[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
