[Federal Register Volume 60, Number 73 (Monday, April 17, 1995)]
[Proposed Rules]
[Pages 19179-19181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-9347]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-183-AD]
Airworthiness Directives; British Aerospace Model BAC 1-11 200
and 400 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to British Aerospace Model BAC
1-11 200 and 400 series airplanes, that currently requires structural
inspections and repairs or replacements, as necessary. This action
would require additional inspections of certain Structural Significant
Items (SSI) and expansion of the inspection area for certain other
SSI's. This proposal is prompted by the results of a structural
integrity audit, which indicated that in order to maintain the
structural integrity of these airplanes as they approach or exceed the
manufacturer's original fatigue design life goal, certain SSI's need to
be inspected. The actions specified by the proposed AD are intended to
ensure continuing structural integrity of these airplanes.
DATES: Comments must be received by May 26, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-183-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 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.
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:
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 94-NM-183-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-03, Attention: Rules
Docket No. 94-NM-183-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On September 16, 1988, the FAA issued AD 87-24-06 R1, amendment 39-
6037 (53 FR 37993, September 29, 1988), applicable to British Aerospace
Model BAC 1-11 200 and 400 series airplanes. That AD requires
structural inspections and repairs or replacements, as necessary, in
order to ensure the continuing airworthiness of these airplanes as they
approach or exceed the manufacturer's original fatigue design life
goal. That action was prompted by a structural re-evaluation, which
identified certain structurally significant items (SSI) in which
undetected fatigue cracks could propagate and compromise the structural
integrity of these airplanes. The requirements of that AD are intended
to ensure continuing structural integrity of these airplanes.
Since the issuance of that AD, British Aerospace has conducted a
structural integrity audit to assess the structural inspection program
of Model BAC 1-11 200 and 400 series airplanes. The results of this
audit indicated that, in order to maintain the structural integrity of
these airplanes as they approach or exceed 85,000 landings (the
manufacturer's original fatigue design life goal), certain additional
SSI's need to be inspected and the inspection area for certain other
SSI's needs to be expanded.
British Aerospace has issued BAC 1-11 Alert Service Bulletin 51-A-
PM5830, Issue 4, dated January 28, 1993. This revision of the alert
service bulletin adds ten inspections of the doors to the structural
inspection program. Some of these inspections merely expand the area of
inspection for certain SSI's. Additionally, this revision of the alert
service bulletin describes procedures for repair or replacement of
cracked parts. Table 3 of the alert service bulletin specifies life
limits for certain components in the engine mount/attachment structure
of certain airplanes. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom, has classified this
revision of the alert 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 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, the proposed AD would supersede AD 87-24-06 R1 to
require a revision of the FAA-approved maintenance inspection program
to [[Page 19180]] include additional structural inspections of certain
SSI's, expansion of the inspection area for certain other SSI's, and
repair or replacement of cracked parts; and establishes a life limit
for the engine mount/attachment structure on certain airplanes. The
actions would be required to be accomplished in accordance with the
alert service bulletin described previously.
However, certain inspections and repairs specified in the alert
service bulletin have been excluded from the requirements of this
proposal. Those inspections and repairs have been identified in the
alert service bulletin as Maintenance Planning Guide (MPG), Reference
Numbers 52-10-6R and 53-10-2R. The actions specified in MPG 52-10-6R
are currently required by AD 87-21-06, amendment 39-5744 (52 FR 38396,
October 16, 1987), and those in MPG 53-10-29R will be addressed in a
separate rulemaking action.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this long-standing requirement.
The FAA estimates that 31 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 158 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $293,880, or $9,480 per airplane, per inspection cycle.
The total 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.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-6037 (53 FR
37993, September 29, 1988), and by adding a new airworthiness directive
(AD), to read as follows:
British Aerospace Airbus Limited (Formerly British Aerospace
Commercial Aircraft Limited, British Aerospace Aircraft Group):
Docket 94-NM-183-AD. Supersedes AD 87-24-06 R1, Amendment 39-6037.
Applicability: Model BAC 1-11 200 and 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 (f) 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 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.
To ensure continuing structural integrity of the airplane,
accomplish the following:
(a) Within 6 months after November 3, 1988 (the effective date
of AD 87-4-06 R1, amendment 39-6037), incorporate a revision into
the FAA-approved maintenance inspection program which requires
inspections, repairs, and replacements, as necessary, in accordance
with Tables 1, 2, and 3 of British Aerospace BAC 1-11 Alert Service
Bulletin 51-A-PM5830, Issue 3, dated March 19, 1987. The revision to
the maintenance inspection program must include procedures to notify
the manufacturer when Structural Significant Items are found cracked
or otherwise significantly deteriorated. Information collection
requirements contained in this regulation have been approved by the
Office of Management and Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have
been assigned OMB Control Number 2120-0056. The inspection
thresholds, repetitive intervals and inspection techniques are
listed in the alert service bulletin.
(b) Within 6 months after the effective date of this AD, replace
the revision of the FAA-approved maintenance inspection program
required by paragraph (a) of this AD, with a revision which requires
inspections, repairs, and replacements, as necessary, in accordance
with Tables, 1 (except Maintenance Planning Guide Reference Numbers
52-10-6R and 53-10-29R), 2, and 3 of British Aerospace BAC 1-11
Alert Service Bulletin 51-A-PM5830, Issue 4, dated January 28, 1993.
The revision to the maintenance inspection program must include
procedures to notify the manufacturer when Structural Significant
Items are found cracked or otherwise significantly deteriorated.
Information collection requirements contained in this regulation
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056. The inspection thresholds, repetitive intervals and inspection
techniques are listed in the alert service bulletin.
Note 2: Maintenance Planning Guide (MPG) Reference Numbers 52-
10-6R and 53-10-29R, listed in Table 1 of British Aerospace BAC 1-11
Alert Service Bulletin 51-A-PM5830, Issue 4, dated January 28, 1993,
are excluded from the requirements of this AD for the following
reasons:
[[Page 19181]]
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MPG reference
No. Reason
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52-10-6R-....... Required by AD 87-21-06, amendment 39-5744.
53-10-29R-...... Will be addressed in a separate rulemaking action.
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(c) Within one year after November 3, 1988 (the effective date
of AD 87-24-06 R1, amendment 39-6037), or prior to the accumulation
of the number of landings listed in the landing threshold indicated
in British Aerospace BAC 1-11 Alert Service Bulletin 51-A-PM5830,
Issue 3, dated March 19, 1987, whichever occurs later, and
thereafter, at intervals not to exceed the number of landings
specified in the alert service bulletin, accomplish the inspections,
repairs, and replacements, as necessary, of the Structural
Significant Items identified in Tables 1, 2, and 3 of that service
bulletin.
(d) Within one year after the effective date of this AD, or
prior to the accumulation of the number of landings listed in the
landing threshold indicated in British Aerospace BAC 1-11 Alert
Service Bulletin 51-A-PM5830, Issue 4, dated January 28, 1993,
whichever occurs later, and thereafter, at intervals not to exceed
the number of landings specified in the alert service bulletin,
accomplish the inspections, repairs, and replacements, as necessary,
of the Structural Significant Items identified in Tables 1 (except
Maintenance Planning Guide Reference Numbers 52-10-6R and 53-10-
29R), 2, and 3 of the alert service bulletin.
Note 3: For operators that have accomplished this inspection
previously in accordance with the requirements of AD 87-24-06 R1,
amendment 39-6037: This paragraph requires that the next scheduled
inspection for that SSI be performed within the repetitive interval
specified for that SSI in the alert service bulletin after the last
inspection performed in accordance with the requirements of AD 87-
24-06 R1 for that SSI.
(e) For any cracked structure detected during any inspection
required by this AD, prior to further flight, accomplish paragraph
(e)(1), (e)(2), or (e)(3) of this AD.
(1) Replace the cracked part with a serviceable part of the same
part number, in accordance with the Airplane Maintenance Manual. Or
(2) Repair the cracked structure in accordance with the
Structural Repair Manual, listed in the service bulletin. Or
(3) Repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(f) 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(g) 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.
Issued in Renton, Washington, on April 11, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-9347 Filed 4-14-95; 8:45 am]
BILLING CODE 4910-13-U
