[Federal Register Volume 67, Number 143 (Thursday, July 25, 2002)]
[Rules and Regulations]
[Pages 48537-48539]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-18481]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-02-AD; Amendment 39-12831; AD 2002-15-03]
RIN 2120-AA64


Airworthiness Directives; Hamilton Sundstrand Corporation Model 
568F-1 Propellers.

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule, request for comments.

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SUMMARY: This amendment supersedes an emergency airworthiness directive 
(AD) 2002-05-51 that was sent previously to all known U.S. owners and 
operators of Hamilton Sundstrand Corporation (formerly Hamilton 
Standard Division) model 568F-1 propellers. That AD requires 
replacement of propeller blades, part numbers (P/N's) R815505-2 and 
R815505-3, that have a serial number (SN) of FR1698 or lower, with 
serviceable propeller blades, a prohibition against installing any 
propeller blades, P/N's R815505-2 and R815505-3, that have a SN of 
FR428 or lower, that were previously installed on an ATR-42-400 or an 
ATR-72 airplane, on any other airplane, and initial and repetitive 
ultrasonic shear wave inspection of the blade tulip on installed blades 
P/N's R815505-2 and R815505-3, that have a SN of FR1698 or lower. This 
amendment requires those same actions, and also requires replacing 
certain SN blades before further flight. This amendment also requires 
initial and repetitive ultrasonic shear wave inspections of the blade 
tulip on installed blades, P/N's R815505-2 and R815505-3, that have a 
SN of FR1698 or lower until they are replaced. This amendment is 
prompted by a report of a blade failure that resulted in damage to the 
airplane. The actions specified in this AD are intended to prevent 
blade failure due to corrosion-induced fatigue, which could result in 
blade separation and possible loss of airplane control.

DATES: Effective August 9, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of August 9, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before September 23, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-02-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The applicable service information may be obtained from Hamilton 
Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1-3-
AB43, Windsor Locks, CT 06096-1010, U.S.A.; Fax 1-860-654-5107. This 
information may be examined, by appointment, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer, 
Boston Aircraft Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7158; fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: On March 7, 2002, the FAA issued emergency 
AD 2002-05-51, applicable to Hamilton Sundstrand Corporation (formerly 
Hamilton Standard Division) model 568F-1 propellers installed with 
blades, P/N's R815505-2 and R815505-3, that have a SN of FR1698 or 
lower. That AD requires:
     Replacement of propeller blades, P/N's R815505-2 and 
R815505-3, that have a SN of FR1698 or lower, with serviceable 
propeller blades.
     A prohibition against installing any propeller blades, P/
N's R815505-2 and R815505-3, that have a SN of FR428 or lower, that 
were previously installed on an ATR-42-400 or an ATR-72 airplane, on 
any other airplane.
     Ultrasonic shear wave inspection of the blade tulip on 
installed blades P/N's

[[Page 48538]]

R815505-2 and R815505-3, that have a SN of FR1698 or lower, within 50 
hours after receipt to that emergency AD.
     Repetitive ultrasonic shear wave inspection of the blade 
tulip on installed blades, P/N's R815505-2 and R815505-3, that have a 
SN of FR1698 or lower, within 50 flight hours since-last-inspection.
    That action was prompted by a report that a Hamilton Sundstrand 
propeller blade failed on an Aerospatiale ATR42-500 airplane. The 
failure occurred shortly after takeoff. The airplane was able to return 
safely to the point of departure. The position 5 blade failed outboard 
of the counterweight mounting flange. Additional damage to the 
propeller, engine, and nacelle was found. Root cause investigation has 
determined that the fracture began at an area of corrosion on the 
metallic portion of the blade just above and opposite the counterweight 
mounting flange. Engineering evaluation of the blade population that is 
susceptible to corrosion-induced fatigue has determined that the 
affected blades must be replaced to prevent blade failure. Subsequent 
investigation has determined that the suspect blade population must be 
inspected for fatigue cracks, due to corrosion pitting, using a 
repetitive ultrasonic shear wave inspection. This condition, if not 
corrected, could result in blade failure due to corrosion-induced 
fatigue, which could result in blade separation and possible loss of 
airplane control.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of 
Hamilton Sundstrand Alert Service Bulletin No. 568F-61-A35, Revision 2, 
dated March 21, 2002, which provides procedures to perform the 
ultrasonic shear wave inspection of the blade tulip.

FAA's Determination of an Unsafe Condition and Required Actions

    Since the unsafe condition described is likely to exist or develop 
on other propellers of the same type design, the FAA issued emergency 
AD 2002-05-51 to prevent blade failure due to corrosion-induced 
fatigue, which could result in blade separation and possible loss of 
airplane control. This AD requires:
     Replacement of propeller blades, P/N's R815505-2 and 
R815505-3, that have a SN of FR1698 or lower, that are installed on ATR 
42-400 and ATR 72 airplanes, with serviceable propeller blades before 
further flight.
     A prohibition against installing any propeller blades, P/
N's R815505-2 and R815505-3, that have a SN of FR428 or lower, that 
were previously installed on an ATR 42-400 or an ATR 72 airplane, on 
any other airplane after the effective date of this AD.
     Ultrasonic shear wave inspection of the blade tulip on 
installed blades P/N's R815505-2 and R815505-3, that have a SN of 
FR1698 or lower, within 50 hours after the effective date of this AD.
     Repetitive ultrasonic shear wave inspection of the blade 
tulip on installed blades, P/N's R815505-2 and R815505-3, that have a 
SN of FR1698 or lower, within 50 flight hours since-last-inspection.
    The actions must be done in accordance with the service bulletin 
described previously.

Immediate Adoption of This AD

    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.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NE-02-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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

    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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-15-03  Hamilton Sundstrand Corporation: Amendment 39-12831. 
Docket No. 2002-NE-02-AD. Supersedes AD 2002-05-51.

    Applicability: This airworthiness directive (AD) is applicable 
to Hamilton Sundstrand

[[Page 48539]]

Corporation (formerly Hamilton Standard Division) model 568F-1 
propellers installed with blades, part numbers (P/N's) R815505-2 and 
R815505-3, that have a serial number (SN) of FR1698 or lower. These 
propellers are installed on, but not limited to, Aerospatiale ATR 
42-400 and -500 and ATR 72 airplanes.

    Note 1: This AD applies to each propeller identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For propellers that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (i) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent blade failure due to corrosion-induced fatigue, which 
could result in blade separation and possible loss of airplane 
control, do the following:
    (a) For propeller blades P/N's R815505-2 and R815505-3, replace 
propeller blades SN FR265 or lower before further flight.
    (b) Before further flight, replace propeller blades P/N's 
R815505-2 and R815505-3, that have a SN of FR1698 or lower, 
installed on ATR 72 and ATR 42-400 airplanes.
    (c) After the effective date of this AD, do not install any 
propeller blade that was removed in accordance with paragraph (b) of 
this AD on any airplane.
    (d) Replace propeller blades P/N's R815505-2 and R815505-3, that 
have a SN of FR1698 or lower, installed on ATR 42-500 airplanes, 
before December 31, 2002.
    (e) After the effective date of this AD, do not install any 
propeller blades, P/N's R815505-2 and R815505-3, that have a SN of 
FR1698 or lower, on any airplane unless an ultrasonic shear wave 
inspection of the blade tulip is done in accordance with the 
Accomplishment Instructions of Hamilton Sundstrand ASB 568F-61-A35, 
Revision 2, dated March 21, 2002, before installation of the 
propeller blade.
    (f) Procedures for removing the propeller blade and installing a 
serviceable blade can be found in Hamilton Sundstrand Maintenance 
Manual P5206.
    (g) Within 50 FH since-last-inspection, for propeller blades, P/
N's R815505-2 and R815505-3, that have a SN of FR1698 or lower, 
perform an ultrasonic shear wave inspection of the blade tulip in 
accordance with the Accomplishment Instructions of Hamilton 
Sundstrand ASB 568F-61-A35, Revision 2, dated March 21, 2002, and 
remove blades with unacceptable indications in accordance with the 
ASB.
    (h) Thereafter, within 50 FH since-last-inspection, for 
propellers blades P/N's R815505-2 and R815505-3, that have a SN of 
FR1698 or lower, perform an ultrasonic shear wave inspection of the 
blade tulip in accordance with the Accomplishment Instructions of 
Hamilton Sundstrand ASB 568F-61-A35, Revision 2, dated March 21, 
2002, and remove blades with unacceptable indications in accordance 
with the ASB.

Optional Terminating Action

    (i) Replacement of propeller blades, P/N R815505-2, with 
propeller blades, P/N R81505R2; or propeller blades, P/N R815505-3, 
with propeller blades, P/N R815505R3, constitutes terminating action 
for the repetitive inspection requirements specified in paragraph 
(h) of this AD.

Alternative Methods of Compliance

    (j) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Boston Aircraft Certification 
Office (ACO). Operators must submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Boston ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Boston ACO.

Special Flight Permits

    (k) Special limited flight permits may be issued in accordance 
with Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) for a nonrevenue flight to a location where 
the requirements of this AD can be done.

Documents That Have Been Incorporated By Reference

    (l) The actions required by this AD must be done in accordance 
with Hamilton Sundstrand Alert Service Bulletin No. 568F-61-A35, 
Revision 2, dated March 21, 2002. This incorporation by reference 
was approved by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 
Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, 
Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010, U.S.A.; Fax 1-860-
654-5107. Copies may be inspected, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (m) This amendment becomes effective August 9, 2002.

    Issued in Burlington, Massachusetts, on July 15, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-18481 Filed 7-24-02; 8:45 am]
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