DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

14 CFR Part 39

[Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-13-AD] RIN  2120
-AA64

AIRWORTHINESS DIRECTIVES; Arrow  Falcon  Exporters, Inc.  (Previously Utah
State University), et al., Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E,
UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation
Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This  document proposes  adopting a  new airworthiness  directive
(AD) for the specified type-certificated military surplus helicopters. The
AD would require: Creating a  component history card or equivalent  record
for each main rotor grip (grip); determining and recording the total hours
time-in-service (TIS)  for each  grip; visually  inspecting the  upper and
lower tangs of the grip for  a crack; inspecting the grip buffer  pads for
delamination and if delamination  is present, inspecting the  grip surface
for  corrosion or  other damage;  inspecting the  grip for  a crack  using
ultrasonic  (UT)   and  fluorescent-penetrant   inspection  methods;   and
establishing  a  retirement  life  for  certain  grips.  This  proposal is
prompted by three in-flight failures of grips installed on Bell Helicopter
Textron, Inc.  (BHTI) Model  212 helicopters,  which resulted  from cracks
originating in the lower main rotor blade bolt lug. The actions  specified
by the proposed AD are intended to prevent failure of the grip, separation
of a main rotor blade, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 7, 2010.

ADDRESSES: Use one of the  following addresses to submit comments  on this
proposed AD:

Federal eRulemaking Portal: Go to  http://www.regulations.gov. Follow  the
instructions for submitting comments.

Fax: 202-493-2251.

Mail: U.S.  Department of  Transportation, Docket  Operations, M-30,  West
Building  Ground  Floor,  Room  W12-140,  1200  New  Jersey  Avenue,  SE.,
Washington, DC 20590.

Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30,
West Building  Ground Floor,  Room W12-140,  1200 New  Jersey Avenue, SE.,
Washington, DC 20590,  between 9 a.m.  and 5 p.m.,  Monday through Friday,
except Federal holidays.

You may get  the service information  identified in this  proposed AD from
Bell  Helicopter  Textron,  Inc.,  P.O. Box  482,  Fort  Worth,  TX 76101,
telephone   (817)   280-3391,   fax   (817)   280-6466,   or   at  http://
www.bellcustomer.com/files/.

You may examine the comments to this  proposed AD in the AD docket on  the
Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Michael Kohner,
ASW-170,  Aviation  Safety  Engineer,  Rotorcraft  Directorate, Rotorcraft
Certification  Office,  2601  Meacham  Blvd.,  Fort  Worth,  Texas  76137,
telephone (817) 222-5170, fax (817) 222-5783.

SUPPLEMENTARY INFORMATION:

COMMENTS INVITED

We invite you  to submit any  written data, views,  or arguments regarding
this  proposed AD.  Send your  comments to  the address  listed under  the
caption ADDRESSES. Include  the docket number  "FAA-2010-0564, Directorate
Identifier  2010-SW-13-AD"   at  the   beginning  of   your  comments.  We
specifically  invite  comments   on  the  overall   regulatory,  economic,
environmental, and energy aspects of the proposed AD. We will consider all
comments received by  the closing date  and may amend  the proposed AD  in
light of those comments.

We  will  post  all  comments  we  receive,  without  change,  to  http://
www.regulations.gov, including  any personal  information you  provide. We
will also post a report  summarizing each substantive verbal contact  with
FAA  personnel  concerning  this  proposed  rulemaking.  Using  the search
function of our docket Web site, you can find and read the comments to any
of our dockets, including  the name of the  individual who sent or  signed
the comment. You  may review the  DOT's complete Privacy  Act Statement in
the Federal Register published on April 11, 2000 (65 FR 19477-78).

EXAMINING THE DOCKET

You may examine  the docket that  contains the proposed  AD, any comments,
and other information in person at the Docket Operations office between  9
a.m.  and 5  p.m., Monday  through Friday,  except  Federal  holidays. The
Docket Operations  office (telephone  (800) 647-5527)  is located  in Room
W12-140 on the  ground floor of  the West Building  at the street  address
stated in  the ADDRESSES  section. Comments  will be  available in  the AD
docket shortly after receipt.

DISCUSSION

This document proposes  adopting a new  AD for Model  HH-1K, TH-1F, TH-1L,
UH-1A,  UH-1B,  UH-1E, UH-1F,  UH-1H,  UH-1L, and  UH-1P  helicopters; and
Southwest  Florida  Aviation Model  UH-1B  (SW204 and  SW204HP)  and UH-1H
(SW205) helicopters.  The AD  would require  creating a  component history
card or  equivalent record  for each  grip; determining  and recording the
total hours  TIS for  each grip;  visually inspecting  the upper and lower
tangs  of  the grip  for  a crack;  inspecting  the grip  buffer  pads for
delamination, and if delamination is present, inspecting the grip  surface
for corrosion or other  damage; inspecting the grip  for a crack using  UT
and   fluorescent-penetrant   inspection  methods;   and   establishing  a
retirement life  for grips,  part number  (P/N) 204-011-121-009,  ASI-4011
-121-9, and  P/N 204-011-121-121.  This proposal  is prompted  by three in
-flight failures of grips, P/N 204-011-121-009 and -121, installed on BHTI
Model 212 helicopters, which resulted from cracks originating in the lower
main rotor blade bolt lug. Grips with these same P/Ns, and those  produced
under  an  FAA  Parts  Manufacturing Approval  (PMA)  that  have  a design
approval based on their being identical to the original  BHTI-manufactured
grips, are eligible for installation  on certain modified Model HH-1K,  TH
-1F, TH-1L, and UH-1  helicopters. These helicopters have  an FAA-approved
modification which increases their power  rating to the equivalent of  the
twin-engine Model 212 helicopter power rating. Grips, P/N 204-011-121-005,
and -113, are also affected by the proposed AD if they were ever installed
on a Model 205B or Model UH-1N helicopter; and grip, P/N  204-011-121-117,
is also  affected if  it was  ever installed  on a  Model 205B helicopter.
Additionally, BHTI  has developed  a new,  improved replacement  grip that
will not require the repetitive UT inspections and will have a 25,000 hour
TIS and 500,000 Retirement Index Number (RIN) retirement life for the BHTI
Model 212 helicopters. The RIN  count accumulated for the new  replacement
grips will be  increased by one  for each take-off  or each external  lift
event. The actions  specified by the  proposed AD are  intended to prevent
failure of the grip, separation of a main rotor blade, and subsequent loss
of control of the helicopter.

We have reviewed the following service information:

BHTI Alert Service Bulletin  (ASB) 205B-02-39, Revision B,  dated November
22, 2002, applicable to Model 205B helicopters; and

BHTI ASB  212-02-116, Revision  A, dated  October 30,  2002, applicable to
Model 212 helicopters.

Both ASBs contain  BHTI Nondestructive Inspection  Procedure, Log. No.  00
-340, Revision E, dated April  9, 2002, which describes procedures  for an
UT inspection of  the grip. We  have also reviewed  BHTI Operations Safety
Notice (OSN) 204-85-6, OSN 205-85-9, and OSN 212-85-13, all dated November
14, 1985,  which describe  a cracked  Model 212  helicopter grip  that was
returned to BHTI.

This unsafe condition is likely  to exist or develop on  other helicopters
of the same type designs. Therefore, the proposed AD would require:

Within  10 hours  TIS, creating  a component  history card  or  equivalent
record for the grip, and determining and recording the total hours TIS  of
each grip;

Within 10 hours  TIS, and then  at intervals not  to exceed 25  hours TIS,
visually inspecting  the upper  and lower  tangs of  the grip  for a crack
using a 10-power or higher magnifying glass;

Within 30  days, and  then at  intervals not  to exceed  certain specified
hours TIS  or a  certain number  of engine  start/stops, whichever  occurs
first, for grips with certain specified hours TIS, inspecting the grip for
a crack using a UT inspection method;

At intervals not to exceed 1,200 hours TIS or 24 months, whichever  occurs
first, inspecting the grip buffer pads for delamination, and if delaminat-
ion is present, inspecting the grip surface for corrosion or other damage;

Within 2,400 hours TIS or at  the next main rotor hub overhaul,  whichever
occurs  first,  and then  at  intervals not  to  exceed 2,400  hours  TIS,
removing the grip  buffer pads, visually  inspecting the grip  surface for
corrosion or other damage,  and fluorescent-penetrant inspecting the  grip
for a crack;

Before further flight, removing from service any grip, P/N 204-011-121-009
or ASI-4011-121-9, with 15,000 or more hours TIS;

Before further  flight, removing  from service  any grip,  P/N 204-011-121
-121, with 25,000 or more hours TIS;

Before further flight, replacing any unairworthy grip; and

Establishing a retirement life of  15,000 hours TIS for grip,  P/N 204-011
-121-009 or  ASI-4011-121-9, and  25,000 hours  TIS for  grip, P/N 204-011
-121-121.

We estimate  that this  proposed AD  would affect  20 helicopters  of U.S.
registry, and the  proposed actions would  take the following  approximate
number of work hours per helicopter to accomplish at an average labor rate
of $85 per work hour:

Create new component history cards or equivalent: 2 work hours;

Maintain records: 5 work hours per year;

24 visual inspections using a magnifying glass: 12 work hours per year;

\1/2\ of a buffer pad inspection: 1.5 hours per year;

\1/4\ of a fluorescent penetrant inspection: .5 work hour per year;

4 UT inspections: 4 work hours per year; and

Remove and replace grip set: 20 work hours per year.

Required parts would cost approximately $37,590 per set of grips. Based on
these figures, we  estimate the total  cost impact of  the proposed AD  on
U.S. operators to  be $828,300, if  one set of  grips is installed  on the
total affected fleet of helicopters at the end of the first year.

REGULATORY FINDINGS

We  have  determined  that  this proposed  AD  would  not  have federalism
implications under Executive Order  13132. Additionally, this proposed  AD
would  not  have  a  substantial  direct  effect  on  the  States,  on the
relationship between  the national  Government and  the States,  or on the
distribution of  power and  responsibilities among  the various  levels of
government.

For the reasons discussed above, I certify that the 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 Proc-
   edures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a
   substantial number of small entities under the criteria of the Regulat-
   ory Flexibility Act.

We prepared a draft economic  evaluation of the estimated costs  to comply
with this proposed  AD. See the  AD docket to  examine the draft  economic
evaluation.

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 devel-
op on products identified in this rulemaking action.

LIST OF SUBJECTS IN 14 CFR PART 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference,
Safety.

THE PROPOSED AMENDMENT

Accordingly,  pursuant   to  the   authority  delegated   to  me   by  the
Administrator, the Federal Aviation Administration proposes to amend  part
39 of the Federal Aviation Regulations (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.

SEC. 39.13 [AMENDED]

2. Section  39.13 is  amended by  adding a  new airworthiness directive to
   read as follows: