[Federal Register: March 13, 2008 (Volume 73, Number 50)]
[Proposed Rules]
[Page 13515-13518]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13mr08-28]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0287; Directorate Identifier 2006-SW-15-AD]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model 369A, OH-6A,
369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS 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
[[Page 13516]]
(AD) for MD Helicopters, Inc. (MDHI) Model 369A, OH-6A, 369D, 369E,
369F, 369FF, 369H, 369HE, 369HM, and 369HS helicopters. The proposed AD
would require repetitive tap inspections of each tail rotor (T/R) blade
abrasion strip. This proposal is prompted by an incident in which an
abrasion strip separated from a T/R blade. The actions specified by the
proposed AD are intended to prevent disbonding and subsequent
separation of an abrasion strip from a T/R blade, which could result in
vibration, loss of the T/R, and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before May 12, 2008.
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 Helicopter Technology Company, LLC (HTC) service
information identified in this proposed AD from, HTC, 12902 South
Broadway, Los Angeles, California, 90061, telephone (310) 523-2750, fax
(310) 523-2745, or on the Internet at http://www.helicoptertech.com.
The service information referenced in Note 2 of this proposed AD may be
obtained from MD Helicopters Inc., Attn: Customer Support Division,
4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734,
telephone (800) 388-3378, fax (480) 346-6813, or on the Internet at
http://www.mdhelicopters.com.
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: John Cecil, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5228, fax (562) 627-5210.
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-2008-0287,
Directorate Identifier 2006-SW-15-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 the 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 MDHI Model 369A, OH-
6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, and 369HS helicopters,
with any of the following T/R blades installed:
HTC part number (P/N) 500P3100-101 and -103, or MDHI P/N
369D21640-501, -503, and -505.
HTC P/N 500P3100-301 and -303, or MDHI P/N 369D21641-501,
-503, and -505.
HTC P/N 500P3300-501 and -503, or MDHI P/N 369D21643-501,
-503, and -505.
HTC P/N 500P3500-701 and -703, or MDHI P/N 369D21642-501,
-503, and -505.
Note: An ``M'' or an ``I'' painted on the root of the T/R blade
indicates compliance to an Alternate Method of Compliance (AMOC) to
AD 2003-08-51, (Docket No. 2003-SW-17-AD, Amendment 39-13215 (68 FR
39449, July 2, 2008), corrected at 68 FR 47447, August 11, 2003,
issued by the FAA, Los Angeles Aircraft Certification Office (LAACO)
on June 13, 2003 to HTC. The AMOC addressed shot peening of the
pitch horn of the T/R assembly.
The proposed AD would require, within 25 hours time-in-service
(TIS), and thereafter at intervals not to exceed 25 hours TIS, tap
inspections of the upper and lower surfaces of each T/R blade abrasion
strip using a coin (United States 25-cent piece or equivalent), or a
small brass, mild steel, or aluminum hammer, to detect bonding voids
that exceed 0.2 square inch in size with a minimum of 1.0 inch between
voids, at least 75 percent of the bonded area of the abrasion strip
being free from voids, and no voids at the edge of the abrasion strip.
Modifying each T/R blade in accordance with FAA-approved data by
installing a titanium rivet in the tip of the outboard end of each T/R
blade and painting a ``T'' in the root-end of the T/R blade would be
considered terminating action for the AD. This proposal is prompted by
an incident in which an abrasion strip separated from a T/R blade
during flight. The actions specified by the proposed AD are intended to
prevent disbonding and subsequent separation of an abrasion strip from
a T/R blade, which could result in vibration, loss of the T/R, and
subsequent loss of control of the helicopter.
We have reviewed the following service information:
HTC Mandatory SB Notice No. 3100-4R4, dated May 10, 2006,
which describes procedures for periodic inspection of the abrasion
strip-to-skin bond integrity on each T/R blade, and modifying each T/R
blade by installing a titanium rivet, P/N 500P3124-13, in the tip of
the T/R blade, and painting a ``T'' in the root-end of the T/R blade in
accordance with applicable engineering drawings or standard repair
instructions; and
MD Helicopters Service Bulletin SB369D-203R1, SB369E-
097R1, SB369F-082R1, and SB369H-246R1, dated January 23, 2006, which
describes procedures for periodic inspections of the T/R abrasion
strip-to-skin bond integrity and modification of the T/R blade by HTC
to install a titanium rivet in the tip of the T/R blade.
This unsafe condition is likely to exist or develop on other
helicopters of the same type designs. Therefore, the proposed AD would
require, within 25 hours TIS, unless accomplished previously, and
thereafter at intervals
[[Page 13517]]
not to exceed 25 hours TIS, tap inspections of the upper and lower
surfaces of each T/R blade abrasion strip using a coin (United States
25 cent piece or equivalent) or a small brass, mild steel, or aluminum
hammer, to detect bonding voids in accordance with Part 1--Inspection
of the HTC Mandatory Service Bulletin Notice No. 3100-4R4, dated May
10, 2006. Modifying each T/R blade by installing a titanium rivet, P/N
500P3124-13, in the tip of the T/R blade and painting a ``T'' in the
root-end of the T/R blade would be a terminating action for this AD.
The actions would be required to be accomplished by following the
specified portions of the HTC service bulletin described previously.
We estimate that this proposed AD would affect 718 helicopters of
U.S. registry.
If operators conduct the repetitive inspections required
by this AD instead of modifying their T/R blades by installing a
titanium rivet, the estimated costs per year would be $229,760 per
year, assuming:
24 inspections per year per helicopter (600 hours TIS per
25 hour TIS inspection), * Labor of 5 minutes per T/R blade (10 minutes
(\1/6\ hour) per helicopter), and
An average labor rate of $80 per work hour.
If operators elect to implement the terminating action by
installing a titanium rivet in each T/R blade, the estimated total cost
would be $244,120, assuming:
The cost of removing, reinstalling, and balancing the 2-T/
R blade set for the entire fleet would be $114,880, assuming that it
would take 2 work hours per helicopter to perform these actions at an
average labor rate of $80 per work hour, and
The cost of installing the rivet in each T/R blade in the
fleet would be $129,240, which includes the cost of $10 per rivet ($20
per helicopter), 1 work hour per T/R blade (2 work hours per
helicopter) to install a rivet, at an average labor rate of $80 per
work hour.
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 Procedures (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 Regulatory 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 develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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:
MD Helicopters, Inc. (MDHI): Docket No. FAA-2008-0287; Directorate
Identifier 2006-SW-15-AD.
Applicability
Model 369A, OH-6A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM,
and 369HS, certificated in any category, with a tail rotor (T/R)
blade installed as follows including all serial numbers and those T/
R blades with an ``M'' or an ``I'' painted on the T/R blade root:
Helicopter Technology Company, LLC (HTC) part number
(P/N) 500P3100-101 and -103, or MDHI P/N 369D21640-501, -503, and -
505.
HTC P/N 500P3100-301 and -303, or MDHI P/N 369D21641-
501, -503, and -505.
HTC P/N 500P3300-501 and -503, or MDHI P/N 369D21643-
501, -503, and -505.
HTC P/N 500P3500-701 and -703, or MDHI P/N 369D21642-
501, -503, and -505.
Note 1: An ``M'' or an ``I'' painted on the root of the T/R
blade indicates compliance to an Alternate Method of Compliance
(AMOC) to Emergency AD 2003-08-51 (Docket No. 2003-SW-17-AD,
Amendment 39-13215, April 15, 2003), issued by the FAA, Los Angeles
Aircraft Certification Office (LAACO) on June 13, 2003 to HTC. The
AMOC addressed shot peening of the pitch horn of the T/R assembly.
Compliance
Required as indicated.
To prevent disbonding and subsequent separation of an abrasion
strip from a T/R blade, which could result in vibration, loss of the
T/R, and subsequent loss of control of the helicopter, accomplish
the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished
previously, and thereafter at intervals not to exceed 25 hours TIS,
inspect the abrasion strip-to-skin bond integrity on each T/R blade
using a tap test method in accordance with Part 1--Inspection, in
Helicopter Technology Company, LLC (HTC) Mandatory Service Bulletin
Notice No. 3100-4R4, dated May 10, 2006 (SB).
Note 2: MD Helicopters Service Bulletin SB369D-203R1, SB369E-
097R1, SB369F-082R1, and SB369H-246R1, dated January 23, 2006,
pertain to the subject of this AD.
(b) Modifying each T/R blade in accordance with FAA-approved
data by installing a titanium rivet at the outboard end and painting
the letter ``T'' on the root-end of the T/R blade to indicate the
modification has been accomplished is considered a terminating
action for the requirements of this AD.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Los Angeles Aircraft Certification Office, FAA,
ATTN: John Cecil, Aviation Safety Engineer, 3960 Paramount Blvd.,
Lakewood, California 90712-4137, telephone (562) 627-5228, fax (562)
627-5210, for information about previously approved alternative
methods of compliance.
(d) Special flight permits will not be issued.
[[Page 13518]]
Issued in Fort Worth, Texas, on March 4, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-5068 Filed 3-12-08; 8:45 am]
BILLING CODE 4910-13-P