued in Renton, Washington, on October
21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–26621 Filed 11–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3820; Directorate
Identifier 2014–SW–024–AD; Amendment
39–18716; AD 2016–23–09]
RIN 2120–AA64
Airworthiness Directives; Various
Restricted Category Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for various
restricted category helicopters. This AD
requires cleaning and visually
inspecting certain main rotor (M/R)
blades and, depending on the outcome
of the inspections, repairing or replacing
the M/R blades. This AD was prompted
by a report of an M/R blade with
multiple fatigue cracks around the blade
retention bolt hole. The actions are
intended to detect a crack in the M/R
blade, and prevent failure of the M/R
blade and subsequent loss of helicopter
control.
DATES: This AD is effective December
27, 2016.
ADDRESSES: For service information
identified in this final 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 a copy of the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
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–
3820; 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 AD, the economic
evaluation, any comments received, and
other information. The street address for
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Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations
the Docket Operations Office (phone:
800–647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Charles Harrison, Project Manager, Fort
Worth Aircraft Certification Office,
10101 Hillwood Pkwy., Fort Worth,
Texas 76177; telephone 817–222–5140;
email Charles.C.Harrison@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On April 11, 2016, at 81 FR 21288, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
Model TH–1F, UH–1B, UH–1F, UH–1H,
and UH–1P helicopters with a M/R
blade, part number 204–011–250–005 or
204–011–250–113, installed. The NPRM
proposed to require repetitively
cleaning and visually inspecting the M/
R blades for a crack, corrosion, an edge
void, loose or damaged adhesion, and
an edge delamination. Depending on the
outcome of the inspections, the NPRM
proposed repairing or replacing the M/
R blades. The actions in the NPRM were
prompted by a Bell Helicopter Textron
Inc. evaluation of an M/R blade
installed on a Model UH–1H helicopter
that had 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. A different part-numbered M/R
blade of the same type installed on the
Model UH–1H helicopter may also be
installed on Model TH–1F, UH–1B, UH–
1F, and UH–1P helicopters.
These actions are intended to detect a
crack in an M/R blade, and prevent
failure of the M/R blade, and subsequent
loss of helicopter control.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(81 FR 21288, April 11, 2016).
sradovich on DSK3GMQ082PROD with RULES
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
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Related Service Information
Bell Helicopter issued Alert Service
Bulletin (ASB) No. UH–1H–13–09,
dated January 14, 2013, for the Model
UH–1H helicopter. ASB No. UH–1H–
13–09 specifies a one-time visual
inspection, within 10 hours time-inservice (TIS), of the lower grip pad and
upper and lower grip plates for cracks,
edge voids, and loose or damaged
adhesive squeeze-out. ASB No. UH–1H–
13–09 also specifies a repetitive and
more detailed visual inspection, daily
and at every 150 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.
Bell Helicopter Textron also issued
ASB No. 204–75–1 for Model 204B
helicopters and ASB No. 205–75–5 for
Model 205A–1 helicopters, both
Revision C and both dated April 25,
1979. ASB No. 204–75–1 and ASB No.
205–75–5 call for visually inspecting the
M/R blades during each daily inspection
and repetitively washing the blades and
applying WD–40. ASB No. 204–75–1
and ASB No. 205–75–5 also provide
instructions for repetitively inspecting
the blades every 1,000 hours of
operation or every 12 months,
whichever occurs first, or within 150
hours or 30 days, whichever occurs first,
if the blades have more 1,000 hours of
operation or have been in service more
than 12 months. While ASB No. 204–
75–1 and ASB No. 205–75–5 do not
apply to the helicopters that are the
subject of this AD, they do apply to the
affected M/R blades.
Differences Between This AD and the
Service Information
ASB No. UH–1H–13–09 specifies a
one-time inspection and then a second
repetitive inspection daily and at every
150 hours TIS, and ASB No. 204–75–1
and ASB 205–75–5 call for visually
inspecting the M/R blades daily and
every 1,000 hours TIS or 12 months,
whichever occurs first. This AD requires
all inspections at intervals not to exceed
25 hours TIS or two weeks, whichever
occurs first. This AD contains more
detailed inspection requirements and a
more specific inspection area than the
instructions in ASB No. UH–1H–13–09.
Lastly, ASB No. UH–1H–13–09 applies
to Model UH–1H helicopters with M/R
blade P/N 204–011–250–113, ASB No.
204–75–1 applies to Model 204B
helicopters with M/R blade P/N 204–
011–250 (all dash numbers), and ASB
No. 205–75–5 applies to Model 205A–
1 helicopters with M/R blade P/N 204–
011–250 (all dash numbers). This AD
applies to Model TH–1F, UH–1B, UH–
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83661
1F, UH–1H, and UH–1P helicopters
with M/R blade P/N 204–011–250–005
or 204–011–250–113.
Costs of Compliance
We estimate that this AD affects 607
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) requires a total of 1⁄2 workhour. No parts are needed. At an
estimated 24 inspections a year, the cost
would be $1,032 per helicopter and
$626,424 for the U.S. fleet.
• Replacing an M/R blade requires 12
work hours while parts 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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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
E:\FR\FM\22NOR1.SGM
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83662
Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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):
■
2016–23–09 Various Restricted Category
Helicopters: Amendment 39–18716;
Docket No. FAA–2015–3820; Directorate
Identifier 2014–SW–024–AD.
(a) Applicability
This AD applies to Model TH–1F, UH–1B,
UH–1F, UH–1H, and UH–1P helicopters with
a main rotor (M/R) blade, part number 204–
011–250–005 or 204–011–250–113, installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in an M/R blade, which could result in
failure of the M/R blade and subsequent loss
of helicopter control.
(c) Effective Date
This AD becomes effective December 27,
2016.
sradovich on DSK3GMQ082PROD with RULES
(d) 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.
(e) 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:
(i) Visually inspect the exposed area 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 entire chord width,
visually inspect each layered doubler and
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Jkt 241001
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 (e)(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 (e)(2)(vi) or (e)(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.
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(f) Special Flight Permits
Special flight permits are prohibited.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Charles Harrison,
Project Manager, Fort Worth Aircraft
Certification Office, 10101 Hillwood Pkwy.,
Fort Worth, Texas 76177; telephone 817–
222–5140; email 9-ASW-FTW-AMOCRequests@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.
(h) Additional Information
Bell Helicopter Alert Service Bulletin
(ASB) No. UH–1H–13–09, dated January 14,
2013, and Bell Helicopter Textron ASB No.
204–75–1 and ASB 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 final rule. For service information
identified in this final 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 a copy of this service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on November
4, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2016–27767 Filed 11–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–4223; Directorate
Identifier 2015–NM–108–AD; Amendment
39–18693; AD 2016–22–04]
RIN 2120–AA64
Airworthiness Directives; Gulfstream
Aerospace Corporation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
SUMMARY:
E:\FR\FM\22NOR1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 225 (Tuesday, November 22, 2016)]
[Rules and Regulations]
[Pages 83660-83662]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27767]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024-AD;
Amendment 39-18716; AD 2016-23-09]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for various
restricted category helicopters. This AD requires cleaning and visually
inspecting certain main rotor (M/R) blades and, depending on the
outcome of the inspections, repairing or replacing the M/R blades. This
AD was prompted by a report of an M/R blade with multiple fatigue
cracks around the blade retention bolt hole. The actions are intended
to detect a crack in the M/R blade, and prevent failure of the M/R
blade and subsequent loss of helicopter control.
DATES: This AD is effective December 27, 2016.
ADDRESSES: For service information identified in this final 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 a copy of the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX
76177.
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-
3820; 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 AD, the economic evaluation, any comments received, and
other information. The street address for
[[Page 83661]]
the Docket Operations Office (phone: 800-647-5527) is U.S. Department
of Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager,
Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort
Worth, Texas 76177; telephone 817-222-5140; email
Charles.C.Harrison@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On April 11, 2016, at 81 FR 21288, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Model TH-1F, UH-1B, UH-
1F, UH-1H, and UH-1P helicopters with a M/R blade, part number 204-011-
250-005 or 204-011-250-113, installed. The NPRM proposed to require
repetitively cleaning and visually inspecting the M/R blades for a
crack, corrosion, an edge void, loose or damaged adhesion, and an edge
delamination. Depending on the outcome of the inspections, the NPRM
proposed repairing or replacing the M/R blades. The actions in the NPRM
were prompted by a Bell Helicopter Textron Inc. evaluation of an M/R
blade installed on a Model UH-1H helicopter that had 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. A different part-numbered M/R blade of the same type installed
on the Model UH-1H helicopter may also be installed on Model TH-1F, UH-
1B, UH-1F, and UH-1P helicopters.
These actions are intended to detect a crack in an M/R blade, and
prevent failure of the M/R blade, and subsequent loss of helicopter
control.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (81 FR 21288, April
11, 2016).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
products of these same type designs and that air safety and the public
interest require adopting the AD requirements as proposed.
Related Service Information
Bell Helicopter issued Alert Service Bulletin (ASB) No. UH-1H-13-
09, dated January 14, 2013, for the Model UH-1H helicopter. ASB No. 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
No. UH-1H-13-09 also specifies a repetitive and more detailed visual
inspection, daily and at every 150 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.
Bell Helicopter Textron also issued ASB No. 204-75-1 for Model 204B
helicopters and ASB No. 205-75-5 for Model 205A-1 helicopters, both
Revision C and both dated April 25, 1979. ASB No. 204-75-1 and ASB No.
205-75-5 call for visually inspecting the M/R blades during each daily
inspection and repetitively washing the blades and applying WD-40. ASB
No. 204-75-1 and ASB No. 205-75-5 also provide instructions for
repetitively inspecting the blades every 1,000 hours of operation or
every 12 months, whichever occurs first, or within 150 hours or 30
days, whichever occurs first, if the blades have more 1,000 hours of
operation or have been in service more than 12 months. While ASB No.
204-75-1 and ASB No. 205-75-5 do not apply to the helicopters that are
the subject of this AD, they do apply to the affected M/R blades.
Differences Between This AD and the Service Information
ASB No. UH-1H-13-09 specifies a one-time inspection and then a
second repetitive inspection daily and at every 150 hours TIS, and ASB
No. 204-75-1 and ASB 205-75-5 call for visually inspecting the M/R
blades daily and every 1,000 hours TIS or 12 months, whichever occurs
first. This AD requires all inspections at intervals not to exceed 25
hours TIS or two weeks, whichever occurs first. This AD contains more
detailed inspection requirements and a more specific inspection area
than the instructions in ASB No. UH-1H-13-09. Lastly, ASB No. UH-1H-13-
09 applies to Model UH-1H helicopters with M/R blade P/N 204-011-250-
113, ASB No. 204-75-1 applies to Model 204B helicopters with M/R blade
P/N 204-011-250 (all dash numbers), and ASB No. 205-75-5 applies to
Model 205A-1 helicopters with M/R blade P/N 204-011-250 (all dash
numbers). This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-
1P helicopters with M/R blade P/N 204-011-250-005 or 204-011-250-113.
Costs of Compliance
We estimate that this AD affects 607 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) requires a total of \1/2\ work-hour. No parts
are needed. At an estimated 24 inspections a year, the cost would be
$1,032 per helicopter and $626,424 for the U.S. fleet.
Replacing an M/R blade requires 12 work hours while parts
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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
[[Page 83662]]
under the criteria of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-23-09 Various Restricted Category Helicopters: Amendment 39-
18716; Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024-
AD.
(a) Applicability
This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P
helicopters with a main rotor (M/R) blade, part number 204-011-250-
005 or 204-011-250-113, installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in an M/R blade,
which could result in failure of the M/R blade and subsequent loss
of helicopter control.
(c) Effective Date
This AD becomes effective December 27, 2016.
(d) 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.
(e) 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:
(i) Visually inspect the exposed area 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 entire 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 (e)(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 (e)(2)(vi) or (e)(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.
(f) Special Flight Permits
Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Charles Harrison,
Project Manager, Fort Worth Aircraft Certification Office, 10101
Hillwood Pkwy., Fort Worth, Texas 76177; telephone 817-222-5140;
email 9-ASW-FTW-AMOC-Requests@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.
(h) Additional Information
Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09,
dated January 14, 2013, and Bell Helicopter Textron ASB No. 204-75-1
and ASB 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 final rule. For service
information identified in this final 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 a copy of this service information at the
FAA, Office of the Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor
Blades.
Issued in Fort Worth, Texas, on November 4, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-27767 Filed 11-21-16; 8:45 am]
BILLING CODE 4910-13-P
