[Federal Register: July 31, 2007 (Volume 72, Number 146)]
[Rules and Regulations]
[Page 41615-41618]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31jy07-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28813; Directorate Identifier 2007-SW-09-AD;
Amendment 39-15140; AD 2007-16-01]
RIN 2120-AA64
Airworthiness Directives; Enstrom Helicopter Corporation Model F-
28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F,
280FX, TH-28, 480, and 480B Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Enstrom Helicopter Corporation (Enstrom) Model F-28, F-28A, F-28C, F-
28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480,
and 480B helicopters. This action requires a visual check to determine
if a certain serial-numbered main rotor blade retention pin (retention
pin) is installed, and removing and replacing any affected retention
pin with an airworthy retention pin. This amendment is prompted by a
report from the manufacturer that some retention pins were not
manufactured in accordance with specifications cited on the engineering
drawing. The actions specified in this AD are intended to prevent
failure of a retention pin, separation of a main rotor blade from the
helicopter, and subsequent loss of control of the helicopter.
DATES: Effective August 15, 2007.
[[Page 41616]]
Comments for inclusion in the Rules Docket must be received on or
before October 1, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically;
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: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
Fax: 202-493-2251.
You may get the service information identified in this AD from
Enstrom Helicopter Corporation, 2209 22nd Street, P.O. Box 490,
Menominee, Michigan 49858-0490.
Examining the Docket: You may examine the docket that contains the AD,
any comments, and other information on the Internet at http://dms.dot.gov
, or 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 the DMS receives them.
FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Senior Aerospace
Engineer, FAA, Small Airplane Directorate, Chicago Aircraft
Certification Office, 2300 E. Devon Ave., Room 107, Des Plaines,
Illinois 60018, telephone (847) 298-7135, fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Enstrom
Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-28F, F-28F-R, 280, 280C,
280F, 280FX, TH-28, 480, and 480B helicopters with a retention pin,
part number (P/N) 28-14007-3, installed, with a serial number (S/N)
that is listed in the following table:
Retention Pin S/N
------------------------------------------------------------------------
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04098-01 through 04098-56.
05018-01 through 05018-36.
05143-01 through 05143-56.
05341-1 through 05341-8.
05341-10 through 05341-17.
05341-19.
05341-21 through 05341-33.
05341-35 through 05341-42.
05341-44 through 05341-59.
05341-61.
05341-62.
05341-64 through 05341-71.
06214-3 through 06214-14.
06214-16 through 06214-23.
06214-25 through 06214-29.
06214-31.
06214-33 through 06214-35.
06214-37 through 06214-57.
06214-59 through 06214-68.
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This action requires, before further flight, visually checking each
retention pin to determine if the S/N, which is marked on the head of
the retention pin, is listed in the Applicability section of this AD.
If there is no serial number marked on the head of the retention pin
(i.e., the retention pin head is blank), the retention pin does not
need to be replaced and this visual check constitutes a terminating
action for the requirements of this AD for that retention pin. If an
affected retention pin is installed, determining the retention pin's
number of hours time-in-service (TIS) and removing and replacing it
with an airworthy retention pin that has a S/N that is not listed in
the Applicability section of this AD is required:
Within the next 5 hours TIS or within 30 days, whichever
occurs first, if the retention pin has 545 or more hours TIS, or
On or before reaching 550 hours TIS or within 30 days,
whichever occurs first, if the retention pin has less than 545 hours
TIS.
This amendment is prompted by a report from the manufacturer that some
retention pins were manufactured from steel that did not meet the
specifications cited on the engineering drawing. The actions specified
in this AD are intended to prevent failure of a retention pin,
separation of a main rotor blade from the helicopter, and subsequent
loss of control of the helicopter.
We have reviewed Enstrom Helicopter Corporation Service Directive
Bulletin (SDB) No. 0102 and Enstrom Helicopter Corporation SDB No. T-
029, both dated March 20, 2007, which specify visual and magnetic
particle inspections for cracks in certain serial-numbered retention
pins, and repairing or replacing retention pins in accordance with
certain inspection criteria. This AD does not require inspections for
cracks but requires that each affected retention pin be replaced.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, this AD is being issued
to prevent failure of a retention pin, separation of a main rotor blade
from the helicopter, and subsequent loss of control of the helicopter.
This AD requires removing and replacing certain serial-numbered
retention pins. The visual check required by this AD may be performed
by an owner/operator (pilot), but must be entered into the aircraft
records showing compliance with paragraph (a) of this AD in accordance
with 14 CFR 43.11 and 91.417(a)(2)(v). This AD allows a pilot to
perform this check because it involves only a visual check of the head
of each retention pin to determine the S/N.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability and structural integrity of the helicopter. Therefore,
removing and replacing each affected retention pin is required within 5
hours TIS or within 30 days, depending on the retention pin's hours
TIS, which constitutes a very short time period, and this AD must be
issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
We estimate that this AD will affect 39 helicopters, and
Determining the S/N of all retention pins (3 on each
helicopter) will take approximately 0.5 work hour;
Determining the hours TIS of three affected retention pins
will take approximately 1 work hour; and
Removing and replacing three retention pins will take
approximately 3 work hours at an average labor rate of $80 per work
hour. Required parts will cost approximately $680 per helicopter. Based
on these figures, we estimate the total cost impact of the AD on U.S.
operators to be $1,040 per helicopter or $40,560 if all retention pins
get replaced on the entire fleet.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2007-28813;
Directorate Identifier 2007-SW-09-AD''
[[Page 41617]]
at the beginning of your comments. We specifically invite comments on
the overall regulatory, economic, environmental, and energy aspects of
the AD. We will consider all comments received by the closing date and
may amend the AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. 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 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), or you may visit http://dms.dot.gov
.
Regulatory Findings
We have determined that 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 the 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 an economic evaluation of the estimated costs to comply
with this AD. See the DMS to examine the 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.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2007-16-01 Enstrom Helicopter Corporation: Amendment 39-15140.
Docket No. FAA-2007-28813; Directorate Identifier 2007-SW-09-AD.
Applicability: Model F-28, F-28A, F-28C, F-28C-2, F-28C-2R, F-
28F, F-28F-R, 280, 280C, 280F, 280FX, TH-28, 480, and 480B
helicopters, with a main rotor blade retention pin (retention pin)
having a serial number (S/N) that is listed in the following table,
installed, certificated in any category:
Retention Pin S/N
------------------------------------------------------------------------
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04098-01 through 04098-56.
05018-01 through 05018-36.
05143-01 through 05143-56.
05341-1 through 05341-8.
05341-10 through 05341-17.
05341-19.
05341-21 through 05341-33.
05341-35 through 05341-42.
05341-44 through 05341-59.
05341-61.
05341-62.
05341-64 through 05341-71.
06214-3 through 06214-14.
06214-16 through 06214-23.
06214-25 through 06214-29.
06214-31.
06214-33 through 06214-35.
06214-37 through 06214-57.
06214-59 through 06214-68.
------------------------------------------------------------------------
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a retention pin, separation of a main
rotor blade from the helicopter, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Before further flight, check the S/N that is marked on the
head of each retention pin to see if it is a S/N that is listed in
the Applicability section of this AD. See Figure 1 for the location
of the S/N. If there is no serial number marked on the head of the
retention pin (i.e., the retention pin head is blank), the retention
pin does not need to be replaced and this determination constitutes
a terminating action for the requirements of this AD for that
retention pin.
[[Page 41618]]
[GRAPHIC] [TIFF OMITTED] TR31JY07.016
(b) The visual check required by paragraph (a) of this AD may be
performed by an owner/operator (pilot) holding at least a private
pilot certificate, and must be entered into the aircraft records
showing compliance with paragraph (a) of this AD in accordance with
14 CFR sections 43.11 and 91.417(a)(2)(v).
(c) Determine the number of hours TIS for any affected retention
pin and replace the retention pin with an airworthy retention pin as
follows:
(1) For a retention pin with 545 or more hours TIS, remove the
retention pin and replace it with an airworthy retention pin with a
S/N that is not listed in the Applicability section of this AD
within the next 5 hours TIS or within 30 days, whichever occurs
first.
(2) For a retention pin with less than 545 hours TIS, remove the
retention pin and replace it with an airworthy retention pin with a
S/N that is not listed in the Applicability section of this AD on or
before reaching 550 hours TIS or within 30 days, whichever occurs
first.
Note: Enstrom Service Directive Bulletin No. T-029 and Enstrom
Service Directive Bulletin 0102, both dated March 20, 2007, pertain
to the subject of this AD.
(d) Removing any affected retention pin and replacing it with an
airworthy retention pin that is not included in the Applicability
section of this AD is considered a terminating action for the
requirements of this AD for that retention pin.
(e) 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, Chicago Aircraft Certification Office, FAA,
ATTN: Gregory J. Michalik, Senior Aerospace Engineer, 2300 E. Devon
Ave., Room 107, Des Plaines, Illinois, 60018, telephone (847) 298-
7135, fax (847) 294-7834, for information about previously approved
alternative methods of compliance.
(f) This amendment becomes effective on August 15, 2007.
Issued in Fort Worth, Texas, on July 24, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 07-3711 Filed 7-30-07; 8:45 am]
BILLING CODE 4910-13-P