[Federal Register Volume 62, Number 5 (Wednesday, January 8, 1997)]
[Rules and Regulations]
[Pages 1041-1044]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-475]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-ANE-66; Amendment 39-9863; AD 96-25-20]
RIN 2120-AA64


Airworthiness Directives; Hamilton Standard 14RF and 14SF Series, 
and Hamilton Standard/British Aerospace Model 6/5500/F Propellers

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Hamilton Standard 14RF and 14SF series, and Hamilton 
Standard/British Aerospace Model 6/5500/F propellers, that requires 
initial and repetitive inspections of critical control components, and 
removal and replacement with serviceable parts those critical control 
components that do not meet the return to service criteria. This 
amendment is prompted by failure modes effects analysis (FMEA), 
certification test data, engineering analysis, and repair actions 
performed at overhaul depots. The actions specified by this AD are 
intended to prevent loss of propeller control due to failure of 
critical control components, which could result in loss of control of 
the aircraft.

DATES: Effective February 7, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 7, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from Publication Distribution, Hamilton Standard, One Hamilton 
Road, Windsor Locks, CT 06096-1010; fax (860) 654-6906. This 
information may be examined at the Federal Aviation Administration 
(FAA), New England Region, Office of the Assistant Chief 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 (617) 238-7158, fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Hamilton Standard Models 14RF-9, 
14RF-19, 14RF-21; 14SF-5, 14SF-7, 14SF-11, 14SF-11L, 14SF-15, 14SF-17, 
14SF-19, 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F 
propellers was published in the Federal Register on December 13, 1995 
(60 FR 63988). That action proposed to require initial and repetitive 
inspections of critical aspects of the transfer tube assembly, actuator 
assembly, and propeller control unit (PCU) for wear. This AD would also 
require, prior to further flight, removing and replacing with 
serviceable parts those critical components that do not meet the return 
to service criteria.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Three commenters state that the initial AD inspection interval for 
the transfer tube should be 10,500 hours time in service (TIS) as noted 
in the appropriate Hamilton Standard Service Bulletin (SB) and 
supported by the manufacturers wear data. The commenters also indicated 
that the time interval of 10,500 hours TIS is significant since it 
coincides with the Major Inspection Interval (MII) that many operators 
adhere to on certain propeller installations. In addition, the 
commenters requested that credit be given to MII inspections that have 
been done recently that meet the inspection requirements of the 
appropriate SBs.
    The FAA concurs in part. Although the wear data supports an 
inspection interval by more than 3 times the 10,500 hour TIS interval, 
the FAA has determined that the initial inspection should be 
accomplished within 6,000 hours TIS, or 3 years, whichever occurs 
first, after the effective date of this AD. The initial inspection 
compliance time was selected because the transfer tubes have not been 
time tracked. The 6,000 hours TIS initial inspection compliance time 
will result in all transfer tubes to be inspected within a time 
interval supported by the wear data. Also, credit cannot be given to 
components inspected during the MII unless the components were 
inspected in accordance with the appropriate critical parts inspection 
SBs. The FAA intends to give credit for critical parts inspections 
performed in accordance with the appropriate SBs that have already been 
performed within the 10,500 hours TIS interval.
    The initial inspection also coincides with the installation of the 
new major alteration feature, Secondary Drive Quill (SDQ) that is 
mandated by AD 95-22-12 to be completed prior to June 30, 1998. This 
coordination effort will give a smooth phase-in of all requirements 
with a minimal impact on record keeping and operational commitments. To 
conclude, the FAA has determined that an initial inspection within 
6,000 hours TIS, or 3 years whichever occurs first, after the effective 
date of this AD will safely introduce the transfer tube into a 
repetitive inspection at 10,500 hours TIS intervals thereafter.
    Two commenters state that at present there is no tracking of time 
in service for these components and that tracking will be unduly 
burdensome. The FAA concurs that there is no current requirement to 
track component time in service, but disagrees that adding the 
requirement to track time would be unduly burdensome since time 
tracking

[[Page 1042]]

is currently conducted on other propeller components. Systems to track 
time on propeller components have already been established. The FAA 
program to introduce these components to time tracking begins with an 
initial phase in interval of 6,000 hours TIS, or 3 years, whichever 
occurs first, after the effective date of this AD, followed by a 
repetitive inspection of these components at a 10,500 hours TIS 
interval that was not required at certification.
    Two commenters state that the total economic impact of the proposed 
rule has been underestimated because the FAA did not include costs such 
as loss of revenue from having aircraft sit idle while awaiting the 
required inspections. The FAA does not concur. The cost impact of this 
AD was calculated using data from the industry as to the time and parts 
needed to accomplish the required actions. The FAA does not include the 
costs of secondary effects of performing the actions required by the AD 
in its economic analysis. As a matter of law, in order to be operated 
in commercial service, an aircraft must conform to its type design and 
be in a condition for safe flight. The type design of the affected 
propellers was certificated only after the FAA found that the design 
complied with all applicable airworthiness requirements. In adopting 
those certification requirements, the FAA already determined a level of 
safety that is cost beneficial. With this AD, the FAA has determined 
that an unsafe condition exists, that means that a cost-beneficial 
level of safety is no longer achieved, and that additional requirements 
must be performed in order to restore that level of safety. Because 
that level of safety was already determined to be cost-beneficial, a 
full cost analysis is not required for each AD, and the costs of the 
secondary effects of performing the actions required by the AD are not 
added to the cost analysis of the AD.
    In addition the FAA has increased the initial inspection compliance 
time to 6,000 hours TIS, or 3 years, whichever occurs first, after the 
effective date of this AD. The increase in initial inspection 
compliance time will smooth the transition to the 10,500 hours TIS 
repetitive inspection program and minimize the impact on aircraft 
operation.
    Three commenters state that, to date, there is no evidence of in-
service wear of the affected components. The FAA concurs in part. The 
engineering and repair data indicate wear does exist but at an 
extremely low level. Since wear does occur on these critical components 
they must be inspected periodically and these components must be 
removed from an unspecified repair status to a defined inspection 
interval category.
    Two commenters state that the PCU inspection is already required by 
another AD. The FAA concurs in part. The purpose of this new AD is to 
integrate inspection items not covered by AD 95-22-12 into a 
comprehensive coordinated inspection requirement for the propeller 
control system. Airworthiness directive 95-22-12 only addresses 
inspection of the PCU servo ballscrew internal spline, installation of 
a secondary drive quill, and a torque check inspection of the primary 
ballscrew quill.
    One commenter states that the repetitive inspection interval should 
be reduced from 10,500 hours TIS to 2,500 hours TIS. The FAA does not 
concur. Engineering investigation, analysis, and field and laboratory 
testing reveal these components can operate safely within the 10,500 
hours TIS inspection interval so the interval does not need to be 
reduced further.
    Two commenters state that credit should be given for Critical Parts 
Inspections (CPIs) that have already been performed within the previous 
10,500 hours TIS MII. The FAA concurs in part. This final rule 
increases the initial inspection interval from 1,000 hours TIS to 6,000 
hours TIS, or 3 years, whichever occurs first, after the effective date 
of this AD, for these CPI items, and thereafter requires inspection at 
intervals of 10,500 hours TIS in accordance with the applicable SBs. 
The FAA intends to give credit for those CPIs conducted in accordance 
with the SBs applicable to this AD.
    One commenter requests clarification on the definition of time in 
service, TIS. The FAA concurs. The FAA interprets this question that 
time in service, for the purpose of this AD, is defined as operating 
time since issuance of this AD or operating time since last inspection 
in accordance with this AD. The FAA has added this definition to the AD 
as new paragraph (d).
    One commenter states that there is insufficient time to accomplish 
the inspections based upon limited repair shop capacity. The FAA re-
evaluated the overall phase in program and determined that an initial 
inspection compliance interval 6,000 hours TIS, or 3 years, whichever 
occurs first, after the effective date of this AD would safely 
introduce components to the repetitive inspection program while 
alleviating the repair shop capacity problem.
    Since publication of the NPRM, Hamilton Standard has issued 
Revision 1, dated April 23, 1996, to the following SBs: 14RF-9-61-64, 
14RF-19-61-32, 14RF-21-61-51, 14SF-61-70, and 6/5500/F-61-25. This 
revision modifies a figure, adds an additional figure, deletes the 
requirement to inspect the PCU retaining nut, and makes minor editorial 
changes for clarification only. This final rule references this new 
revision as well as the original issuances.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 3,280 propellers of the affected design in 
the worldwide fleet (excluding spares). The FAA estimates that 1,370 
propellers installed on aircraft of U.S. registry will be affected by 
this AD, that it will take approximately 4.3 work hours per propeller 
to accomplish the required actions, and that the average labor rate is 
$60 per work hour. Based on these figures, the total cost impact of the 
AD on U.S. operators is estimated to be $353,460 per fleet inspection.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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

[[Page 1043]]

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:

96-25-20  Hamilton Standard: Amendment 39-9863. Docket 95-ANE-66.

    Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-
21, and 14SF-5, 14SF-7, 14SF-11, 14SF-11L, 14SF-15, 14SF-17, 14SF-
19, 14SF-23 and Hamilton Standard/British Aerospace 6/5500/F 
propellers installed on but not limited to Embraer EMB-120 and EMB-
120-RT; SAAB-SCANIA SF 340B; Aerospatiale ATR42-100, ATR42-300, 
ATR42-320, ATR72; DeHavilland DHC-8-100 series, DHC-8-300 Series; 
Construcciones Aeronauticas SA (CASA) CN-235 series and CN-235-100; 
Canadair CL-215T and CL-415; and British Aerospace ATP Airplanes.

    Note 1: This airworthiness directive (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 (e) 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: Required as indicated, unless accomplished 
previously.
    To prevent loss of propeller control due to failure of critical 
components, which could result in loss of control of the aircraft, 
accomplish the following:
    (a) Inspect transfer tube assemblies and propeller control units 
(PCUs) for wear within 6,000 hours time in service (TIS), or 3 
years, whichever occurs first, after the effective date of this AD. 
Perform inspections of the critical aspects of these components in 
accordance with the applicable service bulletins (SBs) listed in 
paragraph (c) of this AD. Thereafter, inspect at intervals not to 
exceed 10,500 hours TIS since last inspection. Prior to further 
flight, remove and replace with serviceable parts those components 
that do not meet the return to service criteria defined in the 
applicable SBs. (For PCUs that have a Secondary Drive Quill (SDQ) 
installed in accordance with AD 95-22-12, it is not necessary to 
conduct an initial inspection again. They may advance to the 
repetitive inspection interval based on the TIS since SDQ 
installation.)
    (b) Inspect actuator assemblies for wear within 10,500 hours TIS 
after the effective date of this AD, or at the next major inspection 
interval (MII), whichever occurs first. Perform inspections of the 
critical aspects of these components in accordance with the 
applicable service bulletins (SBs) listed in paragraph (c) of this 
AD. Thereafter, inspect at intervals not to exceed 10,500 hours TIS 
since last inspection. Prior to further flight, remove and replace 
with serviceable parts those components that do not meet the return 
to service criteria defined in the applicable SBs.
    (c) Perform the inspections for wear required by this AD in 
accordance with, and use the return to service criteria defined in, 
the following applicable Hamilton Standard SBs, Revision 1, all 
dated April 23, 1996, or Original, dated November 27, 1995: 14RF-9-
61-64, 14RF-19-61-32, 14RF-21-61-51, 14SF-61-70, and 6/5500/F-61-25.
    (d) For the purpose of this AD, time in service (TIS) is defined 
as operating time since issuance of this AD or operating time since 
last inspection in accordance with this AD.
    (e) 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. The request should be forwarded through an appropriate FAA 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Boston Aircraft Certification Office.

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

    (f) Special 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) to operate the aircraft to a location where the 
requirements of this AD can be accomplished.
    (g) The actions required by this AD shall be done in accordance 
with the following Hamilton Standard SBs:

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            Document No.                    Pages               Revision                       Date             
----------------------------------------------------------------------------------------------------------------
14RF-9-61-64.......................  1, 2..............  1.....................  April 23, 1996.                
                                     3.................  Original..............  November 27, 1995.             
                                     4.................  1.....................  April 23, 1996.                
                                     5-11..............  Original..............  November 27, 1995.             
                                     12, 13............  1.....................  April 23, 1996.                
                                     14-28.............  Original..............  November 27, 1995.             
                                     29................  1.....................  April 23, 1996.                
                                     30, 31............  Original..............  November 27, 1995.             
                                     32................  1.....................  April 23, 1996.                
                                     33................  Original..............  November 27, 1995.             
                                     34................  1.....................  April 23, 1996.                
Total Pages: 34.                                                                                                
14RF-9-61-64.......................  1-33..............  Original..............  November 27, 1995.             
Total Pages: 33.                                                                                                
14RF-19-61-32......................  1, 2..............  1.....................  April 23, 1996.                
                                     3.................  Original..............  November 27, 1995.             
                                     4.................  1.....................  April 23, 1996.                
                                     5-11..............  Original..............  November 27, 1995.             
                                     12, 13............  1.....................  April 23, 1996.                
                                     14-28.............  Original..............  November 27, 1995.             
                                     29................  1.....................  April 23, 1996.                
                                     30, 31............  Original..............  November 27, 1995.             
                                     32................  1.....................  April 23, 1996.                
                                     33................  Original..............  November 27, 1995.             
                                     34................  1.....................  April 23, 1996.                
Total Pages: 34.                                                                                                
14RF-19-61-32......................  1-33..............  Original..............  November 27, 1995.             
Total pages: 33.                                                                                                
14RF-21-61-51......................  1, 2..............  1.....................  April 23, 1996.                
                                     3.................  Original..............  November 27, 1995.             

[[Page 1044]]

                                                                                                                
                                     4.................  1.....................  April 23, 1996.                
                                     5-11..............  Original..............  November 27, 1995.             
                                     12, 13............  1.....................  April 23, 1996.                
                                     14-27.............  Original..............  November 27, 1995.             
                                     28................  1.....................  April 23, 1996.                
                                     29-31.............  Original..............  November 27, 1995.             
                                     32................  1.....................  April 23, 1996.                
                                     33................  Original..............  November 27, 1995.             
                                     34................  1.....................  April 23, 1996.                
Total Pages: 34.                                                                                                
14RF-21-61-51......................  1-33..............  Original..............  November 27, 1995.             
Total Pages: 33.                                                                                                
14SF-61-70.........................  1, 2..............  1.....................  April 23, 1996.                
                                     3.................  Original..............  November 27, 1995.             
                                     4.................  1.....................  April 23, 1996.                
                                     5, 6..............  Original..............  November 27, 1995.             
                                     7.................  1.....................  April 23, 1996.                
                                     8-11..............  Original..............  November 27, 1995.             
                                     12-14.............  1.....................  April 23, 1996.                
                                     15-29.............  Original..............  November 27, 1995.             
                                     30................  1.....................  April 23, 1996.                
                                     31, 32............  Original..............  November 27, 1995.             
                                     33................  1.....................  April 23, 1996.                
                                     34................  Original..............  November 27, 1995.             
                                     35................  1.....................  April 23, 1996.                
Total Pages: 35.                                                                                                
14SF-61-70.........................  1-34..............  Original..............  November 27, 1995.             
Total Pages: 34.                                                                                                
6/5500/F-61-25.....................  1, 2..............  1.....................  April 23, 1996.                
                                     3.................  Original..............  November 27, 1995.             
                                     4.................  1.....................  April 23, 1996.                
                                     5, 6..............  Original..............  November 27, 1995.             
                                     7.................  1.....................  April 23, 1996.                
                                     8-10..............  Original..............  November 27, 1995.             
                                     11-13.............  1.....................  April 23, 1996.                
                                     14-28.............  Original..............  November 27, 1995.             
                                     29................  1.....................  April 23, 1996.                
                                     30, 31............  Original..............  November 27, 1995.             
                                     32................  1.....................  April 23, 1996.                
                                     33................  Original..............  November 27, 1995.             
                                     34................  1.....................  April 23, 1996.                
Total Pages: 34.                                                                                                
6/5500/F-61-25.....................  1-33..............  Original..............  November 27, 1995.             
Total Pages: 33.                                                                                                
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    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 Publication Distribution, 
Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010; 
fax (860) 654-6906. Copies may be inspected at the FAA, New England 
Region, Office of the Assistant Chief 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.
    (h) This amendment becomes effective on February 7, 1997.

    Issued in Burlington, Massachusetts, on December 11, 1996.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 97-475 Filed 1-7-97; 8:45 am]
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