Document ID: FAA-2012-1093-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Brantly International, Inc. Helicopters
Posted Date: 2012-10-16T04:00Z

[Federal Register Volume 77, Number 200 (Tuesday, October 16, 2012)]
[Proposed Rules]
[Pages 63285-63287]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-25444]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1093; Directorate Identifier 2011-SW-020-AD]
RIN 2120-AA64

Airworthiness Directives; Brantly International, Inc. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
Brantly International, Inc. (Brantly) Model B-2, Model B-2A, and Model 
B-2B helicopters with a certain main rotor blade. This proposed AD was 
prompted by multiple reports of main rotor (M/R) blade cracks and an 
accident in which a crack that originated near the M/R blade trailing 
edge resulted in the loss of a large section of the M/R blade. The 
proposed actions are intended to prevent loss of the M/R blade and 
subsequent loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by December 17, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://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 http://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 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 
Brantly International, Inc., 621 South Royal Lane, Suite 100, Coppell, 
Texas 75019, telephone (972) 829-4638, email 
tarcher@superiorairparts.com. You may review a copy of 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: Marc Belhumeur, Senior Project 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5177; 
email marc.belhumeur@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

    We propose to adopt a new AD for all Brantly B-2, B-2A, and B-2B 
helicopters with an M/R blade, part number (P/N) 248-101, 248-202, or 
248-404. This proposed AD is prompted by a 2007 accident in New Zealand 
in which a large inboard section of the M/R blade of a Brantly B-2B 
helicopter separated from the helicopter during flight. Laboratory 
analysis concluded that the M/R blade failure was caused by hydrocarbon 
contaminants inside the blade's skin-to-foam bond and that the fracture 
originated near the blade's trailing edge. There were three other 
reports of portions of M/R blades separating during flight and another 
five reports of M/R blades having cracks or other defects that were 
found during inspections.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant 
information and determined that an unsafe condition exists and is 
likely to exist or develop on other products of these same type 
designs.

Related Service Information

    We reviewed Brantly International Inc. Service Bulletin No. 111, 
dated February 10, 2011 (SB 111). The bulletin describes procedures for 
inspecting the M/R blades every 300 hours time-in-service (TIS) using 
Eddy Current Procedure ET002, performing a visual inspection using a 
10X power magnifying glass and conducting a tap

[[Page 63286]]

test every 25 hours TIS and a visual inspection of the M/R blades 
before the first flight of the day.

Proposed AD Requirements

    This proposed AD would require, before the first flight of each 
day, for any helicopter with M/R blade, P/N 248-101, 248-202, or 248-
404, visually inspecting the M/R blade for a crack, nick, wrinkle, or 
bend. Within 8 hours TIS, this proposed AD would require for any 
helicopter with an M/R blade P/N 248-404 with 10 or more years in 
service or 1,000 or more hours TIS, whichever occurs first, or for any 
helicopter with M/R blade, P/N 248-101 or P/N 248-202:
     Having an inspector qualified to the American Society for 
Nondestructive Testing (ASNT) Level II or equivalent, perform an eddy 
current inspection for a crack or a nick and repeating this inspection 
at intervals not to exceed 300 hours TIS or five calendar years, 
whichever occurs first.
     Tap inspecting for delamination focusing more attention on 
the inboard first 12 inches of the top and bottom of the M/R blade and 
repeating this action at intervals not to exceed 25 hours TIS.
     Visually inspecting with a 10X or higher power magnifying 
glass for a crack, nick, crease, wrinkle, bend, added hole (such as a 
drilled hole to stop the spread of a crack), extra rivet, or inadequate 
rivet spacing and repeating this inspection at intervals not to exceed 
25 hours TIS.
     Before further flight, removing from service any M/R blade 
that has a crack, nick, crease, wrinkle, bend, extra hole, extra rivet 
or inadequate rivet spacing or any delamination.

Differences Between This Proposed AD and the Service Information

    SB 111 requires accomplishment of sections 1 and 2 before further 
flight. The proposed AD requires it to be completed within 8 hours TIS. 
SB 111 allows up to 10 square inches of delamination outside of the 
inboard 12 inches of the M/R blade. The proposed AD does not.

 Costs of Compliance

    We estimate that this proposed AD would affect 76 helicopters of 
U.S. registry. We estimate the following costs to comply with this 
proposed AD, using an average of $85 per work-hour:
     For the visual inspection before the first flight of each 
day, we estimate that it would require about one work-hour for a labor 
cost of $85 per inspection cycle. No parts would be needed, so the 
total cost for the U.S. fleet would be $6,460.
     For the eddy current inspection, we estimate that it would 
require about four work-hours for a labor cost of $340 per inspection 
cycle. No parts would be needed, so the total cost for the 76-
helicopter U.S. fleet would be $25,840 per inspection cycle.
     For the visual inspection with the magnifying glass and 
the tap inspection, we estimate that it would require about three work-
hours for a labor cost of $255 per inspection cycle. No parts would be 
needed, so the total cost for the U.S. fleet would be $19,380 per 
inspection cycle.
     Replacing an M/R blade, if needed, would require about two 
work-hours for a labor cost of $170. An M/R blade would cost $7,500 for 
a total cost of $7,670 per helicopter, assuming one M/R blade is 
replaced.

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

    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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Brantly International, Inc.: Docket No. FAA-2012-1093; Directorate 
Identifier 2011-SW-020-AD.

(a) Applicability

    This AD applies to the Model B-2, Model B-2A, and Model B-2B 
helicopters, with a main rotor (M/R) blade, part number (P/N) 248-
101, 248-202, or 248-404, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack, nick, crease, 
wrinkle, bend, extra hole, extra rivet, inadequate rivet spacing, or 
any delamination in an M/R blade. Any of these conditions could 
result in loss of an M/R blade and subsequent loss of control of the 
helicopter.

(c) 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.

(d) Required Actions

    (1) Before the first flight of each day, visually inspect each 
M/R blade for a crack, nick, wrinkle, or bend. Pay particular 
attention to the M/R blade root area, the area around the lead/lag 
damper mounting fork, and the trailing edge.
    (2) Within 8 hours time-in-service (TIS), for a helicopter with 
an M/R blade, P/N 248-101 or P/N 248-202, and for a helicopter with 
an M/R blade P/N 248-404 with 10 or more years or 1,000 or more 
hours TIS, whichever occurs first, remove each M/R blade and:
    (i) Using an inspector qualified to the American Society for 
Nondestructive Testing

[[Page 63287]]

(ASNT) Level II or equivalent, eddy current inspect each M/R blade 
for a crack or a nick in accordance with paragraph number 4 and 
paragraph number 7 through 17 of Technique Number ET002, dated 
November 2007, attached to Brantly International, Inc., Service 
Bulletin No. 111, dated February 10, 2011 (SB 111).
    (ii) Thereafter, at intervals not to exceed 300 hours TIS or 
five calendar years, whichever occurs first, repeat the eddy current 
inspection in accordance with the requirements of paragraph 
(d)(2)(i) of this AD.
    (iii) Using a metallic coin or tap hammer, tap inspect each M/R 
blade for delamination in the bonded areas as shown on SB 111, 
Section 4. Pay particular attention to the root area in the first 12 
inches of the top and bottom of each M/R blade.
    (iv) Using a 10X or higher power magnifying glass, visually 
inspect for a crack, nick, crease, wrinkle, bend, extra hole (such 
as a stop drill hole), extra rivet, and any inadequate rivet spacing 
caused by additional holes or rivets.
    (v) Thereafter, at intervals not to exceed 25 hours TIS, repeat 
the tap inspection in accordance with the requirements of paragraph 
(d)(2)(iii) of this AD and the visual inspection using a 10X or 
higher power magnifying glass in accordance with the requirements of 
paragraph (d)(2)(iv) of this AD.
    (3) Before further flight, remove from service any M/R blade 
with a crack, nick, crease, wrinkle, bend, extra hole, extra rivet, 
delamination, or inadequate rivet spacing caused by additional holes 
or rivets.

(e) Alternative Methods of Compliance (AMOC)

    (1) The Manager, Safety Management Group, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. Send your proposal to: Marc Belhumeur, Senior 
Project Engineer, Rotorcraft Certification Office, Rotorcraft 
Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; 
telephone (817) 222-5177; email marc.belhumeur@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.

(f) Additional Information

    For service information identified in this AD, contact Brantly 
International, Inc, 621 South Royal Lane, Suite 100, Coppell Texas 
75019, telephone (972) 829-4638, email tarcher@superiorairparts.com. 
You may review a copy of this information at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

 (g) Subject

    Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor 
Blade.

    Issued in Fort Worth, Texas, on October 5, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-25444 Filed 10-15-12; 8:45 am]
BILLING CODE 4910-13-P