[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Rules and Regulations]
[Pages 36008-36011]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-12172]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18958; Directorate Identifier 2004-NE-32-AD; 
Amendment 39-14137; AD 2005-13-01]
RIN 2120-AA64


Airworthiness Directives; [Hoffmann Propeller GmbH & Co KG Models 
HO-V343 and HO-V343K Propellers]

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-V343K 
propellers. That AD currently requires initial and repetitive visual 
inspections of propeller blades for blade shake and blade nut preload. 
That AD also requires initial and repetitive eddy current inspections 
of blade hubs for damage and cracks. This AD requires an ultrasonic 
inspection of the propeller hub and an eddy current inspection of the 
propeller hub if any cracks are discovered during ultrasonic 
inspection.

[[Page 36009]]

Additionally, this AD requires sending a hub inspection report to the 
manufacturer. This AD also requires replacement of the propeller if any 
signs of blade shake, cracks, or other damage to the propeller hub 
outside serviceable limits are detected during the inspections. This AD 
results from the discovery of a propeller blade separation due to a 
possible hub failure. We are issuing this AD to prevent propeller hub 
failure and blade separation due to an unknown root cause, leading to 
damage and possible loss of control of the airplane.

DATES: Effective July 7, 2005. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of July 7, 2005.
    We must receive any comments on this AD by August 22, 2005.

ADDRESSES: Use one of the following addresses to comment on this 
proposed 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: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Hoffmann Propeller GmbH & Co KG, K[uuml]pferlingstra[beta]e 
9, D-83022 Rosenheim, Germany, telephone ++49-(0)8031-1878-0; fax ++49-
(0)8031-1878-78 for the service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer, 
Boston Aircraft Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7158; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On August 24, 2004, the FAA issued AD 2004-
18-01, Amendment 39-13778 (69 FR 53603, September 2, 2004). That AD 
requires initial and repetitive visual inspections of propeller blades 
for blade shake and blade nut preload. That AD also requires initial 
and repetitive eddy current inspections of blade hubs for damage and 
cracks. That AD resulted from a report of a blade separating from 
either a model HO-V343 or HO-V343K propeller. That condition, if not 
corrected, could result in propeller hub failure and blade separation 
due to an unknown root cause, leading to damage and possible loss of 
control of the airplane.

Actions Since AD 2004-18-01 Was Issued

    Since that AD was issued, the Luftfahrt-Bundesamt (LBA), which is 
the aviation authority for Germany, notified us that an unsafe 
condition might still exist on Hoffmann propeller models HO-V343 and 
HO-V343K propellers. The LBA advises that another instance of a 
propeller blade separation due to possible hub failure has been 
reported. The root cause of the failure is not known and is still under 
investigation. This AD requires an ultrasonic inspection of the 
propeller hub and eddy current inspection of the propeller hub if any 
cracks are discovered during ultrasonic inspection. Additionally, this 
AD requires sending a hub inspection report to the manufacturer. This 
AD also requires replacement of the propeller if any signs of blade 
shake, cracks, or other damage to the propeller hub outside serviceable 
limits are detected during the inspections. We certificated these 
propellers for use in the U.S. in 1997 and it is possible that some 
U.S. airplanes have acquired sufficient service hours for the 
propellers to be subject to the failure mode. We are issuing this AD to 
prevent propeller hub failure and blade separation due to an unknown 
root cause, leading to damage and possible loss of control of the 
airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of Hoffmann 
Propeller GmbH & Co KG Service Instruction (SI) No. 61-10-05 SI E 4D, 
dated March 16, 2005. This SI describes procedures for initial and 
repetitive visual inspections of propeller blades for blade shake, 
blade nut preload, and inspection of blade retaining threads for 
cracks. This service instruction also describes procedures for initial 
and repetitive ultrasonic and eddy current inspections of blade hubs 
for damage or cracks. The LBA classified this service instruction as 
mandatory and issued AD D-2004-352R4 in order to ensure the 
airworthiness of these Hoffmann Propeller GmbH & Co KG propellers in 
Germany.

Bilateral Airworthiness Agreement

    This propeller model is manufactured in Germany and is type 
certificated for operation in the United States under the provisions of 
Sec.  21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Under this bilateral 
airworthiness agreement, the LBA has kept the FAA informed of the 
situation described above. We have examined the findings of the LBA, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Hoffmann Propeller GmbH & Co KG Models HO-V343 and HO-
V343K propellers of the same type design. We are issuing this AD to 
prevent propeller hub failure and blade separation due to an unknown 
root cause, leading to damage and possible loss of control of the 
airplane.
    This AD requires initial and repetitive visual inspections of 
propeller blades for blade shake and blade nut preload. This AD also 
requires an ultrasonic inspection of the propeller hub and an eddy 
current inspection of the propeller hub if any cracks are discovered 
during ultrasonic inspection. Additionally, this AD requires sending a 
hub inspection report to the manufacturer. This AD also requires 
replacement of the propeller if any signs of blade shake, cracks, or 
other damage to the propeller hub outside serviceable limits are 
detected during the inspections. You must use the service information 
described previously to perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or

[[Page 36010]]

arguments regarding this AD. Send your comments to an address listed 
under ADDRESSES. Include ``AD Docket No. FAA-2004-18958; Directorate 
Identifier 2004-NE-32-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the rule that might suggest a need 
to modify it.
    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 the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including 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) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the DMS receives them.

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 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 a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2004-NE-32-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under 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. The FAA amends Sec.  39.13 by removing Amendment 39-13778 (69 FR 
53603, September 2, 2004), and by adding a new airworthiness directive, 
Amendment 39-14137, to read as follows:

2005-13-01 Hoffmann Propeller GmbH & Co KG: Amendment 39-14137. 
Docket No. FAA-2004-18958; Directorate Identifier 2004-E-32-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 7, 
2005.

Affected ADs

    (b) This AD supersedes AD 2004-18-01, Amendment 39-13778.

Applicability

    (c) This AD applies to Hoffmann Propeller GmbH & Co KG (Hoffmann 
Propeller) models HO-V343 and HO-V343K propellers. These propellers 
are installed on, but not limited to, general aviation airplanes 
possibly having an FAA-approved Supplemental Type Certificate.

Unsafe Condition

    (d) This AD results from a report of a blade separating from 
either a model HO-V343 or HO-V343K propeller. We are issuing this AD 
to prevent propeller hub failure and blade separation due to an 
unknown root cause, leading to damage and possible loss of control 
of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Propeller Blade Shake Inspection During Preflight Inspection

    (f) For all propellers, perform an inspection for propeller 
blade shake at each preflight inspection. If you have any blade 
shake, replace the propeller assembly.

Propeller Blade Nut Preload Inspection

    (g) For all propellers, use paragraph 2.1 of the Accomplishment 
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to inspect blade nut preload at 
the following intervals:
    (1) Before further flight after the effective date of this AD.
    (2) Inspect within 50 flight hours (FH) time-since-initial 
inspection.
    (3) Thereafter, inspect within 100 FH time-since-last inspection 
(TSLI).
    (h) If the blade nut preload inspection shows a loss of the 
blade nut preload, before further flight perform an ultrasonic 
inspection (UI) as specified in paragraph (i) of this AD.

Ultrasonic Inspection

    (i) If the propeller meets any of the conditions detailed in 
subparagraphs (1) and (2) below, before further flight, calibrate 
the ultrasonic probe and conduct an ultrasonic inspection of the 
propeller hub blade retaining threads for cracks inserting the probe 
in each hub arm bore. Use paragraph 2.2 of the Accomplishment 
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform the inspection.
    (1) The propeller hub has accumulated 500 or more FH time-since-
new (TSN), and has not been inspected using an ultrasonic or eddy 
current method, or
    (2) The blade nut preload and final retorque force inspection 
called for in paragraph (g) of this AD indicates a loss of blade 
retention nut preload torque below allowable limits.
    (j) For propellers with hubs that have accumulated 500 or more 
FH TSN repeat the ultrasonic inspection within intervals of 100 FH 
TSLI.

[[Page 36011]]

Eddy Current Inspection

    (k) If the ultrasonic inspection shows any signs of cracks or 
damage, conduct an eddy current inspection of the threads in the hub 
bore before further flight. Use paragraph 2.3 of the Accomplishment 
Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform this inspection.
    (l) If you find any signs of cracks or damage to the propeller 
hub outside serviceable limits during the eddy current inspection, 
repair or replace the propeller before further flight.

Credit for Previous Inspections

    (m) Previous credit is allowed for propeller hub inspections 
performed under the requirements of AD 2004-18-01.

Hub Inspection Report

    (n) Complete Hoffmann Hub Inspection Report HO-V343 detailing 
any blade shake, blade nut preload history and final blade nut 
retorque force and forward report to Hoffmann Propeller GmbH & Co 
KG, K[uuml]pferlingstra[szlig]e 9, D-83022 Rosenheim, Germany, 
telephone ++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78.

Alternative Methods of Compliance (AMOCs)

    (o) The Manager, Boston Aircraft Certification Office, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (p) You must use Hoffmann Propeller Service Instruction No. 61-
10-05 SI E 4D, dated March 16, 2005, to perform the checks and 
inspections required by this AD. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You 
can get a copy from Hoffmann Propeller GmbH & Co KG, 
K[uuml]pferlingstra[szlig]e 9, D-83022 Rosenheim, Germany, telephone 
++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78; or 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/code_of_federal_regulations/ibr_locations.html.

Related Information

    (q) LBA airworthiness directive D-2004-352R4, dated April 10, 
2005, which holds EASA Approval No. 2005-2514, also addresses the 
subject of this AD.

    Issued in Burlington, Massachusetts, on June 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-12172 Filed 6-21-05; 8:45 am]
BILLING CODE 4910-13-P