[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]
BILLING CODE 4910-13-U