[Federal Register: August 8, 2005 (Volume 70, Number 151)]
[Proposed Rules]
[Page 45581-45585]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08au05-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22034; Directorate Identifier 2004-NM-182-AD]
RIN 2120-AA64
Airworthiness Directives; Gulfstream Model GV and GV-SP Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Gulfstream Model GV and certain Model GV-SP series airplanes.
This proposed AD would require a one-time inspection of the left and
right aileron and elevator actuators to determine the part and serial
numbers of each actuator, repetitive inspections of suspect actuators
to detect broken damper shafts, and replacement of any actuator having
a broken damper shaft. This proposed AD would also require that
operators report any broken damper shaft they find to the FAA. This
proposed AD also would provide an optional terminating action for the
repetitive inspection requirements of this proposed AD. This proposed
AD is prompted by reports of broken or cracked damper shafts within the
aileron and elevator actuator assemblies. We are proposing this AD to
detect and correct broken damper shafts, which could result in locking
of an aileron or elevator actuator (hard-over condition), which would
activate the hard-over protection system (HOPS), resulting in increased
pilot workload and consequent reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by September 22,
2005.
ADDRESSES: Use one of the following addresses to submit comments 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.
By 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.
For service information identified in this proposed AD, contact
Gulfstream Aerospace Corporation, Technical Publications Dept., P.O.
Box 2206, Savannah, Georgia 31402-9980.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-22034; the directorate identifier for this docket is
2004-NM-182-AD.
FOR FURTHER INFORMATION CONTACT: Gerald Avella, Aerospace Engineer,
Systems and Equipment Branch, ACE-119A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia 30349; telephone (770) 703-6066; fax (770) 703-
6097.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22034;
Directorate Identifier 2004-NM-182-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed 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 proposed AD. Using the search function of
that 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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in
[[Page 45582]]
person at the Docket Management Facility office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The Docket
Management Facility office (telephone (800) 647-5227) is located on the
plaza level of the Nassif Building at the DOT street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System (DMS) receives them.
Discussion
We have received a report from the airplane manufacturer,
Gulfstream, indicating that the damper shafts in two actuators broke
under normal torquing requirements during assembly of the actuators for
a Gulfstream Model GV-SP airplane. Approximately one week after the
original occurrence, a third actuator was found with a cracked damper
shaft. In each case, the cracks originated at the threaded base of the
damper shaft. In addition, the third actuator was found to be from a
manufacturing lot previous to that of the other two actuators. Parker
Aerospace, the actuator manufacturer, notified Gulfstream that the
production process used after 1998 to manufacture aileron and elevator
actuator damper shafts (internal to the actuator) may induce cracks in
the threaded portion of the shaft. This cracking could cause the
retaining nut and the separated portion of the failed damper shaft to
become dislodged from the damper body and block the movement of the
assembly. This condition, if not corrected, could result in locking of
an aileron or elevator actuator (hard-over condition), which would
activate the hard-over protection system (HOPS), resulting in increased
pilot workload and consequent reduced controllability of the airplane.
The affected aileron and elevator actuators installed on Gulfstream
Model GV and GV-SP series airplanes are identical to those installed on
Model G-1159, G-1159A, G-1159B, and G-IV series airplanes. Therefore,
all of these models may be subject to the identified unsafe condition.
Other Rulemaking for Additional Airplane Models
On October 4, 2004, we issued AD 2004-21-03, amendment 39-13824 (69
FR 61305, October 18, 2004), applicable to all Gulfstream Model G-1159,
G-1159A, G-1159B, and G-IV series airplanes. That AD currently requires
a one-time inspection of the left and right aileron and elevator
actuators to determine the part and serial numbers of each actuator,
repetitive inspections of suspect actuators to detect broken damper
shafts, and replacement of any actuator having a broken damper shaft.
That AD also requires that operators report any broken damper shaft(s)
they find to the FAA. That AD also provides an optional terminating
action for the repetitive inspection requirements of that AD. That AD
was prompted by reports of broken or cracked damper shafts within the
aileron and elevator actuator assemblies. The actions required by that
AD are intended to detect and correct broken damper shafts, which could
result in locking of an aileron or elevator actuator (hard-over
condition), subsequent loss of aileron or elevator control, and
consequent reduced controllability of the airplane.
Relevant Service Information
We have reviewed the following Gulfstream customer bulletins:
Table.--Relevant Service Information
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Model Customer bulletin Dated
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1. GV and GV-SP series airplanes Gulfstream G500 August 23, 2004.
Customer Bulletin
4.
2. GV and GV-SP series airplanes Gulfstream G550 August 23, 2004.
Customer Bulletin
4.
3. GV and GV-SP series airplanes Gulfstream GV August 23, 2004.
Customer Bulletin
123.
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The customer bulletins describe procedures for a one-time
inspection of the left and right aileron and elevator actuators to
determine the part number (P/N) and serial number (S/N) of each
actuator. The customer bulletins also describe procedures for an
inspection of the actuators with certain P/Ns and S/Ns to detect broken
damper shafts, and replacement of any actuator having a broken damper
shaft with a new or serviceable actuator.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require:
1. A one-time inspection of the left and right aileron and elevator
actuators to determine the part and serial numbers of each actuator;
2. Repetitive inspections of suspect actuators to detect broken
damper shafts, and replacement of any actuator having a broken damper
shaft; and
3. Any broken damper shaft found during the initial and repetitive
inspections is to be reported to the FAA. These actions are to be done
in accordance with the service information described previously, except
as discussed under ``Differences Between the Proposed AD and Customer
Bulletins.''
We are not proposing to require the terminating action (i.e.,
replacement of all suspect actuators) at this time, because we have
determined, and the actuator manufacturer has confirmed, that the
necessary replacement actuators (with a P/N and/or S/N not listed in
the applicable customer bulletin) are not yet available and will not be
available for another 24 to 36 months. Therefore, we are providing the
terminating action as an option for operators once those parts become
available.
Differences Between the Proposed AD and Customer Bulletins
The customer bulletins do not specify what to do if an installed
actuator has either a P/N or S/N that is missing or is unreadable. This
proposed AD would require that those actuators also be inspected to
detect broken damper shafts--as if they have a P/N and S/N listed in
the customer bulletins.
The customer bulletins recommend a one-time inspection of the
aileron and elevator actuators for broken damper shafts. However, a
suspect damper shaft found undamaged during the initial inspection
still has the potential to break at some time in the future. Because a
one-time inspection alone would not provide the degree of safety
necessary, we have determined that repetitive inspections of the
suspect actuators are necessary to ensure an adequate level of safety
for the affected transport airplane fleet. We have also determined that
an interval of 500 flight hours is an appropriate compliance time for
the repetitive inspections. Although the customer bulletins do not
include
[[Page 45583]]
repetitive inspections, they do note that a recurring inspection will
be added to the applicable airplane maintenance manual.
The customer bulletins also do not specify the type of inspection
to use to detect broken damper shafts. We have determined that a
detailed inspection for this action is appropriate. Therefore, this
proposed AD would require a detailed inspection to detect broken damper
shafts, and we have included the definition of a detailed inspection in
this proposed AD.
The customer bulletins specify replacing an actuator having a
broken damper shaft, but they do not specify the type of replacement
actuator. This proposed AD would require replacement with either:
A new or serviceable actuator having a subject P/N and S/N
listed in the customer bulletin, provided the actuator has been and
continues to be inspected for broken damper shafts in accordance with
the requirements of this proposed AD; or
A new or serviceable actuator having a P/N and/or S/N
different from any listed in the customer bulletin. Replacing an
actuator with an actuator having a different P/N and/or S/N would
terminate the requirements of this proposed AD for that actuator only.
The customer bulletins do not specify reporting findings of broken
damper shafts. This proposed AD would require that findings of all
broken damper shafts be reported to the FAA. When the unsafe condition
addressed by an AD is likely due to a manufacturer's quality control
(QC) problem, a reporting requirement is instrumental in ensuring that
we can gather as much information as possible regarding the extent and
nature of the QC problem or breakdown, especially in cases where the
data may not be available through other established means. This
information is necessary to ensure that proper corrective action will
be taken. Based on the results of these reports, we may determine that
further corrective action is warranted.
The Accomplishment Instructions of the customer bulletins specify
to submit the Service Reply Card or compliance information to the
manufacturer. This proposed AD does not include those actions.
These differences have been coordinated with the airplane
manufacturer.
Clarification of Applicability
The effectivities of the customer bulletins include all Model GV
and certain Model GV-SP series airplanes, equipped with aileron or
elevator actuators having certain P/Ns and S/Ns. Because there is no
way to determine if an actuator with a suspect P/N and S/N is installed
without inspecting the airplane, this proposed AD would apply to all
Model GV series airplanes and Model GV-SP series airplanes having
certain S/Ns. This requirement would ensure that the actions specified
in the service bulletins and required by this proposed AD are
accomplished on all affected airplanes. Note that the first action in
the customer bulletins is an inspection to determine if an actuator
having a certain P/N and S/N is installed.
Interim Action
This proposed AD is considered to be interim action. The inspection
reports that are required by this proposed AD will enable us to work
with the manufacturer to obtain better insight into the nature and
extent of the broken damper shafts, and eventually to develop final
action to address the unsafe condition. Once final action has been
developed and replacement parts are available, we may consider further
rulemaking.
Changes to 14 CFR Part 39/Effect on the AD Relating to Special Flight
Permits
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOC). This material is included in part 39, except that
the office authorized to approve AMOCs is identified in each individual
AD. However, as amended, part 39 provides for the FAA to add special
requirements for operating an airplane to a repair facility to do the
work required by an airworthiness directive. For the purposes of this
proposed AD, we have determined that such a special flight permit would
be prohibited if a broken damper shaft is found during the inspection
of the subject aileron and elevator actuators provided by paragraph (i)
of this proposed AD. Locking of an aileron or elevator actuator, which
would activate the hard-over protection system (HOPS), would
significantly reduce controllability of the airplane and increase pilot
workload. Intentionally operating an airplane in this condition would
inherently increase the risk of a major event.
Costs of Compliance
There are about 214 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 174 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
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Work Average labor Cost per
Action hours rate per hour Parts airplane Fleet cost
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Inspection for part/serial number.... 1 $65 $0 $65 $11,310.
Inspection of actuators, per 2 65 0 130 $22,620, per inspection
inspection cycle (if required). cycle.
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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 proposed AD would not have federalism
implications under Executive Order
[[Page 45584]]
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 that the 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. See the ADDRESSES section for a location
to examine the regulatory evaluation.
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
airworthiness directive (AD):
Gulfstream Aerospace Corporation: Docket No. FAA-2005-22034;
Directorate Identifier 2004-NM-182-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by September 22, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to all Gulfstream Model GV
series airplanes, and Model GV-SP series airplanes having serial
numbers (S/Ns) 5001 through 5052 inclusive; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by reports of broken or cracked damper
shafts within the aileron and elevator actuator assemblies. We are
issuing this AD to detect and correct broken damper shafts, which
could result in locking of an aileron or elevator actuator (hard-
over condition), which would activate the hard-over protection
system (HOPS), resulting in increased pilot workload and consequent
reduced controllability 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.
Service Information References
(f) The term ``customer bulletin,'' as used in this AD, means
the Accomplishment Instructions of the applicable Gulfstream
customer bulletins specified in Table 1 of this AD. Although the
customer bulletins recommend completing and submitting the Service
Reply Card or reporting compliance with the customer bulletin, those
actions are not required by this AD.
Table 1.--Applicable Gulfstream Customer Bulletins
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Model Customer bulletin Dated
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(1) GV-SP series airplanes...... Gulfstream G500 August 23, 2004.
Customer Bulletin
4.
(2) GV-SP series airplanes...... Gulfstream G550 August 23, 2004.
Customer Bulletin
4.
(3) GV series airplanes......... Gulfstream GV August 23, 2004.
Customer Bulletin
123.
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Inspection To Determine Actuator Part and Serial Numbers
(g) Within 500 flight hours after the effective date of this AD:
Do a one-time inspection of the left and right aileron and elevator
actuators to determine the part number (P/N) and S/N of each
actuator, in accordance with the applicable customer bulletin.
No Subject Actuators Installed
(h) If no actuator with a P/N and S/N listed in the applicable
customer bulletin is identified during the inspection required by
paragraph (g) of this AD, no further action is required by this AD,
except as required by paragraph (l) of this AD.
Initial and Repetitive Inspections and Corrective Action for Subject
Actuators
(i) For any actuator identified during the inspection required
by paragraph (g) of this AD with a P/N and S/N listed in the
applicable customer bulletin, and for actuators for which the P/N or
S/N is missing or unreadable: Before further flight, do a detailed
inspection of each identified actuator to detect a broken damper
shaft, in accordance with the applicable customer bulletin.
Note 1:
For the purposes of this AD, a detailed inspection is: ``An
intensive examination of a specific item, installation, or assembly
to detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary. Surface cleaning and
elaborate procedures may be required.''
(1) If no damper shaft is found broken: Repeat the inspection
required by paragraph (i) of this AD thereafter at intervals not to
exceed 500 flight hours.
(2) If any damper shaft is found broken: Before further flight,
do the action specified in either paragraph (i)(2)(i) or (i)(2)(ii)
of this AD, in accordance with the applicable customer bulletin.
(i) Replace the actuator with a new or serviceable actuator
having a P/N and S/N listed in the applicable customer bulletin,
provided the new or serviceable actuator has been inspected in
accordance with the requirements of paragraph (i) of this AD.
Thereafter, repeat the inspection required by paragraph (i) of this
AD for that actuator at intervals not to exceed 500 flight hours.
(ii) Replace the actuator with a new or serviceable actuator
having a P/N and/or S/N not listed in the applicable customer
bulletin. This replacement terminates the requirements of this
paragraph for that actuator only.
Optional Terminating Action
(j) Except as required by paragraph (l) of this AD, replacement
of all suspect actuators with new or serviceable actuators having a
P/N and/or S/N not listed in the applicable customer bulletin
terminates the requirements of this AD.
Reporting Requirement
(k) Submit a report of any broken damper shafts to the Manager,
Atlanta Aircraft Certification Office (ACO), FAA, One Crown Center,
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; fax (770)
703-6097. The report must be done at the applicable time specified
in paragraph (k)(1) or (k)(2) of this AD. The report must include
the inspection date, the airplane model and S/N, the actuator
position (left or right aileron or elevator), and the actuator P/N
and S/N. Information collection requirements contained in this AD
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
(1) If the inspection required by paragraph (i) of this AD is
done after the effective date of this AD: Submit a report within 30
days after each inspection required by paragraph (i) of this AD.
[[Page 45585]]
(2) If an inspection required by paragraph (i) of this AD was
done before the effective date of this AD: Submit a report within 30
days after the effective date of this AD.
Parts Installation
(l) As of the effective date of this AD, no person may install
an aileron or elevator actuator having a P/N and S/N specified in
the applicable customer bulletin on any airplane, unless the
actuator has been inspected according to paragraph (i) of this AD.
Special Flight Permit Prohibited
(m) Special flight permits (14 CFR 21.197 and 21.199) are not
allowed if any broken damper shaft is found during any inspection
required by paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(n) The Manager, Atlanta ACO, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19..
Issued in Renton, Washington, on August 2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-15589 Filed 8-5-05; 8:45 am]
BILLING CODE 4910-13-P