[Federal Register Volume 59, Number 82 (Friday, April 29, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-9988]


[[Page Unknown]]

[Federal Register: April 29, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-33-AD; Amendment 39-8900; AD 94-09-11]

 

Airworthiness Directives; Raytheon Corporate Jets Model BAe 125-
1000A and Hawker 1000 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 Raytheon Corporate Jets Model BAe 125-1000A 
and Hawker 1000 series airplanes. This action requires inspections of 
the thrust reverser system for integrity, and correction of any 
discrepancy found. This amendment is prompted by a report that there is 
a possibility of failure of the drive links (or attachments) on the 
thrust reversers of these airplanes due to the single link design 
concept of the thrust reverser link and lock system. This condition, if 
not corrected, could result in inadvertent deployment of a thrust 
reverser during flight. The actions specified in this AD are intended 
to prevent a significant reduction in the controllability of the 
airplane due to an in-flight deployment of a thrust reverser.

DATES: Effective May 16, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 16, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before June 28, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-33-AD, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
Raytheon Corporate Jets, Inc., 3 Bishops Square, St. Albans Road West, 
Hatfield, Hertfordshire, AL109NE, United Kingdom. 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 Raytheon 
Corporate Jets Model BAe 125-1000A and Hawker 1000 series airplanes. 
The CAA advises that the manufacturer of the thrust reversers on these 
airplanes has conducted a reassessment of the failure modes and effects 
analysis for the thrust reverser system, and has provided to the 
airplane manufacturer additional recommendations for repetitive 
inspection intervals of the system. Results of that reassessment 
revealed that failure of the drive links (or attachments) on the thrust 
reversers can occur due to the single link design concept of the thrust 
reverser link and lock system. This condition, if not corrected, can 
result in inadvertent deployment of a thrust reverser during flight, 
which could result in a significant reduction in the controllability of 
the airplane
    Raytheon Corporate Jets, Inc., has issued Service Bulletin SB 78-
12, dated January 24, 1994, that describes procedures for a detailed 
visual inspection of the thrust reverser drive mechanism to detect wear 
and abrasion and to ensure the security of the attachment of the 
actuator to its drive links, of the drive links to the thrust reverser 
structure, and of the ends of the drive link and link hinges. The 
service bulletin also describes procedures for repetitive inspections 
of the thrust reverser system for structural integrity. Accomplishment 
of these inspections will ensure the continued structural integrity of 
the thrust reverser system. The CAA classified this service bulletin as 
mandatory.
    This airplane model is manufactured in the United Kingdom and is 
type certificated for operation in the United States under the 
provisions of Sec. 21.29 of the Federal Aviation Regulations 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 deployment of 
a thrust reverser in flight and subsequent reduced controllability of 
the airplane. This AD requires repetitive inspections of the thrust 
reverser system for integrity, and correction of any discrepancy found. 
The inspections are required to be accomplished in accordance with the 
service bulletin described previously. Correction of any discrepancy 
found is required to be accomplished in accordance with procedures 
described in the airplane maintenance manual.
    This is considered interim action. The airplane manufacturer 
currently is developing a secondary locking feature on the thrust 
reverser doors. Once this modification is developed, approved, and 
available, the FAA may consider further rulemaking to require its 
installation.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-33-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 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 14 CFR part 
39 of the Federal Aviation Regulations 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:

94-09-11 Raytheon Corporate Jets, Inc.: Amendment 39-8900. Docket 
94-NM-33-AD.

    Applicability: Model BAe 125-1000A and Hawker 1000 series 
airplanes; as listed in Raytheon Corporate Jets Service Bulletin SB 
78-12, dated January 24, 1994; certificated in any category. -
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent inadvertent deployment of a thrust reverser during 
flight, which could result in a significant reduction in the 
controllability of the airplane, accomplish the following:
    (a) Within 60 days or 150 hours time-in-service after the 
effective date of this AD, whichever occurs first: Perform a 
detailed visual inspection of the thrust reverser drive mechanism to 
detect wear and abrasion and to ensure the security of the 
attachment of the actuator to its drive links, of the drive links to 
the thrust reverser structure, and of the ends of the drive link and 
link hinges; in accordance with paragraph 2.B. of Raytheon Corporate 
Jets Service Bulletin SB 78-12, dated January 24, 1994. Prior to 
further flight, correct any discrepancy found, in accordance with 
procedures described in the airplane maintenance manual.
    (b) At intervals not to exceed 150 hours time-in-service after 
accomplishing the inspection required by paragraph (a) of this AD, 
and whenever any stang fairing is removed for any reason: Perform a 
detailed visual inspection of the thrust reverser system to ensure 
its integrity, as specified in paragraphs (b)(1) and (b)(2) of this 
AD.
    (1) If the stang fairing seals are intact: Inspect the visible 
driver links, idler links, and attachment bolts to the thrust 
reverser doors, in accordance with paragraph 2.D.(1) of Raytheon 
Corporate Jets Service Bulletin SB 78-12, dated January 24, 1994. 
Prior to further flight, correct any discrepancy found during this 
inspection, in accordance with procedures described in the airplane 
maintenance manual.

    Note 1: The stang fairings need not be removed during this 
inspection.

    (2) If any stang fairing has been disturbed or if the inspection 
seal is broken: Inspect the appropriate mechanism in accordance with 
paragraph 2.D.(2) of Raytheon Corporate Jets Service Bulletin SB 78-
12, dated January 24, 1994. Prior to further flight, correct any 
discrepancy found, in accordance with procedures described in the 
airplane maintenance manual.
    (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 2: 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 
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the 
airplane to a location where the requirements of this AD can be 
accomplished.
    (e) The inspections shall be done in accordance with Raytheon 
Corporate Jets Service Bulletin SB 78-12, dated January 24, 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 Raytheon Corporate Jets Inc., 3 
Bishops Square, St. Albans Road West, Hatfield, Hertfordshire, 
AL109NE, United Kingdom. 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 May 16, 1994.

    Issued in Renton, Washington, on April 20, 1994.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-9988 Filed 4-28-94; 8:45 am]
BILLING CODE 4910-13-U