[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.

-----------------------------------------------------------------------

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