[Federal Register Volume 60, Number 218 (Monday, November 13, 1995)]
[Rules and Regulations]
[Pages 56939-56941]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27786]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-217-AD; Amendment 39-9424; AD 95-23-04]
Airworthiness Directives; British Aerospace Model BAC 1-11 400
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 all British Aerospace Model BAC 1-11 400 series
airplanes. This action requires an inspection of the rod ends of the
lift dumper to detect drill holes; a dye penetrant inspection to detect
any cracking of drilled holes; and replacement of the rod end with an
undrilled rod end, if necessary. This amendment is prompted by a report
that, during a routine examination of the operating mechanism of the
lift dumper, two cracked aft rod ends were found. Investigation
revealed that holes had been drilled in the rod ends for grease nipples
during manufacturing, and that cracking had developed at the holes. The
actions specified in this AD are intended to prevent asymmetric
deployment and subsequent lateral control problems due to cracking of
either pair of aft rod ends of the operating mechanism of the lift
dumper.
DATES: Effective November 28, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 28, 1995.
Comments for inclusion in the Rules Docket must be received on or
before January 12, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-217-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056.
The service information referenced in this AD may be obtained from
British Aerospace, Airbus Limited, P.O. Box 77, Bristol BS99 7AR,
England. 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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1149.
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 1-11 400 series airplanes. The CAA advises that, during a
routine examination of the operating mechanism of the lift dumper,
cracking was found on two aft rod ends (one per wing) on a British
Aerospace Model BAC 1-11 500 series airplane. Investigation revealed
that, during manufacture, holes had been drilled in
[[Page 56940]]
the rod ends for grease nipples. The cracking had developed at the
point where an external grease nipple had been fitted to the eye-end of
the rods, and caused the failure of the rod ends. This condition, if
not corrected, could result in uncontrolled asymmetric deployment and
subsequent lateral control problems, particularly at low speeds with
the flaps extended.
The subject aft rod ends installed on Model BAC 1-11 500 series
airplanes are similar to those installed on Model BAC 1-11 400 series
airplanes. Therefore, Model BAC 1-11 400 series airplanes are subject
to this same unsafe condition. (The Model BAC 1-11 500 is not type
certificated for operation in the United States.)
British Aerospace has issued Alert Service Bulletin 27-A-PM6034,
Issue 1, dated October 6, 1995, which describes procedures for visual
inspection to detect drill holes for a grease nipple in the housing of
the rod ends. If drill holes are detected, the alert service bulletin
also describes procedures for a dye penetrant inspection to detect any
cracking of the drill holes, and eventual replacement of the rod end
with an undrilled rod end. 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 asymmetric
deployment and subsequent lateral control problems, particularly at low
speeds with the flaps extended, due to failure of either pair of aft
rod ends of the lift dumper operating mechanism. This AD requires a
visual inspection of the lift dumper to detect drill holes in the rod
ends. This AD also requires a dye penetrant inspection to detect any
cracking if drill holes are detected, and eventual replacement of the
rod ends with rod ends that have not been drilled for a grease nipple.
The actions are required to be accomplished in accordance with the
alert service bulletin described previously.
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 95-NM-217-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. 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-23-04 British Aerospace Airbus Limited (Formerly British
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft
Group): Amendment 39-9424. Docket 95-NM-217-AD.
Applicability: All Model BAC 1-11 400 series airplanes,
certificated in any category.
Note 1: This AD applies to each airplane 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 airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (e) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an
[[Page 56941]]
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any airplane from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
Note 2: Inspections and replacement of the rod ends in
accordance with British Aerospace Campaign Wire 27-CW-PM6034, dated
May 18, 1995, are considered to be acceptable for compliance with
the actions specified in this AD.
To prevent asymmetric deployment and subsequent lateral control
problems, particularly at low speeds with the flaps extended, due to
cracking of either pair of aft rod ends of the lift dumper operating
mechanism, accomplish the following:
(a) Within 100 flight hours or 30 days after the effective date
of this AD, whichever occurs first: Perform a visual inspection to
detect drill holes for a grease nipple in the housing of the rod
ends of the lift dumper, in accordance with British Aerospace Alert
Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995.
(b) If no drill holes for a grease nipple are found, no further
action is required by this AD.
(c) If any drill hole for a grease nipple is found, prior to
further flight, perform a dye penetrant inspection to detect
cracking of the rod eye-end, in accordance with British Aerospace
Alert Service Bulletin 27-A-PM6034, Issue 1, dated October 6, 1995.
Pay particular attention to the area surrounding the grease nipple
hole.
(1) If no cracking is found, accomplish the requirements of
paragraphs (c)(1)(i) and (c)(1)(ii) of this AD.
(i) Repeat the inspection required by paragraph (c) of this AD
thereafter at intervals not to exceed 100 flight hours until the rod
ends are replaced in accordance with paragraph (c)(1)(ii) of this
AD.
(ii) Within 60 days after the effective date of this AD, replace
the drilled rod end with an undrilled rod end, in accordance with
the alert service bulletin. Accomplishment of this replacement
constitutes terminating action for the inspections required by
paragraph (c)(1)(i) of this AD.
(2) If any cracking is found, prior to further flight, replace
the rod end with an undrilled rod end, in accordance with British
Aerospace Alert Service Bulletin 27-A-PM6034, Issue 1, dated October
6, 1995.
(d) As of the effective date of this AD, no person shall install
on any airplane a rod end, part number RMX 7GUE, having any holes
drilled for a grease nipple; nor shall any person drill any holes
for a grease nipple in a rod end having part number RMX 7GUE on any
airplane.
(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, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(f) 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.
(g) The inspections and replacement of the rod ends shall be
done in accordance with British Aerospace Alert Service Bulletin 27-
A-PM6034, Issue 1, dated October 6, 1995. This incorporation by
reference was approved by the Director of the Rederal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from British Aerospace, Airbus Limited, P.O. Box 77,
Bristol BS99 7AR, England. 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.
(h) This amendment becomes effective on November 28, 1995.
Issued in Renton, Washington, on November 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-27786 Filed 11-9-95; 8:45 am]
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