[Federal Register: November 23, 2005 (Volume 70, Number 225)]
[Rules and Regulations]
[Page 70718-70720]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23no05-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23085; Directorate Identifier 2005-SW-25-AD;
Amendment 39-14385; AD 2005-24-05]
RIN 2120-AA64
Airworthiness Directives; Boeing Vertol Model 107-II 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
Boeing Vertol (Boeing) Model 107-II helicopters. This action requires a
visual and magnetic particle inspection of the quill shaft. This
amendment is prompted by the discovery of cracks in a quill shaft
during a routine inspection. The actions specified in this AD are
intended to detect a fatigue crack in a quill shaft and prevent
separation of the quill shaft between the aft transmission and the mix
box assembly, loss of rotor synchronization, and subsequent loss of
control of the helicopter.
DATES: Effective December 8, 2005.
Comments for inclusion in the Rules Docket must be received on or
before January 23, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this 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;
Fax: (202) 493-2251; or
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.
You may get the service information identified in this AD from The
Boeing Company, c/o Service Engineering, MC P01-10, P.O. Box 16858,
Philadelphia, PA 19142-3227.
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 Management System (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 the ADDRESSES section. Comments will be available in the AD
docket shortly after the DMS receives them.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aviation Safety
Engineer, FAA, New York Aircraft
[[Page 70719]]
Certification Office, Airframe and Propulsion Branch, 1600 Stewart
Ave., suite 410, Westbury, New York 11590, telephone (516) 228-7325,
fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Boeing
Model 107-II helicopters. This action requires a visual and magnetic
particle inspection of the quill shaft. This amendment is prompted by
the discovery of cracks in a quill shaft during a routine 700-hour TIS
clutch replacement in which a magnetic particle inspection of the quill
shaft was done. Investigation shows that cracking on the ends of the
spline teeth of the quill shaft, around the pinhole, occurs due to a
wear step in the mating pinion gear splines. These cracked spline teeth
can provide stress concentrations that may lead to fatigue cracks. This
condition, if not corrected, could result in separation of the quill
shaft between the aft transmission and the mix box assembly, loss of
rotor synchronization, and subsequent loss of control of the
helicopter.
We have reviewed Boeing Service Bulletin No. 107-63-1005, Revision
1, dated April 27, 2005, which describes procedures for inspections of
quill shafts, part number (P/N) 107D2067, all dash numbers. The service
bulletin also specifies rejecting any quill shaft with chipped or
cracked teeth or any quill shaft with a crack and, although not
required by this AD, specifies measuring and recording wear in the
spline of the mating pinion gear, P/N 107D2215. Also, Boeing recommends
replacing unairworthy quill shafts with airworthy quill shafts, P/N
107D2067-5. These part-numbered quill shafts have been improved with a
shot-peen process. However, in this AD, we are only requiring that you
replace any unairworthy quill shaft with an airworthy quill shaft with
any approved P/N.
This AD is an interim action which covers initial inspections of
the quill shaft. We plan to follow this AD with a superseding Notice of
Proposed Rulemaking (NPRM) containing longer term requirements. The
NPRM will propose adding the pinion gear wear measurements specified in
the service bulletin and will propose adding recurring inspections of
the quill shaft. Also, because we still have not determined the cause
of the wear steps in the mating pinion gear splines, we may consider
further rulemaking when the cause is ultimately determined.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, this AD is being issued
to detect a fatigue crack in a quill shaft and prevent separation of
the quill shaft between the aft transmission and the mix box assembly,
loss of rotor synchronization, and subsequent loss of control of the
helicopter. This AD requires the following for a helicopter with a
quill shaft, P/N 107D2067, and a pinion gear, P/N 107D2215, installed:
Remove the aft transmission assembly, separate the mix box
assembly from the aft transmission, and remove the quill shaft from the
pinion gear assembly;
Visually inspect the external spline of the quill shaft
for a chipped or cracked tooth around the pinhole; and
Magnetic particle inspect the quill shaft for a crack.
Replace any quill shaft that has a crack or a chipped or
cracked tooth with an airworthy quill shaft before further flight.
If the pinion gear has 700 or more hours TIS, comply within 50 hours
TIS, unless accomplished within the previous 350 hours TIS. If the
pinion gear has less than 700 hours TIS, comply on or before reaching
750 hours TIS.
The short compliance time involved is required because these high-
usage helicopters can quickly develop pinion gear wear that could lead
to cracks in the quill shaft and adversely affect the structural
integrity and controllability of the helicopter. Therefore, the actions
described previously are required within 50 hours TIS, a short time
period of about 2 weeks based on the high usage rate of these model
helicopters, 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 7 helicopters. We estimate
that each helicopter inspection will take about 17 work hours at an
average labor rate of $65 per work hour. Required parts will cost
$2,500 for each quill shaft. Based on these figures, we estimate the
total cost impact of the AD on U.S. operators to be $10,235, assuming
one quill shaft is replaced on the 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-2005-23085;
Directorate Identifier 2005-SW-25-AD'' 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
[[Page 70720]]
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:
2005-24-05 Boeing Vertol (Boeing): Amendment 39-14385. Docket No.
FAA-2005-23085; Directorate Identifier 2005-SW-25-AD.
Applicability: Model 107-II helicopters, all serial numbers,
with a quill shaft, part number (P/N) 107D2067, all dash numbers,
and a spiral bevel pinion gear (pinion gear), P/N 107D2215,
installed, certificated in any category.
Compliance: Required as indicated.
To detect a fatigue crack in a quill shaft to prevent separation
of the quill shaft between the aft transmission and the mix box
assembly, loss of rotor synchronization, and subsequent loss of
control of the helicopter, accomplish the following:
(a) For a helicopter with a pinion gear installed with the
following hours time-in-service (TIS):
------------------------------------------------------------------------
Pinion gear hours TIS Compliance time
------------------------------------------------------------------------
700 or more hours TIS.................. Within 50 hours TIS, unless
accomplished within the
previous 350 hours TIS.
Less than 700 hours TIS................ On or before reaching 750 hours
TIS.
------------------------------------------------------------------------
(1) Remove the aft transmission assembly, separate the mix box
assembly from the aft transmission, and remove the quill shaft from
the pinion gear assembly;
(2) Visually inspect the external spline of the quill shaft for
a chipped or cracked tooth around the pinhole; and
(3) Magnetic particle inspect the quill shaft for a crack.
(b) Before further flight, replace any quill shaft that has a
crack or a chipped or cracked tooth with an airworthy quill shaft.
Note 1: Boeing Service Bulletin No. 107-63-1005, Revision 1,
dated April 27, 2005, pertains to the subject of this AD.
Note 2: Replacement quill shafts manufactured by Kawasaki Heavy
Industries (KHI) for use on their Model KV107-II helicopters must be
approved by the geographic Aircraft Certification Office (ACO) on a
case-by-case basis for installation on a Boeing Model 107-II
helicopter.
(c) 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, New York ACO, Engine and Propeller Directorate,
FAA, for information about previously approved alternative methods
of compliance.
(d) Special flight permits will not be issued.
(e) This amendment becomes effective on December 8, 2005.
Issued in Fort Worth, Texas, on November 16, 2005.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-23156 Filed 11-22-05; 8:45 am]
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