[Federal Register Volume 59, Number 182 (Wednesday, September 21, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-23220]
Federal Register / Vol. 59, No. 182 / Wednesday, September 21, 1994 /
[[Page Unknown]]
[Federal Register: September 21, 1994]
VOL. 59, NO. 182
Wednesday, September 21, 1994
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-138-AD; Amendment 39-9027; AD 94-19-05]
Airworthiness Directives; British Aerospace Model BAC 1-11-200
and -400 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain British Aerospace Model BAC 1-11-200 and -400
series airplanes. This action requires revising the Limitations Section
of the FAA-approved Airplane Flight Manual (AFM) to limit reversion of
the flight controls to manual (unpowered) operation. This action also
provides optional terminating action for the AFM limitation. This
amendment is prompted by reports of cracking of certain brackets and
levers in the primary flight control system due to residual stresses,
mechanical loading, and material properties changes associated with
aging. The actions specified in this AD are intended to prevent loss of
integrity of the primary flight control system due to structural
failure of the brackets or levers.
DATES: Effective October 6, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 6, 1994.
Comments for inclusion in the Rules Docket must be received on or
before November 21, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-138-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
British Aerospace, Inc., 22070 Broderick Drive, Sterling, Virginia
20166. This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom, recently notified
the FAA that an unsafe condition may exist on certain British Aerospace
Model BAC 1-11-200 and -400 series airplanes. The CAA advises that it
has received reports of cracking of certain brackets and levers in the
primary flight control system. These brackets and levers were
manufactured from L53 aluminum alloy casting material. Investigation
has revealed that the cracking may be attributed to a combination of
residual stresses, mechanical loading, and material properties changes
associated with aging. Cracking of these brackets and levers could lead
to structural failure of these components. This condition, if not
corrected, could result in loss of integrity of the primary flight
control system.
British Aerospace has issued Alert Service Bulletin 27-A-PM6025,
Issue 1, dated March 23, 1994, which specifies a new operating
restriction for reversion of the flight controls to manual (unpowered)
operation. Limiting /such reversion to emergency situations only will
greatly reduce the probability that flight control system brackets and
levers (manufactured from L53 aluminum alloy casting material) will
experience higher stresses, and thereby higher probability of
structural failure associated with manual operation of the flight
control systems.
The alert service bulletin also describes procedures for repetitive
detailed visual inspections to detect cracking of the rudder pedal
pivot brackets, elevator pivot levers, and aileron pulley brackets
(manufactured from L53 aluminum alloy casting material) in the primary
flight control system, replacement of any cracked bracket or lever with
a serviceable part, and application of water displacing fluid to the
brackets and levers. The CAA classified this alert service bulletin as
mandatory in order to assure the continued airworthiness of these
airplanes in the United Kingdom.
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. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, this AD is being issued to prevent loss of the
integrity of the primary flight control system. This AD requires
revising the Limitations Section of the FAA-approved Airplane Flight
Manual (AFM) to limit reversion of the flight controls to manual
(unpowered) operation. This AD also provides for an optional
terminating action for the AFM limitation, consisting of inspections,
replacement (as necessary), and application of water displacing fluid,
as specified in the alert service bulletin described previously.
The FAA is considering further rulemaking to require accomplishment
of the currently optional terminating action. However, the proposed
compliance time for those actions is sufficiently long so that notice
and time for public comment would not be impracticable.
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 shall 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 rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-138-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-19-05 British Aerospace Airbus Limited (formerly British
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft
Group): Amendment 39-9027. Docket 94-NM-138-AD.
Applicability: Model BAC 1-11-200 and -400 series airplanes
having rudder pedal pivot brackets, elevator pivot levers, or
aileron pulley brackets (manufactured from L53 aluminum alloy
casting material) identified in British Aerospace Alert Service
Bulletin 27-A-PM6025, Issue 1, dated March 23, 1994; certificated in
any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the integrity of the primary flight control
system, accomplish the following:
(a) Within 30 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following limitation; and thereafter operate
the airplane in accordance with that limitation. This may be
accomplished by inserting a copy of this AD in the AFM.
``The flight controls shall not be reverted to manual
(unpowered) operation unless an emergency situation exists during
which the flight crew must revert the flight controls to manual
operation in order to maintain control of the airplane.''
(b) Accomplishment of a detailed visual inspection to detect
cracking of the elevator pivot levers, in accordance with paragraph
2.2 of the Accomplishment Instructions of British Aerospace Alert
Service Bulletin 27-A-PM6025, Issue 1, dated March 23, 1994;
constitutes terminating action for the AFM limitation required by
paragraph (a) of this AD, and that limitation may be removed from
the AFM. Repeat the inspection thereafter at intervals not to exceed
18 months. If any elevator pivot lever is cracked, prior to further
flight, replace it with a serviceable part and apply water
displacing fluid to the levers, in accordance with the alert service
bulletin.
(c) 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, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager,
Standardization Branch, ANM-113.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(e) The inspection and corrective actions shall be done in
accordance with British Aerospace Alert Service Bulletin 27-A-
PM6025, Issue 1, dated March 23, 1994. 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 British Aerospace, Inc., 22070 Broderick Drive,
Sterling, Virginia 20166. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on October 6, 1994.
Issued in Renton, Washington, on September 14, 1994.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-23220 Filed 9-20-94; 8:45 am]
BILLING CODE 4910-13-U
