[Federal Register Volume 61, Number 56 (Thursday, March 21, 1996)]
[Rules and Regulations]
[Pages 11534-11536]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-6386]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-164-AD; Amendment 39-9544; AD 96-06-07]


Airworthiness Directives; British Aerospace Model BAC 1-11 200 
and 400 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 
series airplanes, that currently requires visual inspections to detect 
cracks in the flight deck canopy area, and repair, if necessary. This 
amendment reduces the inspection threshold and repetitive inspection 
interval, and identifies specific structural members to be inspected. 
This amendment also requires eddy current inspections to detect cracks 
of the top sill members at station 82.5, and replacement of cracked 
parts with new parts, or repair of the top sill members. This amendment 
is prompted by reports of additional cracking found in the structural 
members in the flight deck canopy area of the affected airplanes. The 
actions specified by this AD are intended to ensure that cracking in 
the flight deck canopy area is detected and corrected in a timely 
manner; such cracking could result in reduced structural integrity of 
the cockpit frame and the adjacent fuselage structure.

DATES: Effective April 22, 1996.
    The incorporation by reference of British Aerospace Alert Service 
Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, listed in the 
regulations is approved by the Director of the Federal Register as of 
April 22, 1996.
    The incorporation by reference of British Aerospace Alert Service 
Bulletin 53-A-PM5994, Issue 2, dated June 5,

[[Page 11535]]
1990, listed in the regulations was approved previously by the Director 
of the Federal Register as of February 25, 1991 (56 FR 1569, January 
16, 1991).

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol 
BS99 7AR, England. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 91-02-12, 
amendment 39-6861 (56 FR 1569, January 16, 1991), which is applicable 
to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, 
was published in the Federal Register on January 3, 1996 (61 FR 131). 
The action proposed to supersede AD 91-02-12 to continue to require 
repetitive visual inspections to detect cracks in the flight deck 
canopy area, and repair, if necessary. However, it also proposed to:
    1. reduce the inspection threshold and repetitive inspection 
interval,
    2. identify specific structural members to be inspected,
    3. require repetitive eddy current inspections to detect cracks of 
the top sill members at station 82.5, and
    4. require replacement of cracked parts with new parts, or repair 
of the top sill members.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public. 
The FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed.
    There are approximately 31 Model BAC 1-11 200 and 400 series 
airplanes of U.S. registry that will be affected by this AD.
    The actions that are currently required by AD 91-02-12 take 
approximately 18 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact on U.S. operators of the actions currently required is estimated 
to be $33,480, or $1,080 per airplane.
    The new actions that are required by this new AD will take 
approximately 19 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact on U.S. operators of the new requirements of this AD is 
estimated to be $35,340, or $1,140 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    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.
    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) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-6861 (56 FR 
1569, January 16, 1991), and by adding a new airworthiness directive 
(AD), amendment 39-9544, to read as follows:

96-06-07 British Aerospace Airbus Limited (Formerly British 
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft 
Group): Amendment 39-9544. docket 94-NM-164-AD. Supersedes AD 91-02-
12, Amendment 39-6861.

    Applicability: All 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 
otherwise 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, unless accomplished 
previously.
    To prevent reduced structural integrity of the cockpit frame and 
the adjacent fuselage structure, accomplish the following:
    (a) Prior to the accumulation of 30,000 total landings, or 
within 6 months after February 25, 1991 (the effective date of AD 
91-02-12, amendment 39-6861), whichever occurs later; and thereafter 
at intervals not to exceed 5,000 landings: Perform a visual 
inspection to detect cracks of the flight deck canopy area, in 
accordance with British Aerospace Alert Service Bulletin 53-A-
PM5994, Issue 2, dated June 5, 1990; or Issue 3, dated April 8, 
1993. Pay particular attention to the top sill joint strap, the top 
sill intercostal, the frame at Station 113, and the top sill boom 
and web. Repeat this inspection until the inspections required by 
paragraph (c) of this AD are accomplished. After the effective date 
of this AD, the inspection shall be accomplished only in accordance 
with Issue 3 of the alert service bulletin.
    (b) If any crack is found during the inspection required by 
paragraph (a) of this AD, prior to further flight, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate. Following 
accomplishment of the repair, repeat the inspection required by 
paragraph (a) of this AD thereafter at intervals not to exceed 5,000 
landings until the inspections required by paragraph (c) of this AD 
are accomplished.
    (c) Perform a detailed visual inspection to detect cracks of the 
top sill joint strap at station 82.5, of the frame at station 113, 
and of the frame at station 160.5 (left-hand side only) between 
stringers 13 and 15; and an eddy current inspection to detect cracks 
of the top sill members at station 82.5. Perform these inspections 
in accordance with British Aerospace Airbus Limited Alert Service 
Bulletin 53-A-PM5994, Issue 3, dated April

[[Page 11536]]
8, 1993, at the time specified in paragraph (c)(1) or (c)(2) of this 
AD, as applicable. Accomplishment of these inspections terminates 
the repetitive inspection requirement of paragraph (a) of this AD.
    (1) For airplanes operating at a maximum cabin differential 
pressure not exceeding 7.5 pounds per square inch (psi): Perform the 
inspections at the later of the times specified in paragraphs 
(c)(1)(i) and (c)(1)(ii) of this AD. Thereafter, repeat these 
inspections at intervals not to exceed 5,000 landings or 7,500 hours 
time-in-service, whichever occurs first.
    (i) Prior to the accumulation of 20,000 total landings since 
date of entry into service; or
    (ii) Within 1,200 landings or 12 months after the effective date 
of this AD, whichever occurs later.
    (2) For airplanes operating at a maximum cabin differential 
pressure greater than 7.5 psi, but not exceeding 8.2 psi, including 
those airplanes having incorporated British Aerospace Airbus Limited 
Modification PM3187: Perform the inspections at the later of the 
times specified in paragraphs (c)(2)(i) and (c)(2)(ii) of this AD. 
Thereafter, repeat these inspections at intervals not to exceed 
3,500 landings or 5,250 hours time-in-service, whichever occurs 
first.
    (i) Prior to the accumulation of 14,000 total landings since 
date of entry into service; or
    (ii) Within 800 landings or 12 months after the effective date 
of this AD, whichever occurs later.

    Note 2: British Aerospace Airbus Limited Modification PM3187 
increases the cabin differential pressure from the normal 7.5 psi to 
8.2 psi. If Modification PM3187 has been incorporated on the 
airplane, that airplane is considered to be subject to the 
requirements of paragraph (c)(2) of this AD.

    (d) If any crack is found during any inspection required by 
paragraph (c) of this AD, prior to further flight, accomplish the 
requirements of paragraph (d)(1), (d)(2), or (d)(3), as applicable.
    (1) For cracking of the joint strap, doubler, or angle at the 
sill joint at station 82.5: Replace the cracked part with a new part 
in accordance with British Aerospace Airbus Limited Alert Service 
Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993.
    (2) For cracking of the frame at station 113: Repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113.
    (3) For cracking of the frame at station 160.5: Repair in 
accordance with the Structural Repair Manual, as specified in 
British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5994, 
Issue 3, dated April 8, 1993.
    (e) 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. 
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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (f) 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.
    (g) The inspections shall be done in accordance with British 
Aerospace Alert Service Bulletin 53-A-PM5994, Issue 2, dated June 5, 
1990; or British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 
3, dated April 8, 1993. The incorporation by reference of British 
Aerospace Alert Service Bulletin 53-A-PM5994, Issue 2, dated June 5, 
1990, was approved previously by the Director of the Federal 
Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as 
of February 25, 1991 (56 FR 1569, January 16, 1991). The 
incorporation by reference of British Aerospace Alert Service 
Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, 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, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 
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.
    (h) This amendment becomes effective on April 22, 1996.

    Issued in Renton, Washington, on March 12, 1996.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-6386 Filed 3-20-96; 8:45 am]
BILLING CODE 4910-13-P