AD 2006-03-11
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | BAE Systems (Operations) Limited | HS 748 Series 2A | Airworthiness Directives; British Aerospace Model HS 748 Airplanes |
| aircraft | BAE Systems (Operations) Limited | HS 748 Series 2B | Airworthiness Directives; British Aerospace Model HS 748 Airplanes |
Unsafe Condition
Uncommanded re-engagement of the elevator gust lock, which could result in restriction of the elevator's movement and consequent reduced controllability of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install a baulking actuator system for the elevator gust lock, perform a functional test and inspection of the actuator system for wiring errors, conduct repetitive inspections of the gust lock baulk lever for correct operation, and take corrective action if necessary. Operators must contact the FAA or CAA for repair instructions if the baulk lever is found to be operating incorrectly.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
British Aerospace Model HS 748 airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
The FAA is adopting a new airworthiness directive (AD) for all British Aerospace Model HS 748 airplanes. This AD requires installing a baulking actuator system for the elevator gust lock; doing a functional test and an inspection of any previously installed baulking actuator system for wiring errors; doing repetitive inspections of the gust lock baulk lever for correct operation; and corrective action, if necessary. This AD results from incidents where an elevator gust lock re-engaged without input from the flightcrew, and may have caused a flight control restriction. We are issuing this AD to prevent uncommanded re- engagement of the elevator gust lock, which could result in restriction of the elevator's movement and consequent reduced controllability of the airplane.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Rules and Regulations]
[Pages 6667-6669]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-1149]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23799; Directorate Identifier 2004-NM-141-AD;
Amendment 39-14475; AD 2006-03-11]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model HS 748
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
British Aerospace Model HS 748 airplanes. This AD requires installing a
baulking actuator system for the elevator gust lock; doing a functional
test and an inspection of any previously installed baulking actuator
system for wiring errors; doing repetitive inspections of the gust lock
baulk lever for correct operation; and corrective action, if necessary.
This AD results from incidents where an elevator gust lock re-engaged
without input from the flightcrew, and may have caused a flight control
restriction. We are issuing this AD to prevent uncommanded re-
engagement of the elevator gust lock, which could result in restriction
of the elevator's movement and consequent reduced controllability of
the airplane.
DATES: This AD becomes effective February 24, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 24,
2006.
We must receive comments on this AD by April 10, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
<bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow
the instructions for sending your comments electronically.
<bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your
comments electronically.
<bullet> Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
<bullet> Fax: (202) 493-2251.
<bullet> 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 British Aerospace Regional Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia 20171, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified us that an unsafe condition
may exist on British Aerospace Model HS 748 airplanes. The CAA advises
that there have been two incidents where re-engagement of the elevator
gust lock without input by the flightcrew may have caused a flight
control restriction. Uncommanded re-engagement of the elevator gust
lock, if not corrected, could result in restriction of the elevator's
movement and consequent reduced controllability of the airplane.
Relevant Service Information
British Aerospace has issued BAE Systems (Operations) Limited
Service Bulletin HS748-27-135, Revision 2, dated October 2, 2003. The
service bulletin describes procedures for installing a baulking
actuator system for the elevator gust lock; doing a functional test of
the actuator system for correct operation; and inspecting the gust lock
baulk lever for correct operation. Accomplishing the actions specified
in the service information is intended to adequately address the unsafe
condition. The CAA mandated a previous revision of the service bulletin
(which specified some wiring procedures incorrectly) and issued British
airworthiness directive 003-12-2002 to ensure the continued
airworthiness of these airplanes in the United Kingdom. The CAA has
also issued British airworthiness directive G-2004-0002, dated February
18, 2004, which supersedes British airworthiness directive 003-12-2002,
and requires doing additional actions in accordance with Revision 2 of
the service bulletin.
Service Bulletin HS748-27-135 refers to BAE Systems (Operations)
Limited Alert Service Bulletin HS748-A27-128, Revision 1, dated
December 10, 2002, as an additional source of service information for
accomplishing a check of the rigging of the gust lock system.
Service Bulletin HS748-27-135 also refers to BAE Systems
(Operations) Limited Service Bulletin HS748-A27-76, Revision 3, dated
December 20, 1996, as an additional source of service information for
accomplishing an overlap check of the lever gate stop.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. We have examined the CAA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to prevent uncommanded re-
engagement of the elevator gust lock, which could result in restriction
of the elevator's movement and consequent reduced controllability of
the airplane. This AD requires accomplishing the actions specified in
the service information described previously, except as described in
``Difference Between This AD and the Service Bulletin.''
[[Page 6668]]
Difference Between This AD and the Service Bulletin
Where the service bulletin specifies to inspect the baulk lever for
correct operation but does not specify corrective action, this AD
requires operators to contact the FAA or the CAA (or its delegated
agent) for repair instructions.
Clarification on Wiring Inspections
British airworthiness directive G-2004-0002 specifies to inspect
the baulk lever installation for correct wiring, and correct the wiring
as necessary. The Accomplishment Instructions of Revision 2 of the
service bulletin has a note that states that rework in accordance with
Revision 2 of the service bulletin is needed for wiring that was done
in accordance with Revision 1. This AD requires a general visual
inspection for correct wiring and rerouting the wiring as applicable in
accordance with Revision 2.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
The following table provides the estimated costs to comply with
this AD for any affected airplane that might be imported and placed on
the U.S. Register in the future.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Work labor
Action hours rate per Parts cost Cost per airplane
hour
----------------------------------------------------------------------------------------------------------------
Installation................... 49 $65 $18,500...... $21,685.
Inspection, per inspection 2 $65 None......... $130, per inspection cycle.
cycle.
----------------------------------------------------------------------------------------------------------------
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
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 relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
23799; Directorate Identifier 2004-NM-141-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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 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 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
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.
Examining the Docket
You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, or in 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
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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
[[Page 6669]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-03-11 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-14475. Docket No. FAA-
2006-23799; Directorate Identifier 2004-NM-141-AD.
Effective Date
(a) This AD becomes effective February 24, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model HS 748 series 2A and series 2B airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from incidents where an elevator gust lock
re-engaged without input from the flightcrew, and may have caused a
flight control restriction. We are issuing this AD to prevent
uncommanded re-engagement of the elevator gust lock, which could
result in restriction of the elevator's movement 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.
Installation and Repetitive Inspections
(f) Within 9 months after the effective date of this AD, install
a baulking actuator system for the elevator gust lock in accordance
with the Accomplishment Instructions of BAE Systems (Operations)
Limited Service Bulletin HS748-27-135, Revision 2, dated October 2,
2003.
Note 1: BAE Systems (Operations) Limited Service Bulletin HS748-
27-135, Revision 2, dated October 2, 2003, refers to BAE Systems
(Operations) Limited Alert Service Bulletin HS748-A27-128, Revision
1, dated December 10, 2002; and BAE Systems (Operations) Limited
Service Bulletin HS748-A27-76, Revision 3, dated December 20, 1996;
as additional sources of service information for doing the
installation.
(g) At the later of the times specified in paragraphs (g)(1) or
(g)(2), test the actuator system for correct operation in accordance
with Appendix 2 of BAE Systems (Operations) Limited Service Bulletin
HS748-27-135, Revision 2, dated October 2, 2003. Repeat the
inspection thereafter at intervals not to exceed 750 flight hours or
240 days, whichever occurs first. Correct any operation errors
before further flight in accordance with a method approved by the
FAA or the Civil Aviation Authority (CAA) (or its delegated agent).
(1) 750 flight hours or 240 days after installation of the
actuator system, whichever occurs first.
(2) 750 flight hours or 240 days after the effective date of
this AD, whichever occurs first.
Inspection of Any Installation Done in Accordance With Older Service
Bulletin
(h) For airplanes with a baulking actuator system installed in
accordance with the Accomplishment Instructions of BAE Systems
(Operations) Limited Service Bulletin HS748-27-135, Revision 1,
dated December 10, 2002: Within 750 flight hours or 240 days after
the effective date of this AD, whichever occurs first, do the
actions specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Do a general visual inspection of the actuator system for
correct wiring in accordance with the Accomplishment Instructions of
BAE Systems (Operations) Limited Service Bulletin HS748-27-135,
Revision 2, dated October 2, 2003. Reroute any wiring as applicable
before further flight in accordance with the service bulletin.
(2) Do a functional test of the actuator system in accordance
with Appendix 1 of BAE Systems (Operations) Limited Service Bulletin
HS748-27-135, Revision 2, dated October 2, 2003.
Note 2: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Previous Actions
(i) Actions done before the effective date of this AD in
accordance with BAE Systems (Operations) Limited Service Bulletin
HS748-27-135, Revision 1, dated December 10, 2002, are considered
acceptable for compliance with paragraphs (f) and (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(k) British airworthiness directives G-2004-0002, dated February
18, 2004, and 003-12-2002, also address the subject of this AD.
Material Incorporated by Reference
(l) You must use BAE Systems (Operations) Limited Service
Bulletin HS748-27-135, Revision 2, dated October 2, 2003, to perform
the actions that are required by this AD, unless the AD specifies
otherwise. The Director of the Federal Register approved the
incorporation by reference of this document in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact British Aerospace Regional
Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia
20171, for a copy of this service information. You may review copies
at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.
Issued in Renton, Washington, on January 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-1149 Filed 2-8-06; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2023-10-02
final ruleAirworthiness Directives; Transport and Commuter Category Airplanes
Unsafe Condition: Radio altimeter anomalies that are undetected by the automation or pilot, particularly close to the ground (e.g., landing flare), could lead to loss of continued safe flight and landing. Additional...
2018-23-12
final ruleAirworthiness Directives; Zodiac Aero Evacuation Systems (Also Known as Air Cruisers Company) Airplanes
Unsafe Condition: Reports indicating that affected fusible plugs activated (vented gas) below the rated temperature.
2011-05-10
final ruleAirworthiness Directives; BAE Systems (Operations) Limited Model ATP Airplanes; BAE Systems (Operations) Limited Model HS 748 Airplanes
Unsafe Condition: Non-pinched hinge pin ends may lead to migration of a tab hinge pin out of the hinge, resulting in restricted movement of the tab control and reduced control of the airplane.
2005-23-22 Recurring
final ruleAirworthiness Directives; British Aerospace Model HS 748 Airplanes
Unsafe Condition: Fatigue cracking and corrosion of the rear pressure bulkhead and associated areas, and the fin attachment fittings, particularly the fin link beam, could result in damage to the airplane structure ...
