[Federal Register Volume 63, Number 73 (Thursday, April 16, 1998)]
[Proposed Rules]
[Pages 18852-18854]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10055]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-87-AD]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Model BAe 146-200A 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain British Aerospace Model 
BAe 146-200A series airplanes. This proposal would require a one-time 
inspection of the gust damper of the elevator control system to 
determine if the gust damper is properly charged, and of the horizontal 
stabilizer to detect cracking of elevator hinge rib 1; and corrective 
action, if necessary. This proposal is prompted by the issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by the proposed AD are 
intended to detect and correct cracking

[[Page 18853]]

of elevator hinge rib 1 of the horizontal stabilizer, which could occur 
if the gust damper of the elevator control system discharges and allows 
the elevator to move freely in ground gust conditions. Such cracking 
could result in damage to the structural attachment of the elevator to 
the horizontal stabilizer, and consequent reduced controllability of 
the airplane.

DATES: Comments must be received by May 18, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-87-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained AI(R) American Support, Inc., 13850 Mclearen Road, Herndon, 
Virginia 20171. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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 98-NM-87-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 98-NM-87-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom, notified the FAA that an unsafe 
condition may exist on certain British Aerospace Model BAe 146-200A 
series airplanes. The elevator control system on this model 
incorporates a gust damper, which, when properly pressurized with 
hydraulic fluid, prevents free movement of the elevators in ground wind 
gusts. The CAA advises that two airplanes, which had been stored in the 
desert for an extended period of time, were each found to have a 
cracked or broken elevator hinge rib 1. Investigation revealed that the 
gust damper of the elevator control system on the airplanes was 
discharged, which may have been caused by deterioration of the gust 
damper seals due to the desert heat. The discharged gust damper of the 
elevator control system allowed the elevators on the airplanes to move 
freely in ground wind gusts, which resulted in high impact loads on the 
elevator hinge rib 1 stops, and consequent cracking of elevator hinge 
rib 1 on these airplanes. Such cracking, if not corrected, could result 
in damage to the structural attachment of the elevator to the 
horizontal stabilizer, and consequent reduced controllability of the 
airplane.

Explanation of Relevant Service Information

    British Aerospace has issued Service Bulletin SB.55-16, dated July 
14, 1997, which describes procedures for performing a one-time visual 
inspection of the gust damper of the elevator control system to 
determine whether the gust damper is properly charged, and recharging 
any gust damper that is found to be improperly charged. This service 
bulletin also describes procedures for performing a one-time detailed 
visual inspection of the horizontal stabilizer, using a borescope, to 
detect cracking of elevator hinge rib 1. Accomplishment of the actions 
specified in the service bulletin is intended to adequately address the 
identified unsafe condition. The CAA classified this service bulletin 
as mandatory and issued British airworthiness directive 010-07-97, 
dated March 2, 1998, in order to assure the continued airworthiness of 
these airplanes in the United Kingdom.

FAA's Conclusions

    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.

Explanation of Requirements of Proposed Rule

    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, the proposed AD would require accomplishment of 
the actions specified in the service bulletin described previously, 
except as discussed in the following paragraph.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer should be contacted for repair instructions if 
any cracking is found in elevator hinge rib 1, this proposal would 
require that discrepant parts be replaced with new or serviceable parts 
prior to further flight, in accordance with replacement instructions 
provided by the manufacturer and approved by the CAA.

Cost Impact

    The FAA estimates that 19 British Aerospace Model BAe 146-200A 
series airplanes of U.S. registry would be affected by this proposed 
AD. It would take approximately 1 work hour per airplane to accomplish 
the proposed inspections, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be $1,140, or $60 per airplane.

[[Page 18854]]

    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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), 40113, 44701.

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

British Aerospace Regional Aircraft (Formerly British Aerospace 
Regional Aircraft Limited, Avro International Aerospace Division; 
British Aerospace, PLC; British Aerospace Commercial Aircraft 
Limited): Docket 98-NM-87-AD.

    Applicability: Model BAe 146-200A series airplanes, as listed in 
British Aerospace Service Bulletin SB.55-16, dated July 14, 1997; 
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 request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking of elevator hinge rib 1 of the 
horizontal stabilizer, which could result in damage to the 
structural attachment of the elevator to the horizontal stabilizer 
and consequent reduced controllability of the airplane; accomplish 
the following:
    (a) Within 60 days after the effective date of this AD, 
accomplish paragraphs (a)(1) and (a)(2) of this AD, in accordance 
with British Aerospace Service Bulletin SB.55-16, dated July 14, 
1997.
    (1) Perform a visual inspection of the gust damper of the 
elevator control system to determine if the gust damper is properly 
charged. If any gust damper is found to be improperly charged, prior 
to further flight, recharge the gust damper in accordance with the 
service bulletin.
    (2) Perform a detailed visual inspection, using a borescope, to 
detect cracking of elevator hinge rib 1, on the left and right side 
of the airplane, in accordance with the service bulletin. If any 
cracking is found, prior to further flight, replace any cracked 
hinge rib 1 with a new or serviceable part, in accordance with a 
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or procedures provided by 
the manufacturer that are approved by the Civil Aviation Authority, 
which is the airworthiness authority for the United Kingdom.
    (b) 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, International Branch, ANM-116, 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, International 
Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (c) 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.

    Note 3: The subject of this AD is addressed in British 
airworthiness directive 010-07-97, dated March 2, 1998.

    Issued in Renton, Washington, on April 9, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 98-10055 Filed 4-15-98; 8:45 am]
BILLING CODE 4910-13-U