[Federal Register Volume 78, Number 226 (Friday, November 22, 2013)]
[Rules and Regulations]
[Pages 69987-69989]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-27635]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0556; Directorate Identifier 2007-SW-30-AD; 
Amendment 39-17662; AD 2013-23-07]
RIN 2120-AA64


Airworthiness Directives; Erickson Air-Crane Incorporated 
Helicopters (Type Certificate Previously Held by Sikorsky Aircraft 
Corporation)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 90-26-12 for 
Sikorsky Aircraft Corporation (Sikorsky) Model S-64E helicopters. AD 
90-26-12 required checks of the main rotor blades for a crack. This new 
AD retains the actions required by AD 90-26-12, reflects that the type 
certificate (TC) for this model helicopter has been transferred to 
Erickson Air-Crane Incorporated (Erickson), and expands the 
applicability to include the similar Erickson Model S-64F helicopters. 
This AD is prompted by a need to expand the applicability to include 
Model S-64F helicopters and clarify the applicable main rotor blades by 
part number. These actions are intended to detect a crack in the main 
rotor blade and prevent blade separation and subsequent loss of control 
of the helicopter.

DATES: This AD is effective December 27, 2013.

[[Page 69988]]


ADDRESSES: For service information identified in this AD, contact 
Erickson Air-Crane Incorporated, ATTN: Chris Erickson, Director of 
Regulatory Compliance, 3100 Willow Springs Rd., P.O. Box 3247, Central 
Point, OR 97502; telephone (541) 664-5544; fax (541) 664-2312; email 
[email protected]. 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.

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, 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: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 90-26-12, Amendment 39-6841 (55 FR 51406, 
December 14, 1990) (AD 90-26-12), which applied to Sikorsky Model S-64E 
helicopters. The NPRM published in the Federal Register on July 3, 2013 
(78 FR 40063). Since we issued AD 90-26-12, cracks were detected on the 
main rotor blades of Model S-64F helicopters, which are are similar to 
the main rotor blades used on the Model S-64E helicopter. Also, on 
February 13, 1992, Sikorsky transferred TC H6EA for Model S 64E and S 
64F helicopters to Erickson. We also determined that the primary 
temperatures listed in the Required Actions section of this AD should 
be converted from degrees Celsius to degrees Fahrenheit for increased 
clarity.
    As a result, the NPRM proposed to retain the same checks and 
procedures as those required by AD 90-26-12, but in a revised format to 
meet current publication requirements and to expand the applicability 
to include both the Erickson S-64E and S-64F helicopters. The NPRM also 
proposed to require recurring checks of the Blade Inspection Method 
(BIM) indicator on each blade to determine whether the BIM indicator is 
signifying that the blade pressure may have been compromised by a blade 
crack.

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 40063, 
July 3, 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

    Erickson issued Service Bulletin (SB) No. 64F15-2, Revision A, 
dated July 14, 1999, for the Model S-64F and SB No. 64B15-4, Revision 
5, dated September 17, 2013, for the Model S-64E. Erickson released 
both service bulletins to provide operation and check procedures for 
BIM blades installed on the Model S-64E and S-64F helicopters. Several 
blade spars with a crack emanating from corrosion pits and other damage 
have been found because of BIM pressure indications. The checks in SB 
No. 64F15-2 for the Model S-64F are the same as those required by AD 
90-26-12 for the Model S-64E helicopters.

Costs of Compliance

    We estimate that this AD affects 27 helicopters of U.S. Registry. 
We estimate that operators will incur the following costs in order to 
comply with this AD. Each visual BIM pressure indicator color check 
will take about 0.1 work-hour at an average labor rate of $85 per work-
hour. Based on these figures, each visual BIM pressure indicator color 
check will cost about $9 per helicopter or $230 for the fleet. Each BIM 
pressure indicator function check will take about 0.25 work-hour, and 
cost about $21, or $574 for the fleet.
    If a main rotor blade must be replaced, it will take about 2 work-
hours and required parts cost about $125,000. Based on these figures, 
it will cost about $125,170 per helicopter to replace a main rotor 
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 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.

[[Page 69989]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
90-26-12, Amendment 39-6841 (55 FR 51406, December 14, 1990), and 
adding the following new AD:

2013-23-07 Erickson Air-Crane Incorporated (Type Certificate 
Previously Held By Sikorsky Aircraft Corporation): Amendment 39-
17662; Docket No. FAA-2013-0556; Directorate Identifier 2007-SW-30-
AD.

(a) Applicability

    This AD applies to Erickson Air-Crane Incorporated (Erickson) 
Model S-64E and S-64F helicopters, with rotary wing blade assembly 
(main rotor blade), part number 6415-20201-043, -045, -047, -048, -
049, -050, or -051; or 6415-20601-041, -042, -043, -044, -045, -046, 
-047, -048, -049, -050, -051, or -052, installed, certificated in 
any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the main 
rotor blade (blade), which could result in blade separation and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 90-26-12, Docket No. 90-ASW-27, Amendment 
39-6841 (55 FR 51406, December 14, 1990).

(d) Effective Date

    This AD becomes effective December 27, 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, visually check the Blade Inspection 
Method (BIM) pressure indicators of the main rotor blades for a 
black or red color indication.
    (2) Before further flight, replace any blade with a black or red 
color indication in a BIM pressure indicator with an airworthy part 
of the same part number unless the black or red color indication is 
determined to be the result of BIM system malfunction.

    Note 1 to paragraph (f)(2) of this AD:  Paragraphs (f)(4)(i-iv) 
of this AD specify how to determine if a BIM system is functioning 
correctly.

    (3) Repeat the visual BIM pressure indicator check required by 
paragraph (f)(1) of this AD prior to the first flight of each day 
and thereafter at intervals not to exceed:
    (i) Three hours time-in-service (TIS) from the last check for 
helicopters engaged in seven or more external lifts per hour; or
    (ii) Five hours TIS from the last check for helicopters engaged 
in either less than seven external lifts per hour or operation 
without external cargo.
    (4) Prior to the first flight of each day, check the BIM 
pressure indicator for proper function as follows:
    (i) Press in and hold the manual test lever (grenade-type 
handle) on the raised area of the handle over the pin-type actuation 
plunger. Do not handle the indicator glass bulb since the heat of 
the hand may change the internal reference pressure and result in an 
erroneous indicator reading.
    (ii) Depress the actuation plunger fully to shut off the 
pressure completely from the blade into the indicator. If necessary, 
press with the thumbs of both hands to overcome the plunger spring 
force.

    Note 2 to paragraph (f)(4)(ii) of this AD:  If pressure is 
applied to the end of the lever on the flat area, the actuation 
plunger will not fully depress.

    (iii) Verify proper operation of the indicator by observing that 
a full-black or full-red (unsafe) indication appears in not less 
than 10 or more than 30 seconds after depressing the plunger for a 
temperature of 20 degrees F (-6.7 degrees C) or above. At lower 
temperatures, extend the upper limit to the corresponding time as 
follows:
    (A) 19 to 0 degrees F (-7.2 to -17.8 degrees C); upper limit of 
35 seconds.
    (B) -1 to -20 degrees F (-18.3 to -28.9 degrees C); upper limit 
of 40 seconds.
    (C) -21 to -40 degrees F (-29.4 to -40.0 degrees C); upper limit 
of 50 seconds.
    (D) -41 to -60 degrees F (-40.5 to -51.1 degrees C); upper limit 
of 60 seconds.
    (iv) Release the lever and observe that the black or red 
indication snaps back immediately, leaving an all-white or all-
yellow (safe) indication.
    (v) If the indicator does not meet the specified requirements, 
then either identify and correct the BIM indicator malfunction or 
replace the suspect main rotor blade with an airworthy blade of the 
same part number prior to further flight.
    (5) The checks required by paragraphs (f)(1) and (f)(4)(i-iv) of 
this AD may be performed by the owner/operator (pilot) holding at 
least a private pilot certificate, and must be entered into the 
aircraft records showing compliance with this AD in accordance with 
14 CFR Sec. Sec.  43.9(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The 
record must be maintained as required by 14 CFR Sec. Sec.  91.417, 
121.380, or 135.439.

(g) Special Flight Permits

    Special flight permits will not be issued.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Kohner, 
Aviation Safety Engineer, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 
76137; telephone (817) 222-5170; email [email protected].
    (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.

(i) Additional Information

    Erickson Air-Crane Incorporated Service Bulletins No. 64B15-4, 
Revision 5, dated September 17, 2013 for the Model S-64E and No. 
64F15-2, Revision A, dated July 14, 1999 for the Model S-64F, which 
are not incorporated by reference, contain additional information 
about the subject of this AD. For service information identified in 
this AD, contact Erickson Air-Crane Incorporated, ATTN: Chris 
Erickson, Director of Regulatory Compliance, 3100 Willow Springs Rd, 
P.O. Box 3247, Central Point, OR 97502; telephone (541) 664-5544; 
fax (541) 664-2312; email [email protected]. 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.

(j) Subject

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

    Issued in Fort Worth, Texas, on October 30, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-27635 Filed 11-21-13; 8:45 am]
BILLING CODE 4910-13-P