
[Federal Register Volume 74, Number 94 (Monday, May 18, 2009)]
[Proposed Rules]
[Pages 23131-23133]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-11478]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0545; Directorate Identifier 2008-NE-16-AD]
RIN 2120-AA64


Airworthiness Directives; Dowty Propellers Models R354/4-123-F/
13, R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26, 
and R390/4-123-F/27 Propellers

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
the comment period.

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SUMMARY: This supplemental NPRM revises an earlier proposed 
airworthiness directive (AD), applicable to Dowty Propellers Models 
R354/4-123-F/13, R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25, 
R389/4-123-F/26, and R390/4-123-F/27 propellers. That proposed AD would 
have required initial and repetitive visual inspections of propeller 
blade root outer sleeves for cracks, and removal before further flight 
of propeller blades with cracked blade root outer sleeves. That 
proposed AD resulted from mandatory continuing airworthiness 
information (MCAI) issued by the European Aviation Safety Agency (EASA) 
to identify and correct an unsafe condition on certain Dowty 
propellers. This supplemental NPRM revises the proposed AD to correct 
the listing of propeller models affected. This supplemental NPRM 
results from the discovery that we need to correct one of the propeller 
model numbers affected, and to remove an erroneous propeller model 
number. We are proposing this AD to prevent blade counterweight 
release, which could result in injury or damage to the airplane. The 
MCAI describes the unsafe condition as:

    A number of propeller blade outer sleeves have been found with 
cracks since 1996. Testing has shown that blade retention integrity 
is not affected by this cracking. However, this condition, if not 
detected and corrected, can lead to blade counterweight release, 
possibly resulting in damage to the aircraft and injury to occupants 
or persons on the ground.

    We are proposing this AD to prevent blade counterweight release, 
which could result in injury or damage to the airplane.

DATES: We must receive comments on this proposed AD by June 17, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston 
Aircraft Certification Office, FAA, Engine and Propeller Directorate, 
12 New England Executive Park, Burlington, MA 01803; e-mail: 
terrance.fahr@faa.gov; telephone (781) 238-7155; fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0545; 
Directorate Identifier 2008-NE-16-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD 2008-0033, dated February 19, 
2008, to correct an unsafe condition for the specified products. The 
EASA AD states:

    A number of propeller blade outer sleeves have been found with 
cracks since 1996. Testing has shown that blade retention integrity 
is not affected by this cracking. However, this condition, if not 
detected and corrected, can lead to blade counterweight release, 
possibly resulting in damage to the

[[Page 23132]]

aircraft and injury to occupants or persons on the ground.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Dowty Propellers has issued Alert Service Bulletin No. SF340-61-
A106, Revision 1, dated March 20, 2008. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of the 
United Kingdom, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the United Kingdom, they have 
notified us of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design. This Supplemental NPRM requires initial and 
repetitive visual inspections of propeller blade root outer sleeves for 
cracks, and removal before further flight of propeller blades with 
cracked blade root outer sleeves.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received on the original NPRM.

Request To Reference the Latest Service Bulletin

    One commenter, Colgan Air, requests that we reference the latest 
service bulletin, which is Dowty Propellers Alert Service Bulletin No. 
SF340-61-A106, Revision 1, dated March 20, 2008.
    We agree and changed that reference in this Supplemental NPRM.

Request To Clarify Airplane Manufacturer

    One commenter, SAAB AB, SAAB Aerosystems, requests that we clarify 
that ``340B airplanes'' should be referred to as ``SAAB 340B 
airplanes''.
    We agree and clarified that reference in this Supplemental NPRM.

Need To Correct the Listing of Propeller Models Affected

    We discovered the need to correct the listing of the propeller 
models affected that was included in the original NPRM published in the 
Federal Register on June 30, 2008 (73 FR 36819). That listing, which is 
Dowty Propellers models R354/4-123-F/13, R354/4-123-F/20, R354/4-123-F/
21, R375/4-123-F/21, R389/4-123-F/25, R354/4-123-F/26, and R390/4-123-
F/27 propellers, is changed in this Supplemental NPRM to Dowty 
Propellers Models R354/4-123-F/13, R354/4-123-F/20, R375/4-123-F/21, 
R389/4-123-F/25, R389/4-123-F/26, and R390/4-123-F/27 propellers.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require making 
the changes described previously. We determined that these changes will 
not increase the economic burden on any operator or increase the scope 
of the Supplemental NPRM.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 292 propellers installed on airplanes of U.S. 
registry. We also estimate that it would take 0.5 work-hour per 
propeller to visually inspect for cracks. The average labor rate is $80 
per work hour. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $11,680.

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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. 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 this 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new AD:

Dowty Propellers: Docket No. FAA-2008-0545; Directorate Identifier 
2008-NE-16-AD.

Comments Due Date

    (a) We must receive comments by June 17, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Dowty Propellers Models R354/4-123-F/13, 
R354/4-123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26, 
and R390/4-123-F/27 propellers. These propellers are installed on, 
but not limited to, Saab AB, Saab Aerosystems SF340A and SAAB SF340B 
airplanes.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2008-0033, 
dated February 19, 2008, states:
    A number of propeller blade outer sleeves have been found with 
cracks since 1996. Testing has shown that blade retention integrity 
is not affected by this cracking. However, this condition, if not 
detected and corrected, can lead to blade counterweight release, 
possibly resulting in damage to the aircraft and injury to occupants 
or persons on the ground.


[[Page 23133]]


    This AD requires initial and repetitive visual inspections of 
propeller blade root outer sleeves for cracks, and removal before 
further flight of propeller blades with cracked blade root outer 
sleeves. We are issuing this AD to prevent blade counterweight 
release, which could result in injury or damage to the airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.

Propeller Blade Root Outer Sleeve Visual Inspections

    (1) At the next 1,600 flight hours (FH) aircraft check after the 
effective date of this AD, or, after any blade accumulates 15,000 FH 
time-in-service, whichever occurs later, visually inspect all 
propeller blade root outer sleeves for cracks.
    (2) Thereafter, at intervals not to exceed 1,600 FH, visually 
inspect all propeller blade root outer sleeves for cracks.
    (3) Before further flight, remove any propeller blades found 
with cracked root outer sleeves during the visual inspections in 
paragraphs (e)(1) and (e)(2) of this AD.

FAA AD Differences

    (f) None.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Boston Aircraft Certification Office, FAA, 
Engine and Propeller Directorate, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (h) Refer to European Aviation Safety Agency AD 2008-0033, dated 
February 19, 2008, and Dowty Propellers Alert Service Bulletin No. 
SF340-61-A106, Revision 1, dated March 20, 2008, for related 
information.
    (i) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
terry.fahr@faa.gov; telephone (781) 238-7155; fax (781) 238-7170, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on May 8, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-11478 Filed 5-15-09; 8:45 am]
BILLING CODE 4910-13-P


