Document ID: FAA-2013-0401-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: MD Helicopters, Inc., Helicopters
Posted Date: 2013-10-31T04:00Z

[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65180-65183]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24039]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0401; Directorate Identifier 2012-SW-047-AD; 
Amendment 39-17606; AD 2013-19-24]
RIN 2120-AA64

Airworthiness Directives; MD Helicopters, Inc., Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2003-08-51 for 
MD Helicopters, Inc. (MDHI), Model 369A, 369D, 369E, 369H, 369HE, 
369HM, 369HS, 369F and 369FF helicopters with certain MDHI or 
Helicopter Technology Company (HTC) tail rotor blades installed. AD 
2003-08-51 required reducing the retirement life of each tail rotor 
blade (blade), performing a one-time visual inspection of each blade's 
pitch horn (pitch horn) for a crack or corrosion, and replacing any 
cracked blade or any blade that has exceeded its retirement life with 
an

[[Page 65181]]

airworthy blade. AD 2003-08-51 also required reporting information to 
the FAA within 24 hours following the one-time inspection. Since we 
issued AD 2003-08-51, an accident in England prompted an investigation 
that showed corrosion on the blade's pitch horn that had not been 
detected under the paint. This new AD retains some of the requirements 
of AD 2003-08-51 and also requires paint removal for all pitch horn 
inspections, inspecting for pitting and the shot peen surface's 
condition in addition to cracks and corrosion, and adds certain part-
numbered blades to the applicability. These actions are intended to 
prevent a pitch horn from cracking, leading to vibration, loss of tail 
rotor pitch control, and subsequent loss of tail rotor and helicopter 
control.

DATES: This AD is effective December 5, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of December 5, 
2013.

ADDRESSES: For service information identified in this AD, contact MD 
Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell 
Rd., Mail Stop M615, Mesa, AZ 85215-9734; telephone 1-800-388-3378; fax 
480-346-6813; email serviceengineering@mdhelicopters.com; Web site 
http://www.mdhelicopters.com or contact Helicopter Technology Company, 
12923 South Spring Street, Los Angeles, CA 90061; telephone 310-523-
2750; email gburdorf@helicoptertech.com; Web site 
www.helicoptertech.com.

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 AD, any incorporated-by-reference 
service information, the economic evaluation, any comments received, 
and other information. The street address for 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: Fred Guerin, Aviation Safety Engineer, 
Los Angeles Aircraft Certification Office, Transport Airplane 
Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; 
telephone (562) 627-5232; email fred.guerin@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 13, 2013, at 78 FR 27867, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 by removing AD No. 2003-08-51 (68 FR 39449, July 2, 2003; 
corrected 68 FR 47447, August 11, 2003) and by adding an AD that would 
apply to MDHI Model 369A, 369D, 369E, 369H, 369HE, 369HM, 369HS, 369F 
and 369FF helicopters with a tail rotor blade (blade) part number (P/N) 
369D21640-501, 369D21640-503, 369D21641-501, 369D21641-503, 369D21642-
501, 369D21642-503, 369D21643-501, or 369D21643-503 installed, or with 
an HTC blade P/N 500P3100-101, 500P3100-301, 500P3300-501, or 500P3500-
701 installed. AD No. 2003-08-51 required reducing the retirement life 
of the blade, performing a one-time visual inspection of each pitch 
horn for a crack or corrosion, and replacing any cracked blade or any 
blade that has exceeded its retirement life. AD No. 2003-08-51 was 
prompted by two reports of cracked pitch horns that failed during 
flight. The cracks developed before the blades reached their retirement 
lives.

Actions Since AD 2003-08-51 Was Issued

    Since we published AD No. 2003-08-51, investigation of an accident 
in England found corrosion on the pitch horn that was not detected 
under the paint. The corrosion compromised the shot peen surface, which 
caused premature fatigue failure.
    As a result, the NPRM (78 FR 27867, May 13, 2013) proposed to 
require establishing a retirement life for new applicable blades of 400 
hours time-in-service (TIS), replacing within 10 hours TIS any 
installed blades with 390 to 700 hours TIS, and replacing before 
further flight any blades with more than 700 hours TIS. Within 60 days 
and thereafter at intervals not to exceed one year, the NPRM proposed 
to inspect all other blades with a 10X or higher power magnifying glass 
for a crack, pitting, corrosion, and the condition of the dimpled shot 
peen surface. If there is a crack, pitting, corrosion, or a 
nonconforming shot peen surface, the NPRM proposed to require 
replacement of the blade with an airworthy blade. The proposed 
requirements were intended to prevent a pitch horn from cracking and 
separating from the blade, leading to an unbalanced condition, 
vibration, loss of tail rotor pitch control, and loss of directional 
control of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (78 FR 27867, 
May 13, 2013).

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

    We reviewed MDHI Service Bulletins SB369D-210, SB369E-105, SB369F-
091, and SB369H-252, all dated November 21, 2011, and HTC Mandatory 
Service Bulletin No. 3100-5, dated August 25, 2011 (service bulletins). 
The service bulletins specify removing the paint from the pitch horn, 
performing an inspection of the blade using a 10x magnifying glass and 
a bright light, repainting the pitch horn area, and repeating the 
inspection annually. The service bulletins state that no corrosion, 
pitting, or cracking is acceptable. The MDHI service bulletins adds 
that a lack, removal, or blending of the shot peen surface is 
unacceptable.

Costs of Compliance

    We estimate that this AD will affect 827 helicopters of U.S. 
Registry and that labor costs will average $85 a work-hour. Based on 
these estimates, we expect the following costs:
     The inspection will require 4.5 work hours, and parts will 
cost $20 for a total cost of about $403 per helicopter and $333,281 for 
the U.S. fleet.
     Replacing a tail rotor blade, if needed, would require 1 
work hour. Parts would cost $15,951, for a total cost of $16,036 per 
helicopter.
     The cost is negligible to revise the Airworthiness 
Limitations section of the maintenance manual to reflect a blade's new 
retirement life.

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

[[Page 65182]]

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 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 removing Airworthiness Directive (AD) 
2003-08-51, Amendment 39-13215 (68 FR 39449, August 11, 2003; 
correction 68 FR 47447, August 11, 2003), and adding the following new 
(AD):

2013-19-24 MD Helicopters, Inc.: Amendment 39-17606; Docket No. FAA-
2013-0401; Directorate Identifier 2012-SW-047-AD.

(a) Applicability

    This AD applies to MD Helicopters, Inc. (MDHI), Model 369A, 
369D, 369E, 369H, 369HE, 369HM, 369HS, 369F and 369FF helicopters 
with a tail rotor blade (blade) part number (P/N) 369D21640-501, 
369D21640-503, 369D21641-501, 369D21641-503, 369D21642-501, 
369D21642-503, 369D21643-501, or 369D21643-503 installed, or with a 
Helicopter Technology Company blade P/N 500P3100-101, 500P3100-301, 
500P3300-501, or 500P3500-701 installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as the tail rotor blade 
pitch horn (pitch horn) separating from the tail rotor blade, 
leading to an unbalanced condition, vibration, loss of tail rotor 
pitch control and loss of directional control of the helicopter.

(c) Affected ADs

    This AD supersedes AD No. 2003-08-51, Amendment 39-13215 (68 FR 
39449, July 2, 2003; correction 68 FR 47447, August 11, 2003).

(d) Effective Date

    This AD becomes effective December 5, 2013.

(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) Before further flight, for each applicable blade, revise the 
Airworthiness Limitations section of the maintenance manual to 
reflect that the blade has a retirement life of 400 hours time-in-
service (TIS).
    (2) For helicopters with an applicable blade installed that has 
390 through 700 hours TIS, within 10 hours TIS, replace the blade 
with an airworthy blade.
    (3) For all other applicable helicopters, within 60 days, and 
thereafter at intervals not to exceed one year, remove the paint 
from the blade pitch control arm in accordance with the 
Accomplishment Instructions, Section 2.A.(1) through 2.A.(3), of 
MDHI Service Bulletins SB369D-210, SB369E-105, SB369F-091, and 
SB369H-252, all dated November 21, 2011, as applicable to your model 
helicopter.
    (i) Using a 10X or higher power magnifying glass, inspect all 
four sides and the pocket of the blade pitch control arm for a 
crack, pitting, or corrosion and for the condition of the dimpled 
shot peen surface by referring to Figure 1 of MDHI Service Bulletins 
SB369D-210, SB369E-105, SB369F-091, and SB369H-252, as applicable to 
your model helicopter, and by reviewing the rotorcraft maintenance 
records to determine whether rework was done in this area.
    (ii) If there is pitting, corrosion, a crack, blending or 
removal of any of the dimpled shot peen surface, or any indication 
that the shot peen has not been done, replace the blade with an 
airworthy blade.
    (iii) If there is no pitting, corrosion, cracks, or blending or 
removal of any of the dimpled shot peen surface, refinish the 
stripped pitch control arm in accordance with the Accomplishment 
Instructions, Section 2.A.(6) through 2.A.(7), of MDHI Service 
Bulletins SB369D-210, SB369E-105, SB369F-091, and SB369H-252, as 
applicable to your model helicopter.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office, FAA, 
may approve AMOCs for this AD. Send your proposal to: Fred Guerin, 
Aviation Safety Engineer, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, 
California 90712; telephone (562) 627-5232; email 
fred.guerin@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.
    (3) AMOCs approved previously in accordance with AD No. 2003-08-
51 (68 FR 39449, July 2, 2003; correction 68 FR 47447, August 11, 
2003) are approved as AMOCs for the corresponding requirements in 
this AD.

(h) Additional Information

    MD Helicopters, Inc., maintenance manuals CSP-HMI2, TR12-001, 
CHP-H-4, and TR12-001, which are not incorporated by reference, 
contain additional information about the subject of this AD. For 
service information identified in this AD, contact MD Helicopters, 
Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail 
Stop M615, Mesa, AZ 85215-9734; telephone 1-800-388-3378; fax 480-
346-6813; email serviceengineering@mdhelicopters.com; Web site 
http://www.mdhelicopters.com or contact Helicopter Technology 
Company, 12923 South Spring Street, Los Angeles, CA 90061; telephone 
310-523-2750; email gburdorf@helicoptertech.com; Web site 
www.helicoptertech.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.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor 
Blades.

(j) 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) MD Helicopters Service Bulletin SB369D-210, dated November 
21, 2011.
    (ii) MD Helicopters Service Bulletin SB369E-105, dated November 
21, 2011.
    (iii) MD Helicopters Service Bulletin SB369F-091, dated November 
21, 2011.

[[Page 65183]]

    (iv) MD Helicopters Service Bulletin SB369H-252, dated November 
21, 2011.
    Note 1 to paragraph (j)(2): MD Helicopters Service Bulletins 
SB369D-210, SB369E-105, SB369F-091, and SB369H-252, all dated 
November 21, 2011, are co-published as one document.
    (3) For MD Helicopters service information identified in this 
AD, contact MD Helicopters, Inc., Attn: Customer Support Division, 
4555 E. McDowell Rd., Mail Stop M615, Mesa, AZ 85215-9734; telephone 
1-800-388-3378; fax 480-346-6813; email 
serviceengineering@mdhelicopters.com; Web site http://www.mdhelicopters.com.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may also 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on September 18, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24039 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P