[Federal Register Volume 63, Number 50 (Monday, March 16, 1998)]
[Proposed Rules]
[Pages 12708-12710]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6592]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-03-AD]
RIN 2120-AA64


Airworthiness Directives; British Aerospace (Operations) Limited 
Model B.121 Series 1, 2, and 3 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain British Aerospace (Operations) Limited 
(British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. The 
proposed AD would require installing an inspection opening in the area 
of the main spar web, repetitively inspecting the area at the main spar 
web for cracks and the area of the wing to fuselage attach bolt holes 
for corrosion, and repairing or replacing any cracked or corroded part. 
The

[[Page 12709]]

proposed AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for the United 
Kingdom. The actions specified by the proposed AD are intended to 
prevent structural failure of the main spar web area caused by fatigue 
cracking or separation of the wing from the fuselage caused by corroded 
attach bolt holes, which could result in loss of control of the 
airplane.

DATES: Comments must be received on or before April 17, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-CE-03-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106. Comments may be inspected at this location 
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from British Aerospace (Operations) Limited, British Aerospace Regional 
Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; 
telephone: (01292) 479888; facsimile: (01292) 479703. This information 
also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Roger Chudy, Aerospace Engineer, 
Small Airplane Directorate, Aircraft Certification Service, 1201 
Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-
6932; facsimile: (816) 426-2169.

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 should 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 that summarizes 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 No. 98-CE-03-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, Central Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 98-CE-03-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    The Civil Airworthiness 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 B.121 
Series 1, 2, and 3 airplanes. The CAA reports findings of fatigue 
cracking in the area of the main-spar next to the undercarriage attach 
points, and corrosion at the wing/spar attach bolt holes.
    These conditions, if not corrected in a timely manner, could result 
in structural failure of the main spar web area caused by fatigue 
cracking or separation of the wing from the fuselage caused by corroded 
attach bolt holes, with consequent loss of control of the airplane.

Relevant Service Information

    British Aerospace has issued PUP Service Bulletin No. B121/102, 
Revision No. 1, Issued April 16, 1997, which specifies procedures for 
the following:

--Installing an inspection opening and inspecting, using eddy current 
methods, the area at the main spar web for cracks; and
--Visually inspecting the area of the wing to fuselage attach bolt 
holes for corrosion.

    The CAA classified this service bulletin as mandatory and issued 
British AD 005-10-96, not dated, in order to assure the continued 
airworthiness of these airplanes in the United Kingdom.

The FAA's Determination

    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 (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, including the service information referenced 
above; and determined that AD action is necessary for products of this 
type design that are certificated for operation in the United States.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other British Aerospace Model B.121 Series 1, 2, 
and 3 airplanes of the same type design registered in the United 
States, the FAA is proposing AD action. The proposed AD would require 
installing an inspection opening in the area of the main spar web, 
repetitively inspecting the area at the main spar web for cracks and 
the area of the wing to fuselage attach bolt holes for corrosion, and 
repairing or replacing any cracked or corroded part. Accomplishment of 
the proposed inspections would be required in accordance with British 
Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued 
April 16, 1997. If necessary, the proposed repair or replacement would 
be required in accordance with a scheme obtained from the manufacturer 
through the FAA, Small Airplane Directorate.

Cost Impact

    The FAA estimates that 2 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 18 
workhours per airplane to accomplish the proposed initial inspection 
and inspection opening installation, and that the average labor rate is 
approximately $60 an hour. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be $2,160, 
or $1,080 per airplane. These figures only take into account the cost 
of the proposed initial inspections and inspection opening 
installation, and do not take into account the cost of repetitive 
inspections. The FAA has no way of determining the number of repetitive 
inspections each owner/operator of the affected airplanes will incur.

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

[[Page 12710]]

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 action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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 has been placed 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 a new airworthiness directive 
(AD) to read as follows:

British Aerospace (Operations) Limited:  Docket No. 98-CE-03-AD.

    Applicability: Model B.121 Series 1, 2, and 3 airplanes, all 
serial numbers, 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 (e) 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 in the body of this AD, unless 
already accomplished.
    To prevent structural failure of the main spar web area caused 
by fatigue cracking or separation of the wing from the fuselage 
caused by corroded attach bolt holes, which could result in loss of 
control of the airplane, accomplish the following:
    (a) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, accomplish the following in accordance 
with the Accomplishment Instructions section, Appendix 1, and 
Appendix 2 of British Aerospace PUP Service Bulletin No. B121/102, 
Revision No. 1, dated April 16, 1997:
    (1) Install an inspection opening and inspect, using eddy 
current methods, the area at the main spar web for cracks; and
    (2) Visually inspect the area of the wing to fuselage attach 
bolt holes for corrosion.
    (b) Within 800 hours TIS after the initial inspection required 
by paragraph (a), including subparagraphs, of this AD, and 
thereafter at intervals not to exceed 800 hours TIS, reinspect the 
area of the main spar web as specified in paragraph (a), including 
all subparagraphs, of this AD.
    (c) If any cracks or corrosion damage is found during any 
inspection required by this AD, prior to further flight, accomplish 
the following:
    (1) Obtain a repair or replacement scheme from the manufacturer 
through the FAA, Small Airplane Directorate, at the address 
specified in paragraph (e) of this AD; and
    (2) Incorporate this scheme and continue to repetitively inspect 
as required by paragraph (b) of this AD, unless specified 
differently in the instructions to the repair or replacement scheme.
    (d) Special flight permits may be issued in accordance with 
Secs. 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) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Small Airplane 
Directorate, Aircraft Certification Service, 1201 Walnut, suite 900, 
Kansas City, Missouri 64106. The request shall be forwarded through 
an appropriate FAA Maintenance Inspector, who may add comments and 
then send it to the Manager, Small Airplane Directorate.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (f) Questions or technical information related to British 
Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued 
April 16, 1997, should be directed to British Aerospace (Operations) 
Limited, British Aerospace Regional Aircraft, Prestwick 
International Airport, Ayrshire, KA9 2RW, Scotland; telephone: 
(01292) 479888; facsimile: (01292) 479703. This service information 
may be examined at the FAA, Central Region, Office of the Regional 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

    Note 3: The subject of this AD is addressed in British AD 005-
10-96, not dated.

    Issued in Kansas City, Missouri, on March 9, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-6592 Filed 3-13-98; 8:45 am]
BILLING CODE 4910-13-U