[Federal Register Volume 72, Number 146 (Tuesday, July 31, 2007)]
[Rules and Regulations]
[Pages 41615-41618]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 07-3711]


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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:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
    <bullet> 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;
    <bullet> Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
    <bullet> 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
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
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.
------------------------------------------------------------------------

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:
    <bullet> Within the next 5 hours TIS or within 30 days, whichever 
occurs first, if the retention pin has 545 or more hours TIS, or
    <bullet> 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
    <bullet> Determining the S/N of all retention pins (3 on each 
helicopter) will take approximately 0.5 work hour;
    <bullet> Determining the hours TIS of three affected retention pins 
will take approximately 1 work hour; and
    <bullet> 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
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
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]
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